Directed energy deposition to facilitate high speed applications

Abstract

To provide methods, apparatuses and systems for controlling the density of a fluid near a functional object in order to improve one or more relevant performance metrics.SOLUTION: In certain embodiments, the present invention relates to forming a low density region near the object utilizing a directed energy deposition device to deposit energy along one or more paths in the fluid. In certain embodiments, the present invention relates to synchronizing energy deposition with one or more parameters impacting the functional performance of the object.SELECTED DRAWING: Figure 37

Description

[Technical field]

[0001] (CROSS REFERENCE TO RELATED APPLICATIONS) This application is jointly filed with: (1) International Application No. PCT / US2016 / 038239, filed on June 17, 2016; No. 15 / 186,337, filed on May 17, 2015; and (3) U.S. Provisional Patent Application No. 15 / 186,337, filed on June 18, 2015. All of the above-referenced related applications are hereby incorporated by reference in their entirety. , incorporated herein by reference.

[0002] In addition, each of the following United States patents is incorporated herein by reference in its entirety: Incorporated in: U.S. Patent No. 6,527,221, issued March 4, 2003; U.S. Patent No. 7,063,288 issued on October 17, 2006, U.S. Patent No. 7,121,511 issued on January 1, 2010, U.S. Patent No. 7,648,100 issued on December 19, 2011, and U.S. Patent No. 8,000 issued on December 20, 2011. No. 79,544, issued March 27, 2012; U.S. Patent No. 8,141,811, issued August 20, 2013; U.S. Patent No. 8,511,612 granted on September 17, 2013, U.S. Patent No. 8,534,595 granted on September 17, 2014, No. 8,827,211 issued on September 9, 2013, and U.S. Pat. No. 6,313,433 issued on February 24, 2015. No. 8,960,596.

[0003] FIELD OF THEINVENTION Many applications, such as flow control, drag reduction, and vehicle control, among others Energy deposition techniques have been disclosed in the past to achieve dramatic effects in A study of the huge benefits of energy deposition has shown that the benefits of energy deposition are not obtained when no changes are made. Decisions about how and / or when to deposit energy to enhance the benefits of Several modifications can be made. One such modification is the combination of energy deposition and one or more To synchronize, "time" or "phase" the effects of other processes, The energy deposition may be controlled by such other methods to achieve a desired benefit or maximize a desired effect. The term "synchronize," "time" or "align" refers to the process of "Coordinate" means to time an event or process relative to one or more other events and / or processes. (They can be used interchangeably to refer to such events and / or Processes include, but are not limited to: propulsion processes; fluid mechanical processes; chemical processes; specific motions; the injection, addition, and / or transfer of additional energy or deposition;injection, addition, and / or deposition of further material;removal of energy;removal of material; pressure changes; application of one or more forces; combustion processes; ignition processes; explosion processes. Furthermore, the concept of energy deposition does not involve adding energy to a medium or causing heating of the medium. This heating or energy deposition is broadly interpreted to include any process that This causes the medium to expand faster than the original density, resulting in areas of the medium that are less dense than the original medium. This can be done quickly enough (e.g., instantaneously) so that it remains after tension. Another possibility is Energy deposition and / or processes that result in heating produce a phase change in the medium. and thereby determining the density and / or other properties, e.g. In particular, the density, viscosity and / or strength can be modified. These changes in the one or more media, including the degree of flow, may result in changes in the flow characteristics of the one or more media. and may also result in other property changes and responses of the affected medium.

[0004] By reducing the resistance when crossing a loom, increasing the passing speed in loom applications such as air jets, water jets, shuttles, picks, etc. Synchronizing the energy deposition to match the movement of the material woven by the loom. Synchronizing the energy deposition with the movement of a ground vehicle and its temporary lifting force and propulsion force, and the energy used to achieve these forces, to reduce the resistance of the ground vehicle. Depositing energy on the barrels of several types of barrels used for propelling a projectile, especially on the barrels of guns, small firearms, or breachers, to push air out of the barrel. Reducing the resistance of the projectile enables a higher muzzle velocity with the same amount of driving energy (e.g., the propellant of a conventional gun or the electric driving energy of a railgun). Reducing the resistance also enables achieving a speed comparable to the speed achieved without change by using less driving energy (e.g., less propellant, e.g., less than 90% of the propellant compared to the standard propellant of a specific device, e.g., between 50% and 90%, less than 70%, or less than 80%). In a conventional gun, this means that the same performance can be achieved with less propellant. Therefore, the reduced required amount of propellant reduces the shock wave when the projectile exits the barrel. Reducing this acoustical property is useful for minimizing the adverse effects on the hearing of nearby people, including the operator(s). Reducing this acoustical property can also mitigate detection by acoustic means (similar to a silencer). The energy deposition for pushing air out of the barrel can be applied in various forms. (s). It is possible. For example, two embodiments are: (i) the deposition of electromagnetic energy inside the barrel; or ( ii) the deposition of energy can be of a chemical nature; and may include certain combinations of these two energy deposition approaches. The electromagnetic energy can be in the form of, for example, a discharge inside the barrel. The chemical energy can be in the form of, for example, an additional propellant that expands in front of the projectile upon ignition (as opposed to the role of a conventional propellant that expands behind the projectile and pushes the projectile out of the barrel) and pushes the gas out of the barrel. This additional propellant can be included within the projectile itself. In the application of powder coating, such as supersonic spray deposition, the energy deposition is coordinated with: a burst of powder; the application of heat; the application of a discharge; the application of laser energy; the application of plasma. In supersonic and hypersonic propulsion, the energy deposition is coordinated with the detonation within the engine (e.g., a pulse detonation engine), thereby properly coordinating the hydrodynamic process (this timing is determined by the length scale of the moving body and the propulsion unit(s), and among other factors, in particular, the flight conditions and parameters). The propulsion pulses can also be synchronized to generate laser pulses and supply power to the pulse power supply. BACKGROUND OF THE INVENTION

[0005] (Background of the Invention) Since its inception, PM & AM Research has, in particular, explored a wide range of applications of energy deposition to revolutionize how things fly and control high-speed flows, and how the inventors perform high-speed flight and flow control from the high subsonic region to the hypersonic region. This new approach provides an intuitive sense of the many possibilities opened up. There are several application examples. The basic effect results from the inventors' approach for rapidly expanding gas from the area where the inventors want to flow high-speed / high-pressure gas. (Requiring a certain degree of imagination and freedom) As a simple example, when launching a projectile directly in water and moving it from one side to the other side, or first "separating" the Red Sea and then launching the same bullet to move it through a path without water and considering the difference in effectiveness when trying to cross the Red Sea at high speed with the projectile. (Figure 1) In the first case of directly launching a bullet into high-density water, even a huge streamlined bullet at 1000 m / s

[0006] will only pass through less than 1 m in water. In the second case, after first "separating" the water (i.e., removing the water and forming a path), even the same bullet at 300 m / s can easily move a very long distance. (This discovery example does not address dealing with gravity, which will be addressed later in this specification.) It is this concept and geometry that the inventors utilize to achieve innovative control for high-speed flows and high-speed moving bodies / projectiles. SUMMARY OF THE INVENTION MEANS FOR SOLVING THE PROBLEM

[0007] (Summary of the Invention) Certain embodiments can provide, for example, a method of propelling an object through a fluid, the method comprising: (i) instantaneously heating a portion of the fluid to form a lower-density region surrounded by a higher-density region, wherein the higher-density region includes at least a portion of the heated portion of the fluid; (ii) positioning at least a portion of the object in the lower-density density region. The step of inducing into the region; synchronously (iii) a pulse propulsion unit that propels the object including the step of detonating the reactant. In certain embodiments, for example, steps (i) - (iii) are repeated, for example, at a rate of 0.1 Hz to 100 kHz, for example, 1 Hz to 80 kHz, 10 H z to 50 kHz, 100 Hz to 20 kHz, 1 to 10 kHz, 5 to 10 kHz, 10 to 25 kHz, 25 to 50 kHz rate of repetition, or can be repeated at a rate of 50 to 100 kHz.

[0008] In certain embodiments, one or more (e.g., all) of the following embodiments may include each of the other embodiments or portions thereof. In certain embodiments, for example, the reactant may be present in a higher density region. In certain embodiments, for example, the heating step may include depositing 1 kJ to 10 MJ of energy, for example, 10 kJ to 1 MJ, 100 to 750 kJ, or 200 kJ to 500 kJ into the fluid. In certain embodiments, for example, the heating step may include depositing 10 to 1000 kJ per square meter of cross-sectional area of the object, for example, 10 to 50 kJ per square meter, 50 to 100 kJ, 100 to 250 kJ, 250 to 500 kJ, or 500 to 1000 kJ of energy into the fluid . In certain embodiments, for example, the heating step may include generating a shock wave . In certain embodiments, for example, the lower density region may have a density of 0.01 to 10% of the density of the ambient fluid, for example, 0.5 to 5%, 1.0 to 2 .5% of the density of the ambient fluid, or a density of 1.2 to 1.7%. In certain embodiments, for example, one of the fluids ​The part can be heated along at least one path. In certain embodiments, this at least one path can be formed by energy deposited from a laser, such as a laser filament induced path. In certain embodiments, this laser deposition can include laser pulses that last for a time of 1 femtosecond to 100 nanoseconds, such as 10 femtoseconds to 20 picoseconds, 100 femtoseconds to 25 picoseconds, 100 picoseconds to 20 nanoseconds, or 100 femtoseconds to 30 picoseconds. In certain embodiments, the amount of energy deposited by the laser pulse can be 0.2 mJ to 1 kJ, such as 1 mJ to 10 mJ, 10 mJ to 3 J, 1 00 mJ to 10 J, 10 J to 100 J, 100 J to 1000 J, or 500 mJ to 5 J. In certain embodiments, this laser can generate light in the ultraviolet, infrared, or visible part of the spectrum. In certain embodiments, at least one path can be parallel to the direction of motion of the object. In certain embodiments, the lower density region can include a certain amount of the heated fluid portion that expands outward from at least one path. In certain embodiments, for example, the heated portion of the fluid can be heated by an electric discharge, such as a pulsed electric discharge. In certain embodiments, the electric discharge 6 can move through the fluid at a speed of 10 7 to 10 m / sec. In certain embodiments, the electric discharge can last for a time of 0.1 to 100 microseconds, such as 0.1 to 2 microseconds, 1 to 5 microseconds, 5 to 4 0 microseconds, 10 to 30 microseconds, or 30 to 100 microseconds. In certain nanoseconds, 20 to 200 microseconds, 30 to 100 microseconds, 100 to 500 microseconds, 400 to 1500 micro seconds, or can be formed within a time of 500 to 3000 microseconds. In certain embodiments, the lower density region can be destroyed by thermal buoyancy after a time of 10 to 1000 milliseconds, for example, 20 to 80 milliseconds, 30 to 60 milliseconds, 80 to 120 milliseconds, 150 to 600 milliseconds, or 400 to 1000 milliseconds. In certain embodiments, for example, the object can be in communication with a pulse detonation engine, which can contain the reactants. In certain embodiments, the detonation can be time adjusted such that the intake nozzle of the pulse detonation engine is present in the higher density region. In certain embodiments, the fluid can be air and the pulse detonation engine can be an air breathing pulse detonation engine. Certain embodiments can further include, for example, a step of introducing a quantity of air into the air breathing pulse detonation engine prior to step (ii). In certain embodiments, the pulse detonation engine can provide at least a portion of the power necessary to heat a portion of the fluid. In certain embodiments, the pulse detonation engine can supply energy to a pulsed power source. In certain embodiments, the pulsed power source can supply energy to a filamenting laser, which forms the path that can induce a pulsed discharge. In certain embodiments, the pulsed power source can supply energy to a pulsed discharge generator, which is used to heat a portion of the fluid. In certain embodiments, for example, further portions of the fluid may be heated to form a region of even lower density. It may further include steps. In certain embodiments, the region of lower density and the region of even lower density can be separated by a certain region. Certain embodiments may further include steps of guiding at least a further portion of the object into the region. Certain embodiments may further include steps of guiding at least a further portion of the object into the region of even lower density. For example, in certain embodiments, the heated portion of the fluid can define a tube. In certain embodiments, the speed of sound within the tube can be at least 100% higher than the speed of sound in the surrounding fluid, for example, at least 150%, 200%, 500%, or at least 1000% higher. In certain embodiments, the movement of the object within the tube can be subsonic. In certain embodiments, at least a portion of the movement of the object outside the tube can be supersonic. In certain embodiments, the tube can have a diameter that is 5% to 100% of the effective cross-sectional diameter of the object, for example, 5% to 20%, 20% to 75%, 30% to 50%, 75% to 96%, or 35% to 45%. In certain embodiments, for example, the object can have a bottom diameter of 0.5 to 4 m, for example, 1 to 3 m, or 1 to 2 m. In certain embodiments, the object can move through the fluid at a speed of Mach 6 to 20, for example, Mach 6 to 15, Mach 6 to 10, Mach 6 to 8, or Mach 7 to 8. In certain embodiments, the heating step can include depositing 100 to 750 kJ of energy into the fluid; the object can be characterized by a bottom diameter of 0.5 to 4 m. In certain embodiments, the movement of the object can be hypersonic. In certain embodiments, the object can move through the fluid at a speed of Mach 6 to 20, for example, It can move at speeds of Mach 6 to 15, Mach 6 to 10, Mach 6 to 8, or Mach 7 to 8. In certain embodiments, the heating step deposits 1 00 - 200 kJ, such as 125 - 175, or 140 - 160 kJ of energy per square meter of cross-sectional area of the object into the fluid. In certain embodiments, the tube has a cross-sectional area of 1 - 25% of the cross-sectional area of the object, such as 2 - 15%, 3 - 10%, or 3.5 - 4.5% when the object is at an altitude of 10 - 20 km, such as 12. 5 - 17.5 km, 14 - 16 km, or 14.5 - 15.5 km. In certain embodiments, the tube has a cross-sectional area of 6.25 - 56.25% of the cross-sectional area of the object, such as 10 - 40%, 20 - 30%, or 24 - 26% when the object is at an altitude of 20 - 40 km, such as 25 - 35 km, 28 - 32 km , or 29.5 - 30.5 km. In certain embodiments, the tube has a cross-sectional area of 25 - 225% of the cross-sectional area of the object, such as 50 - 200%, 75 - 150%, or 95 - 105% when the object is at an altitude of 40 - 60 km, such as 40 - 50 km, 42 - 48 km, or 44 - 46 km . In certain embodiments, the resistance experienced by the object can be reduced by at least 96% in step (ii). In certain embodiments, for example, the object may contact a guide rail. In certain embodiments, for example, the object can be in a room, a tube, or a barrel.

[0009] Certain embodiments can provide, for example, a moving body, which: (i) has a filament laser configured to form a path in a portion of the fluid surrounding the moving body ;(ii) configured to deposit energy along the path to form a low-density region Directed energy deposition device; and (iii) includes a pulse detonation engine. In certain embodiments, one or more (e.g., all) of the following embodiments may include each of the other embodiments or portions thereof. In certain embodiments, for example, the filament ray zer may include a pulsed laser. In certain embodiments, for example, the directed energy deposition device may include a pulse discharge generator. Certain embodiments are, for example, (iv) a sensor configured to detect whether a predetermined portion of a moving body is present within the low-density region; and ( v) a synchronization control device functionally connected to the directed energy deposition device and the pulse detonation engine, the synchronization control device being configured to synchronize (a) the formation of the path; and (b) the deposition of energy along the path; and (c) the relative timing of the operation of the pulse detonation engine, and may further include the synchronization control device.

[0010] Certain embodiments can provide, for example, a method of improving a pulse-propelled moving body with a directed energy deposition subassembly. This subassembly can operate to achieve and / or include one or more of the embodiments herein.

[0011] Certain embodiments can provide, for example, a method of operating a moving body, the method comprising: repeating the following steps (i)-(iv) at a rate of 0.1 to 100 times per second:( i) the step of firing a filament laser; synchronously (ii) the step of discharging a directed energy deposition device; synchronously (iii) inducing at least a portion of an object into a low-density region ​​​​​(iv) synchronizing the step of: (i) introducing a signal to the mobile unit when a predetermined portion of the mobile unit enters the low density region; The step of detonating the pulse detonation engine.

[0012] Certain embodiments may utilize a bottom resistance created by, for example, a low pressure area near the rear of the vehicle. A method for reducing drag can be provided, the method comprising: (i) providing at least one and instantaneously depositing energy along one path, thereby discharging a quantity of fluid to at least said and (ii) displacing a portion of the displaced amount of fluid into a low pressure region. The method includes the step of: directing the pressure in the low pressure region into the low pressure region, thereby increasing the pressure in the low pressure region. The invention relates to, for example, a moving body propelled by a pulse propulsion unit, and an energy deposition device. and synchronizing the discharge of the first and second electrodes with the generation of a propulsion pulse by the pulse propulsion unit. .

[0013] Certain embodiments may, for example, provide a fluid flow control for a cross section of a forward portion of a fuselage that includes multiple intake nozzles. A method for reducing wave drag exerted by a wave guide may be provided, the method comprising: (i) providing a wave guide for a wave guide; A portion of the fluid is instantaneously heated to a higher temperature that includes at least a small portion of the heated fluid portion. surrounded by a density region (e.g., aligned or substantially aligned with the longitudinal central axis of the fuselage) (ii) forming a lower density region (i.e., a region of lower density that is aligned with the lower density region); (iii) directing a first portion of the fuselage that is not yet heated into the lower density region; and ) directing a second portion of the fuselage, the second portion including at least one of the intake nozzles, into the higher density region. The method includes the step of:

[0014] Certain embodiments provide, for example, a method for forming a low density region in a fluid adjacent to an object. is capable, and the system comprises: (i) a directional energy using a dispersing device, a plurality of pulses emerging from the object and intersecting at one or more coordinates in the fluid forming a laser beam, wherein the one or more coordinates are located with respect to the object in said step; and (ii) depositing energy along one or more paths defined by the plurality of laser beams. In certain embodiments, one or more of the following embodiments (e.g., all) may include each of the other embodiments or portions thereof In certain embodiments, for example, the step of depositing energy may include depositing a predetermined amount of energy per unit length of one or more paths. In certain embodiments for example, the low density region may have a characteristic diameter along one or more paths, and the characteristic diameter may be proportional to the square root of the amount of energy deposited per unit length of the one or more paths In certain embodiments, for example, the diameter of the tube may be the characteristic diameter. In certain embodiments for example, the characteristic diameter may be further proportional to the inverse square root of the ambient pressure of the fluid. In certain embodiments the diameter of the tube may be the characteristic diameter. In certain embodiments, for example, at least two of the plurality of pulsed laser beams can be generated by splitting a source laser beam generated by a laser subassembly of the object. In certain embodiments for example, a portion of the fluid can be compressed between the low density region and the object. In certain embodiments for example, at least a portion of the deposited energy can be by at least one electrode In certain embodiments, for example, at least a portion of the deposited energy can be by at least one electrode In certain embodiments, for example, at least two of the plurality of pulsed laser beams can be generated by splitting a source laser beam generated by a laser subassembly of the object. In certain embodiments er beam). In certain embodiments, for example a portion of the fluid can be compressed between the low density region and the object. In certain embodiments for example, at least a portion of the deposited energy can be by at least one electrode It can be delivered, and at least a part of the deposited energy is recovered by at least one other electrode. In certain embodiments, for example, a sub-assembly of an object may include at least one electrode. In certain embodiments, for example, a sub-assembly of an object may include at least one other electrode. In certain embodiments, for example, this at least one electrode and / or this at least one other electrode can be disposed in a recessed cavity on the surface of the object.

[0015] Certain embodiments can provide, for example, a method of forming a low-density region in a fluid proximate to an object, the system comprising: (i) directing a laser beam along a line of sight starting at coordinates incident on the object and ending at coordinates exiting the object; and (ii) depositing energy along a path defined by the laser beam.

[0016] Certain embodiments can provide, for example, a method of forming a low-density region in a fluid comprising: (i) forming a transmission path configured to induce deposition of energy; and (ii) depositing energy along the transmission path to form the low-density region.

[0017] In certain embodiments, for example, one or more (e.g., all) of the following embodiments may be included in each of other embodiments or portions thereof. In certain embodiments, for example, the transmission path can pass through a fluid, e.g., air, and / or along the surface of a solid object, e.g., a moving body (e.g., an aircraft, missile, train, torpedo, and other high-speed This is the case. In certain embodiments, for example, this method is performed at a rate of 0.1 Hz to 100 kHz for steps (i ) to (ii), for example, repeating steps (i) to (ii) at a rate of 1 Hz to 80 kHz, 10 Hz to 50 kHz, 100 Hz to 20 kHz, 1 to 10 kHz, 5 to 10 kHz, or may further include repeating steps (i) to (ii) at a rate of 10 to 30 kHz . In certain embodiments , for example, the step of forming the transmission path may include one or more energy sources, for example, one energy source, two energy sources, three energy sources, or four energy sources emitting . In certain embodiments, for example, the one or more emitted energy sources may include electromagnetic radiation, such as X-rays, ultraviolet rays, visible light, infrared rays, microwaves, and / or radio waves; RF plasma discharge; current; electron beam; particle beam; charged particle beam; discharge; and / or corona discharge . In certain further embodiments, for example, the electromagnetic radiation may be at least one laser beam. In certain further embodiments, for example, the first energy source, the second energy source, and / or the third energy source may include at least one directional energy beam. In certain further embodiments, for example, the electromagnetic radiation may include at least one laser beam. In certain further embodiments, for example, the one or more energy sources may include at least one directional energy beam. In certain embodiments, , for example, the step of forming the transmission path includes emitting a laser beam and an electron beam . In certain further embodiments, for example, the laser beam and the electron beam can be emitted simultaneously. In certain further embodiments, for example, the laser beam and the electron beam can be emitted continuously. In certain embodiments, for example, the step of emitting one or more energy sources to form a transmission path includes emitting one or more pulses, a series of pulses, a series of ultrashort pulses, sporadic pulses, random pulses, emissions close to continuous emission, continuous emission of energy and / or any combination of some or all of these types of emissions. In certain embodiments, the step of emitting one or more energy sources to form a transmission path may include at least one pulse, for example, a plurality of pulses, having a duration of from 1 attosecond to 1 femtosecond, such as from 100 attoseconds to 1 femtosecond. In certain embodiments, the step of emitting one or more energy sources to form a transmission path may include at least one pulse, for example, a plurality of pulses, having a duration of from 1 femtosecond to 100 nanoseconds, such as from 10 femtoseconds to 20 picoseconds, from 100 femtoseconds to 25 picoseconds, from 100 picoseconds to 20 nanoseconds, or from 100 femtoseconds to 30 picoseconds. In certain embodiments, the step of emitting one or more energy sources to form a transmission path may include at least one pulse, for example, a plurality of pulses, having a duration of from 100 nanoseconds to 1 microsecond, such as from 500 nanoseconds to 1 microsecond. In certain embodiments, the step of emitting one or more energy sources to form a transmission path may include at least one pulse, for example, a plurality of pulses, having a duration of from 1 microsecond to 10 seconds, such as from 10 microseconds to 1 second, or from 100 microseconds to 500 microseconds. In certain embodiments, the step of emitting one or more energy sources to form a transmission path At least one pulse, for example, a plurality of pulses, which may include, may have a duration of from 0 to 40 seconds. Specific In an embodiment, for example, the step of forming a transmission path is: (a) passing through a first energy source to destroy a characteristic of the fluid (e.g., a region of higher density and / or pressure, e.g., a wave or a wavefront ); (b) introducing a second energy source into the destroyed fluid (e.g., by a wave or a wavefront generated by the first energy source or by the destruction by the wave or the wavefront); and then (c) introducing a third energy source into the fluid, which may be included. In a specific embodiment, for example, the step of forming a transmission path is: (a) emitting a first energy source to destroy a standing wave of the fluid proximate to the moving body; (b) passing a second energy source through the destroyed portion of the fluid; and then (c) introducing a third energy source into the fluid to form a transmission path, which may be included. In a specific embodiment, for example, the first energy source may include a laser beam; the second energy source may include an electron beam; and the third energy source may include a laser beam. In a specific embodiment, for example, the characteristics of the destroyed fluid may be waves, such as standing waves or dynamic waves, such as waves adjacent to an object, such as waves generated by the movement of a moving body. In a specific embodiment, for example, the step of forming a transmission path is: (a) introducing a first energy source into the fluid; and then (b) introducing a second energy source into the fluid, which may be included. In a further specific embodiment, for example, the first energy source may be a laser beam or an electron beam, and the second energy source may be a microwave beam. In a specific embodiment, for example, the step of forming a transmission path is: (a) introducing a first energy source into the fluid; and then (b) introducing a second energy source into the fluid, which may be included. In a further specific embodiment, for example, the first energy source may be a laser beam or an electron beam, and the second energy source may be a microwave beam. In a further specific embodiment, for example, the first energy source may be a laser beam or an electron beam, and the second energy source may be a microwave beam. This is the case. In certain embodiments, for example, the step of forming the transmission path may include forming conductive particles and / or ionic particles. In certain embodiments, for example, the energy deposited may include one or more energy sources, for example, one energy source, two energy sources, three energy sources, or four energy sources. In certain embodiments, for example, the energy deposited may be electromagnetic radiation, such as X-rays, ultraviolet light, visible light, infrared light, micro waves, and radio waves; RF plasma discharge; current; electron beam; particle beam; charged particle beam; discharge electricity; corona discharge, and / or one or more forms of energy including combinations thereof may be included. In certain further embodiments, for example, the electromagnetic radiation may include at least one laser beam. In certain further embodiments, for example, the first energy source, the second energy source, and / or the third energy source may include at least one directed energy beam. In certain further embodiments, for example, the electromagnetic radiation may include at least one laser beam. In certain further embodiments, for example, one or more energy sources may include at least one directed energy beam. In certain embodiments, for example, the energy deposited may include at least one form of energy different from one or more energy sources used to form the transmission path. In certain embodiments, for example, the energy deposited may include at least one form of energy common with one or more energy sources used to form the transmission path. In certain embodiments, for example, the energy deposited may be deposited as one or more pulses, a series of pulses, a series of ultrashort pulses, sporadic pulses random pulses, deposition close to continuous deposition, or continuous deposition of energy. It can be. In certain embodiments, the energy deposition is from 1 attosecond to 1 femtosecond, for example , at least one pulse having a duration of from 100 attoseconds to 1 femtosecond, for example, a plurality of pulses may be included. In certain embodiments, the energy deposition is for a time duration of from 1 femtosecond to 100 nanoseconds , for example, from 10 femtoseconds to 20 picoseconds, from 100 femtoseconds to 25 picoseconds, from 100 picoseconds to 20 nanoseconds, or at least one pulse having a duration of from 100 femtoseconds to 30 picoseconds, for example, a plurality of pulses may be included. In certain embodiments, the energy deposition is for a time duration of from 100 nanoseconds to 1 microsecond, for example, at least one pulse having a duration of from 500 nanoseconds to 1 microsecond may be included, for example, a plurality of pulses. In certain embodiments, the energy deposition is for a time duration of from 1 microsecond to 10 seconds, for example, from 10 microseconds to 1 second, or 100 microseconds to 500 microseconds, at least one pulse having a duration of, for example, a plurality of pulses may be included. In certain embodiments, the energy deposition is for a time duration of from 10 seconds to 1 minute, for example, 20 seconds to 40 seconds, at least one pulse having a duration of, for example, a plurality of pulses may be included. In particular embodiments, for example, the energy deposition and the emission of one or more energy sources for forming the transmission path can be performed on different time scales. In certain embodiments, , for example, the energy deposition and the emission of one or more energy sources for forming the transmission path can be performed on the same time scale or approximately the same time scale. In certain embodiments , for example, the energy deposition can be performed on a time scale faster than the emission of one or more energy sources for forming the transmission path . In certain embodiments, for example, the energy The deposition can be performed at a time scale slower than the emission of one or more energy sources for forming the transmission path.

[0018] Certain embodiments can provide, for example, a method for propelling a moving body (e.g., a transport vehicle, a transporter, a cargo carrier, a supersonic vehicle, a hypersonic vehicle, or a high-altitude vehicle) in the atmosphere, the method comprising: (i) heating a portion of the atmosphere in front of and / or beside the moving body to form a low-density region, the step comprising: (a) forming a starting region in front of the moving body that is configured to couple to and absorb the energy deposition; and (b) depositing energy in the starting region to form the low-density region; (ii) inducing at least a portion of an object into the low-density region; and synchronously (iii) detonating reactants in a pulse propulsion unit that propels the moving body.

[0019] In certain embodiments, for example, one or more (e.g., all) of the following embodiments may be included in each of other embodiments or portions thereof. In certain embodiments, for example, the starting region may be in contact with the moving body. In certain embodiments, for example, the starting region may not be in contact with the moving body, and for example, the starting region may be disposed in front of the direction of movement of the moving body. In certain embodiments, for example, the starting region may be formed up to 4 seconds before the moving body to be propelled, for example, up to 3 seconds before, 1 second before, 500 milliseconds before, 10 milliseconds before, or 1 millisecond before the moving body. In certain embodiments, for example, the starting region may be formed from 1 millisecond to 4 seconds before the moving body to be propelled, for example, from 10 milliseconds to 3 seconds before, or from 50 milliseconds to 1 second before. ​​​​​​​​​​​​​​​It can be formed at or before 100 milliseconds to 500 milliseconds before the propelled moving object. Specific In an embodiment, for example, the heated portion of the atmosphere can be formed up to 4 seconds before the propelled moving object, for example, up to 3 seconds before, 1 second before, 500 milliseconds before, 10 milliseconds before, or 1 millisecond before the moving object. In a specific embodiment, for example, the heated portion of the atmosphere can be formed from 1 millisecond to 4 seconds before the propelled moving object, for example, from 10 milliseconds to 3 seconds, from 50 milliseconds to 1 second, or it can be formed 100 milliseconds to 500 milliseconds before the propelled moving object. In a specific embodiment For example, forming the starting region may include forming conductive particles and / or ion particles. In a specific embodiment, for example, the method: according to the altitude of the moving object, It may further include the step of selecting at least one form of energy for radiation to form the starting region. In a specific further embodiment, for example, at least One form of energy selected for radiation may include a laser beam when the moving object moves below a predetermined threshold altitude. In a specific further embodiment, for example, at least One form of energy selected for radiation may include an electron beam when the moving object moves at or above a predetermined threshold altitude. In a specific embodiment, for example, the method: low density It may further include the step of selecting at least one form of energy to deposit on the starting region to form the region. In a specific further embodiment, for example, at least One form of energy selected for deposition may include a discharge when the moving object moves at a speed lower than a predetermined threshold speed. In a specific further embodiment, for example, at least One form of energy selected for deposition It may include an electron beam when the moving object moves at or above a predetermined threshold altitude. In a specific embodiment, for example, the method: low density It may further include the step of selecting at least one form of energy to deposit on the starting region to form the region. In a specific further embodiment, for example, at least One form of energy selected for deposition may include a discharge when the moving object moves at a speed lower than a predetermined threshold speed. In a specific further embodiment, for example, at least One form of energy selected for deposition may include a discharge when the moving object moves at a speed lower than a predetermined threshold speed. In a specific further embodiment, for example, at least One form of energy selected for deposition may include a discharge when the moving object moves at a speed lower than a predetermined threshold speed. In a specific further embodiment, for example, at least At least one form of energy may include microwave energy if the moving body moves at a predetermined threshold speed or faster. In certain embodiments, for example, this method may further include repeating steps (i)-(iii) at a rate of 0.1 Hz to 100 kHz, for example , at a rate of 1 Hz to 80 kHz, 10 Hz to 50 kHz, 100 Hz to 20 kHz, 1 to 10 kHz, 5 to 10 kHz, repeating steps (i)-(ii), or repeating steps (i)-(iii) at a rate of 10 to 30 kHz. In certain embodiments, for example, the step of forming the starting region may include emitting one or more energy sources, for example, one energy source, two energy sources, three energy sources, or four energy sources. In certain embodiments , for example, the one or more emitted energy sources may be selected from the group consisting of electromagnetic radiation, such as X-rays, ultraviolet rays, visible light, infrared rays, microwaves, and radio waves; RF plasma discharge; current; electron beam; particle beam; charged particle beam; discharge; and corona discharge. In certain further embodiments, for example, the electromagnetic radiation may be at least one laser beam . In certain further embodiments, for example, the first energy source, the second energy source, and / or the third energy source may include at least one directed energy beam . In certain further embodiments, for example, the electromagnetic radiation may include at least one laser beam . In certain further embodiments, for example, the one or more energy sources may include at least one directed energy beam. In certain embodiments, for example, the step of forming the starting region includes emitting a laser beam and an electron beam. In certain further embodiments, for example, the electromagnetic radiation may be at least one laser beam . In certain further embodiments, for example, the one or more energy sources may include at least one directed energy beam. In certain embodiments, for example, the step of forming the starting region may include emitting a laser beam and an electron beam. In certain further embodiments, for example, the electromagnetic radiation may include at least one laser beam . In certain further embodiments, for example, the one or more energy sources may include at least one directed energy beam. In certain embodiments, for example, the step of forming the starting region may include emitting a laser beam and an electron beam. In certain further embodiments, for example, the electromagnetic radiation may include at least one laser beam In certain embodiments, for example, a laser beam and an electron beam can be emitted simultaneously. In certain further embodiments, for example, a laser beam and an electron beam can be emitted continuously. In certain embodiments, for example, the step of emitting one or more energy sources to form an initiation region can include emitting one or more pulses, a series of pulses, a series of ultrashort pulses, sporadic pulses, random pulses, or emissions approaching continuous emission as a continuous emission of energy. In certain embodiments, the step of emitting one or more energy sources to form an initiation region can include at least one pulse, for example, a plurality of pulses, having a duration of from 1 attosecond to 1 femtosecond, such as from 100 attoseconds to 1 femtosecond. In certain embodiments, the step of emitting one or more energy sources to form an initiation region can include at least one pulse, for example, a plurality of pulses, having a duration of from 1 femtosecond to 100 nanoseconds, such as from 10 femtoseconds to 20 picoseconds, from 100 femtoseconds to 25 picoseconds, from 100 picoseconds to 20 nanoseconds, or from 100 femtoseconds to 30 picoseconds. In certain embodiments, the step of emitting one or more energy sources to form an initiation region can include at least one pulse, for example, a plurality of pulses, having a duration of from 100 nanoseconds to 1 microsecond, such as from 500 nanoseconds to 1 microsecond. In certain embodiments, the step of emitting one or more energy sources to form an initiation region can include at least one pulse, for example, a plurality of pulses, having a duration of from 1 microsecond to 10 seconds, such as from 10 microseconds to 1 second or from 100 microseconds to 500 microseconds. In certain embodiments, the step of emitting one or more energy sources to form an initiation region The step of forming lasts for a time of 10 seconds to 1 minute, for example, a time of 20 seconds to 40 seconds, and may include at least one pulse, for example, a plurality of pulses. In a particular embodiment, for example, the deposited energy may include one or more energy sources, for example, one energy source, two energy sources, three energy sources, or four energy sources. In a particular embodiment for example, the deposited energy may be: electromagnetic radiation, for example, X-rays, ultraviolet light, visible light, infrared rays, microwaves, and radio waves; RF plasma discharge; current; electron beam; particle beam; charged particle beam; discharge; and corona discharge, and may include one or more forms of energy selected from the group consisting of In a particular further embodiment, for example, the electromagnetic radiation may be at least one laser beam. In a particular further embodiment, for example, the first energy source, the second energy source, and / or the third energy source may include at least one directed energy beam In a particular further embodiment, for example, the electromagnetic radiation may include at least one laser beam. In a particular further embodiment, for example, one or more energy sources may include at least one directed energy beam. In a particular embodiment, for example, the deposited energy may include at least one form of energy different from one or more energy sources used to form the starting region In a particular embodiment, for example the deposited energy may include at least one form of energy common to one or more energy sources used to form the starting region In a particular embodiment, for example the deposited energy may be one or more pulses, a series of pulses, a series of ultrashort pulses, sporadic Depositing as a pulse, a random pulse, a deposition close to continuous deposition, or a continuous deposition of energy is possible. In certain embodiments, the energy deposition is from 1 attosecond to 1 femtosecond, for example, at least one pulse having a duration of from 100 attoseconds to 1 femtosecond, for example, a plurality of pulses. In certain embodiments, the energy deposition is from 1 femtosecond to 100 nanoseconds and has a duration of, for example, from 10 femtoseconds to 20 picoseconds, from 100 femtoseconds to 25 picoseconds, 100 pico seconds to 20 nanoseconds, or from 100 femtoseconds to 30 picoseconds, and may include at least one pulse, for example, a plurality of pulses. In certain embodiments, the energy deposition has a duration of from 100 nanoseconds to 1 microsecond, for example, from 500 nanoseconds to 1 microsecond and may include at least one pulse, for example, a plurality of pulses. In certain embodiments, the energy deposition has a duration of from 1 microsecond to 10 seconds, for example, from 10 microseconds to 1 second, or from 100 microseconds to 500 microseconds and may include at least one pulse, for example, a plurality of pulses. In certain embodiments, the energy deposition has a duration of from 10 seconds to 1 minute, for example from 20 seconds to 40 seconds and may include at least one pulse, for example, a plurality of pulses . In certain embodiments, for example, the energy deposition and the emission of one or more energy sources for forming the starting region can be performed on different time scales. In certain embodiments the energy deposition and the emission of one or more energy sources for forming the starting region can be performed on the same time scale or on a substantially the same time scale. In certain embodiments the energy deposition, for example, is from one or more energy sources for forming the starting region can be performed on a time scale faster than the emission. In certain embodiments, for example, energy deposition can be performed on a time scale slower than the emission of one or more energy sources for forming the initiation region.

[0020] In certain embodiments, for example, a particular laser assembly may be ineffective or less effective in forming a path of energy deposition in a fluid. For example, a laser assembly may be ineffective when the fluid is below a threshold pressure and / or density and / or when the moving body is operating at a threshold velocity and / or altitude. In certain further embodiments, if a particular laser configuration is not fully effective, for example, a single or another energy source, such as a particle beam in combination with a laser beam, such as an electron beam, can be used to form a path of energy deposition. In certain embodiments, an apparatus, such as a moving body, can include a sensor for detecting low effectiveness, and the apparatus can further include a control device configured to switch from using a laser configuration to using an electron beam ( or a combination of energy sources) to increase the effectiveness of path formation.

[0021] Certain embodiments can provide, for example, a method of propelling a ground vehicle (such as a train, a maglev train, a bullet train, and a hyperloop train) coupled to a track assembly, the method comprising: (i) accumulating a storage of electrical energy mounted on the ground vehicle; (ii) instantaneously discharging at least a portion of the electrical energy from the ground vehicle to a conductive portion of the track assembly, the portion being disposed in front of the body of the ground vehicle, ​As a result, a part of the air near the discharged electrical energy expands, forming a lower density region surrounded by a higher density region in this step; (iii) inducing at least a part of the object into the lower density region; and synchronously (iv) including the step of detonating the reactants of the pulse propulsion unit that propels the object. In certain embodiments, one or more (e.g., all) of the following embodiments may be included in each of the other embodiments or parts thereof. In certain embodiments, for example, the storage of electrical energy may be instantaneous from one or more booster subassemblies of the line assembly to the ground vehicle. In certain embodiments, for example, the ground vehicle can be magnetically levitated.

[0022] Certain embodiments can provide, for example, a ground vehicle transportation system (e.g., trains, maglev high-speed trains, bullet trains, and hyperloop trains), the system comprising: (i) (a ) a track; (b) a track assembly including a power supply; (ii) a storage device configured to receive and store a part of the power supply, such as a capacitor; (iii) a laser configured to form at least one path connecting one or more electrodes present on the body of the ground vehicle to a part of the track assembly, wherein a part of the track assembly is disposed at the front of the ground vehicle ; (iv) a directed energy deposition device configured to deposit a part of the stored power supply along the at least one path; and (v) a control device configured to synchronize the reception of a part of the power supply, the formation of the at least one path, and the deposition of a part of the stored power supply.

[0023] ​​​​​​​​Certain embodiments can provide, for example, a method of improving a ground vehicle (e.g., a train, a maglev train, a bullet train, a hyperloop train, a high-speed passenger vehicle, and an automobile) to reduce resistance, the method including the step of attaching a directional energy deposition subassembly that is configured to receive energy from the power supply of the ground vehicle and deposit the energy in a path connecting the body of the ground vehicle to the coordinates of the ground located at the front of the body. Certain embodiments can provide, for example, a method of improving a ground vehicle (e.g., a train, a maglev train, a bullet train, a hyperloop train, a high-speed passenger vehicle, and an automobile) to reduce resistance, the method including the step of attaching a directional energy deposition subassembly that is configured to receive energy from the power supply of the ground vehicle and deposit the energy in a path connecting the body of the ground vehicle to the coordinates of the ground located at the front of the body. Certain embodiments can provide, for example, a method of improving a ground vehicle (e.g., a train, a maglev train, a bullet train, a hyperloop train, a high-speed passenger vehicle, and an automobile) to reduce resistance, the method including the step of attaching a directional energy deposition subassembly that is configured to receive energy from the power supply of the ground vehicle and deposit the energy in a path connecting the body of the ground vehicle to the coordinates of the ground located at the front of the body. Certain embodiments can provide, for example, a method of improving a ground vehicle (e.g., a train, a maglev train, a bullet train, a hyperloop train, a high-speed passenger vehicle, and an automobile) to reduce resistance, the method including the step of attaching a directional energy deposition subassembly that is configured to receive energy from the power supply of the ground vehicle and deposit the energy in a path connecting the body of the ground vehicle to the coordinates of the ground located at the front of the body. Certain embodiments can provide, for example, a method of improving a ground vehicle (e.g., a train, a maglev train, a bullet train, a hyperloop train, a high-speed passenger vehicle, and an automobile) to reduce resistance, the method including the step of attaching a directional energy deposition subassembly that is configured to receive energy from the power supply of the ground vehicle and deposit the energy in a path connecting the body of the ground vehicle to the coordinates of the ground located at the front of the body. Certain embodiments can provide, for example, a method of improving a ground vehicle (e.g., a train, a maglev train, a bullet train, a hyperloop train, a high-speed passenger vehicle, and an automobile) to reduce resistance, the method including the step of attaching a directional energy deposition subassembly that is configured to receive energy from the power supply of the ground vehicle and deposit the energy in a path connecting the body of the ground vehicle to the coordinates of the ground located at the front of the body.

[0024] Certain embodiments can provide, for example, a method of propelling an object within a barrel (e.g., a barrel associated with a small firearm and a rail gun) containing a fluid, the method including: (i) heating at least a portion of the fluid; (ii) ejecting at least a portion of the fluid from the barrel to form a low-density region within the barrel; and subsequently (iii) igniting and / or detonating a reactant near the object. Certain embodiments can provide, for example, a method of propelling an object within a barrel (e.g., a barrel associated with a small firearm and a rail gun) containing a fluid, the method including: (i) heating at least a portion of the fluid; (ii) ejecting at least a portion of the fluid from the barrel to form a low-density region within the barrel; and subsequently (iii) igniting and / or detonating a reactant near the object. Certain embodiments can provide, for example, a method of propelling an object within a barrel (e.g., a barrel associated with a small firearm and a rail gun) containing a fluid, the method including: (i) heating at least a portion of the fluid; (ii) ejecting at least a portion of the fluid from the barrel to form a low-density region within the barrel; and subsequently (iii) igniting and / or detonating a reactant near the object. Certain embodiments can provide, for example, a method of propelling an object within a barrel (e.g., a barrel associated with a small firearm and a rail gun) containing a fluid, the method including: (i) heating at least a portion of the fluid; (ii) ejecting at least a portion of the fluid from the barrel to form a low-density region within the barrel; and subsequently (iii) igniting and / or detonating a reactant near the object. Certain embodiments can provide, for example, a method of propelling an object within a barrel (e.g., a barrel associated with a small firearm and a rail gun) containing a fluid, the method including: (i) heating at least a portion of the fluid; (ii) ejecting at least a portion of the fluid from the barrel to form a low-density region within the barrel; and subsequently (iii) igniting and / or detonating a reactant near the object.

[0025] In certain embodiments, one or more (e.g., all) of the following embodiments can include each of the other embodiments or portions thereof. In certain embodiments, for example, the reactant can be an explosive charge and / or a propellant (e.g., a chemical propellant). In certain embodiments, for example, the reactant can be attachable to the object. In certain embodiments, for example, the fluid can be air. In certain embodiments, for example, at least a portion of the fluid can be heated by an electric discharge, such as an electric arc between two electrodes (e.g., insulated electrodes) disposed within, along, or near the lumen of the barrel. In certain embodiments, for example, at least a portion of the fluid can be heated by ignition of a chemical reactant. In certain embodiments, one or more (e.g., all) of the following embodiments can include each of the other embodiments or portions thereof. In certain embodiments, for example, the reactant can be an explosive charge and / or a propellant (e.g., a chemical propellant). In certain embodiments, for example, the reactant can be attachable to the object. In certain embodiments, for example, the fluid can be air. In certain embodiments, for example, at least a portion of the fluid can be heated by an electric discharge, such as an electric arc between two electrodes (e.g., insulated electrodes) disposed within, along, or near the lumen of the barrel. In certain embodiments, for example, at least a portion of the fluid can be heated by ignition of a chemical reactant. In certain embodiments, one or more (e.g., all) of the following embodiments can include each of the other embodiments or portions thereof. In certain embodiments, for example, the reactant can be an explosive charge and / or a propellant (e.g., a chemical propellant). In certain embodiments, for example, the reactant can be attachable to the object. In certain embodiments, for example, the fluid can be air. In certain embodiments, for example, at least a portion of the fluid can be heated by an electric discharge, such as an electric arc between two electrodes (e.g., insulated electrodes) disposed within, along, or near the lumen of the barrel. In certain embodiments, for example, at least a portion of the fluid can be heated by ignition of a chemical reactant. In certain embodiments, one or more (e.g., all) of the following embodiments can include each of the other embodiments or portions thereof. In certain embodiments, for example, the reactant can be an explosive charge and / or a propellant (e.g., a chemical propellant). In certain embodiments, for example, the reactant can be attachable to the object. In certain embodiments, for example, the fluid can be air. In certain embodiments, for example, at least a portion of the fluid can be heated by an electric discharge, such as an electric arc between two electrodes (e.g., insulated electrodes) disposed within, along, or near the lumen of the barrel. In certain embodiments, for example, at least a portion of the fluid can be heated by ignition of a chemical reactant. In certain embodiments, one or more (e.g., all) of the following embodiments can include each of the other embodiments or portions thereof. In certain embodiments, for example, the reactant can be an explosive charge and / or a propellant (e.g., a chemical propellant). In certain embodiments, for example, the reactant can be attachable to the object. In certain embodiments, for example, the fluid can be air. In certain embodiments, for example, at least a portion of the fluid can be heated by an electric discharge, such as an electric arc between two electrodes (e.g., insulated electrodes) disposed within, along, or near the lumen of the barrel. In certain embodiments, for example, at least a portion of the fluid can be heated by ignition of a chemical reactant. In certain embodiments, one or more (e.g., all) of the following embodiments can include each of the other embodiments or portions thereof. In certain embodiments, for example, the reactant can be an explosive charge and / or a propellant (e.g., a chemical propellant). In certain embodiments, for example, the reactant can be attachable to the object. In certain embodiments, for example, the fluid can be air. In certain embodiments, for example, at least a portion of the fluid can be heated by an electric discharge, such as an electric arc between two electrodes (e.g., insulated electrodes) disposed within, along, or near the lumen of the barrel. In certain embodiments, for example, at least a portion of the fluid can be heated by ignition of a chemical reactant. In certain embodiments, one or more (e.g., all) of the following embodiments can include each of the other embodiments or portions thereof. In certain embodiments, for example, the reactant can be an explosive charge and / or a propellant (e.g., a chemical propellant). In certain embodiments, for example, the reactant can be attachable to the object. In certain embodiments, for example, the fluid can be air. In certain embodiments, for example, at least a portion of the fluid can be heated by an electric discharge, such as an electric arc between two electrodes (e.g., insulated electrodes) disposed within, along, or near the lumen of the barrel. In certain embodiments, for example, at least a portion of the fluid can be heated by ignition of a chemical reactant. In certain embodiments, one or more (e.g., all) of the following embodiments can include each of the other embodiments or portions thereof. In certain embodiments, for example, the reactant can be an explosive charge and / or a propellant (e.g., a chemical propellant). In certain embodiments, for example, the reactant can be attachable to the object. In certain embodiments, for example, the fluid can be air. In certain embodiments, for example, at least a portion of the fluid can be heated by an electric discharge, such as an electric arc between two electrodes (e.g., insulated electrodes) disposed within, along, or near the lumen of the barrel. In certain embodiments, for example, at least a portion of the fluid can be heated by ignition of a chemical reactant. In certain embodiments, the chemical reactant can be attached to or disposed on the object. In certain embodiments, the chemical reactant can be ignited by an electrical pulse. In certain embodiments, the electrical pulse can be supplied by the object. In certain embodiments, the electrical pulse can be supplied by a piezoelectric generator. In certain embodiments, for example, the fluid can be a gas. In certain embodiments, for example, the fluid can be air. In certain embodiments, the fluid can be a liquid. In certain embodiments, the fluid can be compressible. In certain embodiments, the fluid can be incompressible. In certain embodiments, the heating portion of the fluid can be heated to change its phase. In certain embodiments, for example, a portion of the fluid can be heated by the ignition and explosion of the chemical reactant, for example, by an electrical pulse. In certain embodiments, the electrical pulse can be supplied by the object, for example, by a mechanism that is partially or completely included within the object. In certain embodiments, the electrical pulse can be supplied by a piezoelectric generator, for example, a piezoelectric generator that is partially or completely included within the object. In certain embodiments, for example, the object can be a projectile, for example, a bullet. In certain embodiments, for example, the barrel can be a component of a small firearm or a component of a rail gun. In certain embodiments, for example, the heating can reduce the viscosity of the heating portion of the fluid. In certain embodiments, for example, at least a portion of the fluid can be heated by a discharge having an energy of 5 - 120 J, for example, 10 - 100 J, 10 - Well, this method may further include the step of launching an object from the barrel. In certain embodiments the object can be a projectile. In certain embodiments, the barrel can be a component, for example, a component of a railgun In certain embodiments, for example, the magnitude of the generated acoustic characteristics is at least 10% less than the magnitude of the acoustic characteristics of a conventional 30-06 rifle, a conventional 300 magnum rifle, a jet engine at takeoff, and / or an M2 howitzer, for example, 10% to 50% less, at least 25%, 50%, or at least 75% less. In certain embodiments, for example, the magnitude of the generated acoustic characteristics is less than 300 dB, for example, 50 dB to 150 dB, less than 250 dB, less than 200 dB, less than 175 dB, less than 150 dB, or less than 125 dB can be.

[0026] Certain embodiments can provide, for example, a method of delivering a projectile, the method comprising: (i) the barrel including a breech that enables functional accommodation of the projectile within the lumen of the barrel; (ii) a barrel scavenging system configured to discharge a portion of the fluid present within the lumen and including a pulse heating system disposed within and / or in proximity to the lumen of the barrel; and (iii) a projectile launch system. In certain embodiments, one or more (e.g., all) of the following embodiments can include each of the other

[0027] embodiments or portions thereof. In certain embodiments, for example, the pulse heating system can be disposed in proximity to the breech. In certain embodiments, for example, the pulse heating system can further include a chemical propellant. In certain embodiments, the chemical propellant can include, for example, the pulse heating system can be disposed in proximity to the breech. In certain embodiments, for example, the pulse heating system can further include a chemical propellant. In certain embodiments, the chemical propellant can include, for example, It can be integrated with the projectile and / or the cartridge containing the projectile. In certain embodiments For example, the pulse heating system may further include a pulse discharge generator configured to deposit energy along at least one path within the lumen. In certain embodiments, the pulse heating system may further include a pulsed filament laser configured to form at least one path. In certain embodiments, the pulsed filament laser can be powered by a chemical propellant proximate to the projectile and / or incorporated into the cartridge containing the projectile. In certain embodiments, the pulsed filament laser can be integrated with the projectile and / or the cartridge containing the projectile. In certain embodiments, for example, the synchronous control device can be further included to control the relative timing between the operation of the barrel cleaning system and the operation of the projectile firing system. In certain embodiments, for example, a method for improving the projectile delivery system can be provided, the method including: mounting a directed energy deposition subassembly configured to deposit energy within the lumen of the barrel of the projectile delivery system. In certain embodiments, for example, a method for propelling a projectile within the lumen of a barrel equipped with a barrel cleaning system can be provided, the method including: (i) operating the barrel cleaning system to discharge a portion of the fluid from the lumen; and subsequently, after a few milliseconds, (ii) starting the projectile firing system.

[0028]

[0029]

[0030] ​​​​​​​​​​​​

[0031] Certain embodiments can provide a method for reducing the acoustic characteristics of a projectile, for example, by equipping a gun barrel with a

[0032] sweeping system. Certain embodiments can provide, for example, a gun (sometimes also referred to as a breaching gun) configured to break through a barrier, such as a door, the gun including: (i) a ported barrel including a breech capable of functionally accommodating a shotgun cartridge within the barrel lumen; (ii) a barrel sweeping system configured to discharge at least

[0033] a portion of the fluid present within the lumen and including a pulsed heating system disposed within the lumen; and (iii) a firing system. Certain embodiments can provide, for example, a small firearm cartridge configured for use in a breaching gun, the small firearm cartridge including: (i) a propellant proximate to the rear of the barrel and proximate to at least one projectile; (ii) a directional energy deposition device, such as a pre - propellant, disposed proximate to at least one projectile on the opposite side of the propellant and configured to discharge at least 98% of the initial gas under atmospheric conditions from the barrel of the gun upon ignition of the pre - propellant; and (iii) a firing system coupler configured to synchronize the operation of the directional energy deposition device prior to detonation of the propellant. In certain embodiments, one or more (e.g., all) of the following embodiments can be included in each of other embodiments or portions thereof. In certain embodiments, for example, the firing system coupler is a pre - propellant functionally connected to the firing system It may further include a pre-propellant priming charge.

[0034] Certain embodiments provide, for example, a method of modifying a shock wave approaching a substructure of a moving body (e.g., a military vehicle, both an armored vehicle, a heavy vehicle, an armored personnel vehicle, a passenger vehicle, a train, and / or a mine-clearing vehicle) that is in contact with a lower surface and present in a fluid, the method comprising: (i) heating a portion of the fluid along at least one path to generate at least one volume of heated fluid that expands outwardly from the path, wherein the path extends between the substructure and the lower surface; and (ii) adjusting the duration of the heating to modify the shock wave. The path extends between the substructure and the lower surface; and (ii) adjusting the duration of the heating to modify the shock wave. In certain embodiments, one or more (e.g., all) of the following embodiments may be included in each of the other embodiments or portions thereof. In certain embodiments, for example, the total momentum imparted to the moving body by the shock wave can be reduced by at least 10%, e.g., at least 20%, 30%,

[0035] 40%, or at least 50%. In certain embodiments, for example, the average acceleration experienced by the moving body as a result of the shock wave can be reduced by at least 40%, e.g., at least 50%, at least 60%, at least 70%, or at least 80%. In certain embodiments, for example, a portion of the fluid can be heated by an electrical discharge. In certain embodiments, for example, a portion of the fluid can be heated by depositing at least 3 PV units of energy, where P is the ambient pressure of the fluid and V is the volume of the fluid present between the substructure and the lower surface. In certain embodiments, for example, the total momentum imparted to the moving body by the shock wave can be reduced by at least 10%, e.g., at least 20%, 30%, 40%, or at least 50%. In certain embodiments, for example, the average acceleration experienced by the moving body as a result of the shock wave can be reduced by at least 40%, e.g., at least 50%, at least 60%, at least 70%, or at least 80%. In certain embodiments, for example, a portion of the fluid can be heated by an electrical discharge. In certain embodiments, for example, a portion of the fluid can be heated by depositing at least 3 PV units of energy, where P is the ambient pressure of the fluid and V is the volume of the fluid present between the substructure and the lower surface. In certain embodiments, for example, a portion of the fluid can be heated by depositing at least 3 PV units of energy, where P is the ambient pressure of the fluid and V is the volume of the fluid present between the substructure and the lower surface. This P is the ambient pressure of the fluid, and this V is the volume of the fluid present between the substructure and the lower surface. In certain embodiments, for example, a portion of the fluid can be heated by depositing at least 3 PV units of energy, where P is the ambient pressure of the fluid and V is the volume of the fluid present between the substructure and the lower surface.

[0036] Certain embodiments can provide a method for modifying a blast wave approaching a surface, for example. The method includes: (i) heating a portion of the surface to form at least one hole in the surface; and (ii) adjusting the duration of the heating such that the at least one hole is formed before the blast wave exits the surface.

[0037] In certain embodiments, one or more (e.g., all) of the following embodiments can be included in each of the other embodiments or portions thereof. In certain embodiments, for example, a portion of the surface can be heated by deposition of energy onto the surface. In certain embodiments, for example, the amount of energy deposited onto the surface can be from 1 kJ to 10 MJ, such as from 10 kJ to 1 MJ, from 100 to 750 kJ, or from 200 kJ to 500 kJ. In certain embodiments, for example, the surface can be a paving, soil, and / or a covering material present under the substructure of a moving body. In certain embodiments, a portion of the surface can be heated by depositing an amount of energy between 200 and 500 kJ per cubic meter of volume present between the substructure and the surface, such as between 250 and 400 kJ, or between 300 and 350 kJ. In certain embodiments, the blast wave can have an energy of 100 to 500 MJ, such as 200 to 400 MJ. In certain embodiments, the amount of energy deposited can reduce the energy transmitted from the blast wave to the moving body by at least 10 times, such as at least 20 times, 50 times, 100 times, or at least 200 times the amount of the energy deposited. In certain embodiments, as a result of the blast wave, the moving The net acceleration applied to the body can be reduced by at least 10%, for example, at least 20%, 30%, 40% , or at least 50%. In certain embodiments, a portion of the surface can be heated by the electrical radiation from the moving body.

[0038] Certain embodiments can provide, for example, a method for mitigating explosive gases proximate to the understructure of a moving body (e.g., a military vehicle, an armored vehicle, a Humvee, an armored personnel carrier, a passenger vehicle, a train, and / or a mine clearing vehicle) present in a fluid, the method comprising: (i) heating a portion of the fluid along at least one path to form at least one low density passageway, wherein the path extends from the understructure to the exterior of the moving body; and (ii) adjusting the duration of the heating such that the at least one low density

[0039] passageway receives at least a portion of the explosive gases. Certain embodiments can provide, for example, a moving body equipped with a blast mitigation device, the blast mitigation device comprising: (i) a sensor configured to detect an initial blast under the understructure of the moving body; (ii) a directed energy deposition device configured to deposit energy along at least one path located under the understructure of the moving body; and (iii) a timing control device configured to time the activation of the directed energy deposition device in response to the detection of the initial blast. In certain embodiments, configured to generate at least one volume of heated fluid that expands outwardly from the path In certain embodiments, for example, the energy deposition can be configured to form at least one hole in a surface located below the lower structure of the moving body.

[0040] Certain embodiments can provide, for example, a moving body equipped with a blast mitigation device (e.g., a military vehicle, an armored vehicle, a heavy vehicle, an armored personnel carrier, a passenger vehicle, a train, and / or a mine clearing vehicle), the blast mitigation device including: (i) a sensor configured to detect an initial blast below the lower structure of the moving body; (ii) a directed energy deposition device configured to deposit energy along at least one path extending from the lower structure of the moving body to the exterior of the moving body; and (iii) a synchronization control device configured to time the activation of the directed energy deposition device in response to the detection of the initial blast.

[0041] In certain embodiments, for example, a method of mitigating a blast from an improvised explosive device can be provided using a moving body equipped with a blast mitigation device (e.g., a military vehicle, an armored vehicle, a heavy vehicle, an armored personnel carrier, a passenger vehicle, a train, and / or a mine clearing vehicle). In certain embodiments, for example, the improvised explosive device may be buried.

[0042] Certain embodiments can provide, for example, a method of modifying a moving body to withstand an explosion, the method including the step of attaching a directed energy deposition subassembly configured to deposit energy below the lower structure of the moving body.

[0043] ​​​​​​​​​​​​​Certain embodiments may provide, for example, a method for supersonic deposition of a spray on a surface. The method includes: (i) directing at least one laser pulse through a fluid to the surface; forming at least one path through the fluid, the at least one path comprising: (ii) applying a certain amount of electrical energy to the surface; emitting the gas along the path to form a low density tube; followed by a few microseconds of and then (iii) ejecting the powder, particulate, and / or spray or aerosol material from the supersonic spray nozzle. In a particular embodiment, the method includes the steps of: discharging the material into the low density tube. One or more (e.g., including all) of the aspects may be used interchangeably with any other embodiment or portion thereof. In certain embodiments, for example, steps (i) to (iii) may be performed at a frequency of 0.1 Hz to 100 kHz. Repeat at a rate of 1 Hz to 80 kHz, 10 Hz to 50 kHz, 100 Hz to 20 kHz, 1 to 10 k Hz, repeat at a rate of 5-10 kHz, or repeat at a rate of 10-30 kHz.

[0044] Certain embodiments can provide, for example, a spray deposition apparatus, the spray deposition apparatus comprising: (i) a nozzle configured to spray particulates and / or spray material onto a surface; (ii) the nozzle a pulse filter configured to form at least one path between the filter and the surface; (iii) a filament laser that deposits energy along at least one path to produce a low-density (iv) a pulsed discharge generator configured to form a pulsed tube; and The relative timing of the formation of the path, the deposition of the energy, and the spraying is synchronized. In a particular embodiment, the synchronous control device includes one or more of the following embodiments: The above (e.g., all inclusive) may include each of the other embodiments or portions thereof. In embodiments, for example, the spray can be ultrasonic spray.

[0045] Certain embodiments may provide a method for physical vapor deposition using, for example, a spray deposition device. Certain embodiments can include, for example, depositing a metal powder onto a metal surface.

[0046] Certain embodiments provide methods of spray processing, for example using a spray deposition device. can be done.

[0047] Certain embodiments may provide, for example, a method for improving a supersonic nebulizer, The method includes the steps of: mounting a directed energy deposition subassembly; The nozzle is configured to deposit energy in a path connecting the nozzle of the spray device and a surface. It has been made.

[0048] Certain embodiments are suitable for use in, for example, intermittent weaving machines or looms (e.g., air jet weaving machines, rotor jet loom, shuttle loom, picks loom, and / or high speed loom The present invention provides a method for producing a woven fabric by operating an air jet weaving machine, the air jet weaving machine comprising: configured to receive a yarn and further configured to form a warp span. The method further comprises: depositing energy to generate a low density gas for the weft yarn to pass through the span. The method includes forming an id path.

[0049] In certain embodiments, one or more (e.g., including all) of the following embodiments may be combined with other In certain embodiments, for example, the energy The step of depositing the ion beam is performed at 5 to 50 mJ per 10 cm of guide path for a weft thread with a diameter of 1 mm, e.g. For example, 5-8 mJ, 8-10 mJ, 10-15 mJ, 15-20 mJ, 20-30 mJ, 30-40 mJ, or 40-50 mJ. or at least 8 mJ, at least 20 mJ, or at least 40 mJ. In certain embodiments, for example, the weft yarn has a diameter of 0.1 to 1 mm, for example, 0.25 to 0.75 mm. or a diameter of 0.5 to 0.7 mm, for example a diameter of 0.6 mm. For example, the weft yarn is wound at a speed of 100 to 500 m / s, for example, at a speed of 200 to 400 m / s, or at least A velocity of at least 200 m / s, for example at least 250 m / s, at least 300 m / s, or at least In certain embodiments, the vehicle can move through a guided path at a speed of up to 350 m / s. For example, the weft yarn may be wound at a speed exceeding Mach 0.1, for example, at a speed exceeding Mach 0.3, or at a speed exceeding Mach 0.8. Traveling through a guided path at a speed exceeding Mach 1, or exceeding Mach 1.5 In certain embodiments, for example, the fabric can be spun at a rate of 500 to 60,000 picks / min. For example, 2000-50,000 picks / min, 8,000-30,000 picks / min, or 15,000-25,000 picks / min. In certain embodiments, for example, the induction pathway may include: It may be a cylinder.

[0050] Certain embodiments may, for example, advance the weft yarn through a low density guided path with a jet of high pressure air. In certain embodiments, the high pressure air jet is synchronized with the energy deposition. It can be made to. In certain embodiments, the low-density induction path is downstream of a jet of high-pressure air. It can be formed.

[0051] In certain embodiments, one or more (e.g., all) of the following embodiments may each include another embodiment or a part thereof. In certain embodiments, for example, a further portion of the energy may be deposited downstream of the supply of the booster air to form a further low-density induction path. In certain embodiments, for example, the filling yarn can be wetted with a certain amount of water. In certain embodiments, for example, a further portion of the energy may be deposited downstream of the supply of the booster air to form a further low-density induction path. In certain embodiments, for example, the filling yarn can be wetted with a certain amount of water. In certain embodiments, at least a portion of the certain amount of water can be vaporized within the low-density induction path. It can be vaporized.

[0052] Certain embodiments can provide, for example, a weaving machine (e.g., an air-jet weaving machine, an intermittent air-jet weaving machine, a water-jet weaving machine, a shuttle loom, a pick loom, and / or a high-speed loom), and an air-jet weaving machine configured to manufacture a fabric, the weaving machine comprising: (i) a device comprising a plurality of profiled reeds attached to a sley configured to form a warp shed; (ii) a directional energy deposition assembly configured to form a low-density induction path across the warp shed; and (iii) a filling nozzle in communication with a supply of pressurized air and configured to advance a portion of the filling yarn within the low-density induction path. In certain embodiments, one or more (e.g., all) of the following embodiments may each include another embodiment or a part thereof. In certain embodiments, for example, the warp shed can have a length of 3 to 30 m, such as 4 to 4.5 m, 4.5 to 6 m, 6 to 8 m, 8 to 10 m, 5 to 25 m, or 10 to 20 m. a device comprising a plurality of profiled reeds attached to a sley configured to form a warp shed; (ii) a directional energy deposition assembly configured to form a low-density induction path across the warp shed; and (iii) a filling nozzle in communication with a supply of pressurized air and configured to advance a portion of the filling yarn within the low-density induction path. a device comprising a plurality of profiled reeds attached to a sley configured to form a warp shed; (ii) a directional energy deposition assembly configured to form a low-density induction path across the warp shed; and (iii) a filling nozzle in communication with a supply of pressurized air and configured to advance a portion of the filling yarn within the low-density induction path. a device comprising a plurality of profiled reeds attached to a sley configured to form a warp shed; (ii) a directional energy deposition assembly configured to form a low-density induction path across the warp shed; and (iii) a filling nozzle in communication with a supply of pressurized air and configured to advance a portion of the filling yarn within the low-density induction path. a device comprising a plurality of profiled reeds attached to a sley configured to form a warp shed; (ii) a directional energy deposition assembly configured to form a low-density induction path across the warp shed; and (iii) a filling nozzle in communication with a supply of pressurized air and configured to advance a portion of the filling yarn within the low-density induction path. a device comprising a plurality of profiled reeds attached to a sley configured to form a warp shed; (ii) a directional energy deposition assembly configured to form a low-density induction path across the warp shed; and (iii) a filling nozzle in communication with a supply of pressurized air and configured to advance a portion of the filling yarn within the low-density induction path. In certain embodiments, one or more (e.g., all) of the following embodiments may each include another embodiment or a part thereof. In certain embodiments, for example, the warp shed can have a length of 3 to 30 m, such as 4 to 4.5 m, 4.5 to 6 m, 6 to 8 m, 8 to 10 m, 5 to 25 m, or 10 to 20 m. It can be.

[0053] Certain embodiments can provide a method for improving a weaving machine (e.g., an air jet weaving machine, a water jet weaving machine, a shuttle loom, a pick loom, and / or a high-speed loom), the method including the step of attaching a directed energy deposition subassembly, the subassembly being configured to connect the yarn dispensing nozzle of the loom to an electrode disposed on the opposite side of the loom and to deposit energy along a path passing through a plurality of clamp profiles. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] (DETAILED DESCRIPTION OF THE DRAWINGS)

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[0098] Detailed Description of the Invention The basic concept underlying the inventors' energy deposition approach is that the inventors can redistribute the density of air by depositing energy rapidly (instantaneously) in air. / sculpt the shape of the air. To effectively "separate" the air, it is important to note that energy must be deposited in the air much faster than the gas can expand (e.g., in the form of short laser pulses or microwave pulses, and / or in the form of electrical discharges, among several techniques). Any heating that the gas may transmit when heated will not result in the very effective results described by the inventors herein, even if very high temperatures are used. Generally, "abrupt" / "instantaneous" heating processes generate a "pop" or "bang" sound. When the gas is heated, any heating that the gas may transmit will not result in the very effective results described by the inventors herein, even if very high temperatures are used. Generally, "abrupt" / "instantaneous" heating processes generate a "pop" or "bang" sound. generate a "pop" or "bang" sound.

[0099] (i) To adjust the intensity and spatial distribution of a particular mode of energy deposition; (ii) To maintain a particular path and passageway for proper transmission; and (iii) To couple energy into the flow; various energy deposition techniques are applied to address a wide variety of possible atmospheric and flow conditions in the broadest range of applications. To deposit additional energy To maintain a particular path and passageway for proper transmission; and (iii) To couple energy into the flow; various energy deposition techniques are applied to address a wide variety of possible atmospheric and flow conditions in the broadest range of applications. To deposit additional energy To couple energy into the flow; various energy deposition techniques are applied to address a wide variety of possible atmospheric and flow conditions in the broadest range of applications. To deposit additional energy in the most extensive range of applications to various possible atmospheric and flow conditions. To deposit additional energy To form a nucleation / induction / initiation region (e.g., an initial path); or to deposit additional energy into an initial region or path such as the most effective energy deposition approach depends on the atmospheric conditions (including all represented media and mixed phases, e.g., gas, liquid, solid, plasma) in which the region is to be formed, and the operating conditions of the associated flow. Certain atmospheric and flow conditions may require an initial path formed by energy deposition that can couple more energy as the following steps. Other atmospheric and flow conditions may require energy to be deposited in a single step. In certain applications, energy can be deposited along one or more surfaces, within one or more regions of the atmosphere / flow, and / or in certain combinations of these. One or more energy deposition steps may include, but are not limited to, the following energy deposition techniques: electromagnetic radiation (ranging from X-rays to microwaves); RF plasma discharge; and currents in the form of electron beams, charged particle beams, discharges, and corona discharges; and certain combinations of one or more of these; these energy deposition techniques can be for a transient period ranging from continuous beams to ultrashort pulses (e.g., attosecond pulses; femtosecond; picosecond; nanosecond; microsecond; millisecond; pulse widths of seconds; and longer pulse widths, up to continuous deposition). These time scales can vary for different embodiments and modes of energy deposition, and depositions in different modes are performed on their respective time scales. In addition to its use by itself, continuous or long-term energy deposition can also facilitate short pulse impact energy deposition in specific regions. Furthermore, applications involving pulsing / phasing / synchronization of specific processes using energy deposition can also include longer pulses and continuous processes. These time scales can vary for different embodiments and modes of energy deposition, and depositions in different modes are performed on their respective time scales. In addition to its use by itself, continuous or long-term energy deposition can also facilitate short pulse impact energy deposition in specific regions. Furthermore, applications involving pulsing / phasing / synchronization of specific processes using energy deposition can also include longer pulses and continuous processes. deposition can also include longer pulses and continuous processes. .

[0100] The above embodiments of the application examples and techniques of different energy depositions can facilitate the application under various altitudes and flight conditions. The energy deposition is not limited under different operating atmospheres / conditions, but among numerous thermal spraying coating techniques, in particular; thermal spraying; plasma spraying; detonation spraying; wire arc spraying; flame spraying; high velocity oxy-fuel coating spraying; warm spray; cold spray; can be phase-aligned / synchronized with various types of thermal spraying coating techniques. Similarly, the above embodiments of the application of different energy depositions and techniques can be applied to, among numerous embodiments and application examples (under various possible operating atmospheres and conditions), in particular, looms, gun barrels, trains, engines, moving bodies, explosion mitigation, ignition, detonation. For purposes of illustration of the following description, it is best to first refer to FIGS. 2 and 3 as examples of the expansion described. When energy is "effectively instantaneously" ( "instantaneously") deposited in a specific region of air (e.g., along a line or point), the surrounding air is pushed outward from the expanding blast wave heating region. Until the blast wave generated from the deposited energy decays / slows down to the speed of sound, the surrounding gas is swept outward, leaving a region of high-temperature pressure equilibrium gas, the density of which is much lower than the initial / surrounding density (in some cases, less than 15% of the surrounding density, e.g., less than 10%, less than 8%, less than 5%, less than 3%, less than 2%, or less than 1.5%, and the other 98.5% is pushed outward). When the expanding shock wave decelerates to the speed of sound, it continues to expand at the speed of sound. y oxy-fuel coating spraying); warm spray; cold spray; including various types of thermal spraying coating techniques. Similarly, the above embodiments of the application of different energy depositions and techniques can be applied to, among numerous embodiments and application examples (under various possible operating atmospheres and conditions), in particular, looms, gun barrels, trains, engines, moving bodies, explosion mitigation, ignition, detonation. For purposes of illustration of the following description, it is best to first refer to FIGS. 2 and 3 as examples of the expansion described. When energy is "effectively instantaneously" ( "instantaneously") deposited in a specific region of air (e.g., along a line or point), the surrounding air is pushed outward from the expanding blast wave heating region. Until the blast wave generated from the deposited energy decays / slows down to the speed of sound, the surrounding gas is swept outward, leaving a region of high-temperature pressure equilibrium gas, the density of which is much lower than the initial / surrounding density (in some cases, less than 15% of the surrounding density, e.g., less than 10%, less than 8%, less than 5%, less than 3%, less than 2%, or less than 1.5%, and the other 98.5% is pushed outward). When the expanding shock wave decelerates to the speed of sound, it continues to expand at the speed of sound. For purposes of illustration of the following description, it is best to first refer to FIGS. 2 and 3 as examples of the expansion described. When energy is "effectively instantaneously" ( "instantaneously") deposited in a specific region of air (e.g., along a line or point), the surrounding air is pushed outward from the expanding blast wave heating region. Until the blast wave generated from the deposited energy decays / slows down to the speed of sound, the surrounding gas is swept outward, leaving a region of high-temperature pressure equilibrium gas, the density of which is much lower than the initial / surrounding density (in some cases, less than 15% of the surrounding density, e.g., less than 10%, less than 8%, less than 5%, less than 3%, less than 2%, or less than 1.5%, and the other 98.5% is pushed outward). When the expanding shock wave decelerates to the speed of sound, it continues to expand at the speed of sound. types of thermal spraying coating techniques. Similarly, the above embodiments of the application of different energy depositions and techniques can be applied to, among numerous embodiments and application examples (under various possible operating atmospheres and conditions), in particular, looms, gun barrels, trains, engines, moving bodies, explosion mitigation, ignition, detonation. can be applied to.

[0101] For purposes of illustration of the following description, it is best to first refer to FIGS. 2 and 3 as examples of the expansion described. When energy is "effectively instantaneously" ( "instantaneously") deposited in a specific region of air (e.g., along a line or point), the surrounding air is pushed outward from the expanding blast wave heating region. Until the blast wave generated from the deposited energy decays / slows down to the speed of sound, the surrounding gas is swept outward, leaving a region of high-temperature pressure equilibrium gas, the density of which is much lower than the initial / surrounding density (in some cases, less than 15% of the surrounding density, e.g., less than 10%, less than 8%, less than 5%, less than 3%, less than 2%, or less than 1.5%, and the other 98.5% is pushed outward). When the expanding shock wave decelerates to the speed of sound, it continues to expand at the speed of sound. For purposes of illustration of the following description, it is best to first refer to FIGS. 2 and 3 as examples of the expansion described. When energy is "effectively instantaneously" ( "instantaneously") deposited in a specific region of air (e.g., along a line or point), the surrounding air is pushed outward from the expanding blast wave heating region. Until the blast wave generated from the deposited energy decays / slows down to the speed of sound, the surrounding gas is swept outward, leaving a region of high-temperature pressure equilibrium gas, the density of which is much lower than the initial / surrounding density (in some cases, less than 15% of the surrounding density, e.g., less than 10%, less than 8%, less than 5%, less than 3%, less than 2%, or less than 1.5%, and the other 98.5% is pushed outward). When the expanding shock wave decelerates to the speed of sound, it continues to expand at the speed of sound. For purposes of illustration of the following description, it is best to first refer to FIGS. 2 and 3 as examples of the expansion described. When energy is "effectively instantaneously" ( "instantaneously") deposited in a specific region of air (e.g., along a line or point), the surrounding air is pushed outward from the expanding blast wave heating region. Until the blast wave generated from the deposited energy decays / slows down to the speed of sound, the surrounding gas is swept outward, leaving a region of high-temperature pressure equilibrium gas, the density of which is much lower than the initial / surrounding density (in some cases, less than 15% of the surrounding density, e.g., less than 10%, less than 8%, less than 5%, less than 3%, less than 2%, or less than 1.5%, and the other 98.5% is pushed outward). When the expanding shock wave decelerates to the speed of sound, it continues to expand at the speed of sound. For purposes of illustration of the following description, it is best to first refer to FIGS. 2 and 3 as examples of the expansion described. When energy is "effectively instantaneously" ( "instantaneously") deposited in a specific region of air (e.g., along a line or point), the surrounding air is pushed outward from the expanding blast wave heating region. Until the blast wave generated from the deposited energy decays / slows down to the speed of sound, the surrounding gas is swept outward, leaving a region of high-temperature pressure equilibrium gas, the density of which is much lower than the initial / surrounding density (in some cases, less than 15% of the surrounding density, e.g., less than 10%, less than 8%, less than 5%, less than 3%, less than 2%, or less than 1.5%, and the other 98.5% is pushed outward). When the expanding shock wave decelerates to the speed of sound, it continues to expand at the speed of sound. For purposes of illustration of the following description, it is best to first refer to FIGS. 2 and 3 as examples of the expansion described. When energy is "effectively instantaneously" ( "instantaneously") deposited in a specific region of air (e.g., along a line or point), the surrounding air is pushed outward from the expanding blast wave heating region. Until the blast wave generated from the deposited energy decays / slows down to the speed of sound, the surrounding gas is swept outward, leaving a region of high-temperature pressure equilibrium gas, the density of which is much lower than the initial / surrounding density (in some cases, less than 15% of the surrounding density, e.g., less than 10%, less than 8%, less than 5%, less than 3%, less than 2%, or less than 1.5%, and the other 98.5% is pushed outward). When the expanding shock wave decelerates to the speed of sound, it continues to expand at the speed of sound. For purposes of illustration of the following description, it is best to first refer to FIGS. 2 and 3 as examples of the expansion described. When energy is "effectively instantaneously" ( "instantaneously") deposited in a specific region of air (e.g., along a line or point), the surrounding air is pushed outward from the expanding blast wave heating region. Until the blast wave generated from the deposited energy decays / slows down to the speed of sound, the surrounding gas is swept outward, leaving a region of high-temperature pressure equilibrium gas, the density of which is much lower than the initial / surrounding density (in some cases, less than 15% of the surrounding density, e.g., less than 10%, less than 8%, less than 5%, less than 3%, less than 2%, or less than 1.5%, and the other 98.5% is pushed outward). When the expanding shock wave decelerates to the speed of sound, it continues to expand at the speed of sound. For purposes of illustration of the following description, it is best to first refer to FIGS. 2 and 3 as examples of the expansion described. When energy is "effectively instantaneously" ( "instantaneously") deposited in a specific region of air (e.g., along a line or point), the surrounding air is pushed outward from the expanding blast wave heating region. Until the blast wave generated from the deposited energy decays / slows down to the speed of sound, the surrounding gas is swept outward, leaving a region of high-temperature pressure equilibrium gas, the density of which is much lower than the initial / surrounding density (in some cases, less than 15% of the surrounding density, e.g., less than 10%, less than 8%, less than 5%, less than 3%, less than 2%, or less than 1.5%, and the other 98.5% is pushed outward). When the expanding shock wave decelerates to the speed of sound, it continues to expand at the speed of sound. For purposes of illustration of the following description, it is best to first refer to FIGS. 2 and 3 as examples of the expansion described. When energy is "effectively instantaneously" ( "instantaneously") deposited in a specific region of air (e.g., along a line or point), the surrounding air is pushed outward from the expanding blast wave heating region. Until the blast wave generated from the deposited energy decays / slows down to the speed of sound, the surrounding gas is swept outward, leaving a region of high-temperature pressure equilibrium gas, the density of which is much lower than the initial / surrounding density (in some cases, less than 15% of the surrounding density, e.g., less than 10%, less than 8%, less than 5%, less than 3%, less than 2%, or less than 1.5%, and the other 98.5% is pushed outward). When the expanding shock wave decelerates to the speed of sound, it continues to expand at the speed of sound. ​However, it no longer pushes the gas outward or expands the low-density region. (The low-density region generated when the blast wave expands supersonically) remains, and is pressure balanced by the surrounding pressure (e.g., the low-density region remains as a "bubble" of low-density, high-temperature gas in the surrounding pressure, and the bubble does not collapse by itself, i.e., the bubble is a region where "air is separated"). The volume of this pressure-balanced low-density region is directly proportional to the energy deposited in the gas and also proportional to the surrounding pressure (e.g., the resulting low-density volume doubles when the initial atmospheric pressure before energy deposition is halved). An example of this expansion and the low-density region generated along the surface is shown in FIG. 3. FIG. 3 shows an end view of a single straight leg of the discharge as shown in FIG. 2(b) seen along the path of the discharge, which is a Schlieren photograph.

[0102] The simplest example of an expanding low-density "bubble" can be seen when energy is deposited at a point in air to open a low-density sphere (FIG. 4), and the gas expands spherically and symmetrically from this point (FIG. 5).

[0103] A similarly simple geometry occurs when energy is deposited along a straight line (FIGS. 6, 7, and 8). This causes the gas to expand and open a low-density cylindrical volume (or "tube") centered on the line / axis along which the energy was initially deposited.

[0104] Due to the fact that the high-temperature and low-density geometry is in equilibrium with the surrounding pressure and persists for a long time compared to the hydrodynamics of the object, low-density regions (e.g., spheres and "tubes" in air, and hemispheres and half "tubes" along the surface, as well as other more complex geometries) can interfere with the intended flow ​​​​It can maintain "open" for a time long enough to execute the control thereof.

[0105] One of the simplest ways to imagine the advantages of this approach is to look at a confined explosion. The intuitive knowledge it provides can be directly applied to other high-speed flow applications (e.g., high-speed flight and propulsion systems). Specifically, the inventors can (almost instantaneously) reduce the pressure and induce gas when detecting an undesired pressure rise and / or shock wave. These problems in the field of explosion mitigation are the same concerns that occur in high-speed flight and propulsion systems. Therefore, this first example can be extended to apply the basic concept to a wide range of hypersonic applications. In a specific example of explosion mitigation, when high-pressure explosive gas is confined between the bottom of a moving body and the ground, air is prevented from exiting from under the moving body by the generation of a shock wave in the ambient gas. The longer the high-pressure gas exists under the moving body, the more the pressure on its bottom rises, and the combined shock pushes the moving body upward more strongly. The goal of this application is to vent the high-pressure gas from under the moving body as quickly as possible, thereby reducing the pressure under the moving body and minimizing the combined shock transmitted to the moving body. To achieve this, by opening a low-density path along the bottom surface of the moving body and quickly inducing the high-pressure gas outward from under the moving body, the gas can be quickly vented from under the moving body. This can be achieved by incorporating the inventors' technology (e.g., a directed energy deposition device) into a ground vehicle to form a low-density path, along which the nearby blast wind (e.g., under the lower side of the moving body) can quickly escape. It can be deflected, thereby significantly reducing the force and time with which the blast gas presses on the moving body, , and thus minimizing the total impact applied to the moving body by the blast. FIG. 9 shows that when the initial air density is made lower than that of the moving body, the force and impact that can occur from the explosion are reduced. This is shown as an example.

[0106] To form a high-speed passage through which the high-pressure gas can escape more rapidly from under and around the moving body, the inventors have added a conductive path along the surface of the moving body (similar to the path shown in FIG. 2), which is schematically shown in FIG. 10. These conductive paths can be used to vent the high-pressure gas in the confined volume almost instantaneously, and can be used in high-speed propulsion devices such as isolators, combustors, diffusers, and exhaust systems. This is useful for all applications where it is advantageous to rapidly reduce harmful pressure rises. To form a high-speed passage through which the high-pressure gas can escape more rapidly from under and around the moving body, the inventors have added a conductive path along the surface of the moving body (similar to the path shown in FIG. 2), which is schematically shown in FIG. 10. These conductive paths can be used to vent the high-pressure gas in the confined volume almost instantaneously, and can be used in high-speed propulsion devices such as isolators, combustors, diffusers, and exhaust systems. This is useful for all applications where it is advantageous to rapidly reduce harmful pressure rises. devices, such as isolators, combustors, diffusers, and exhaust systems. This is useful for all applications where it is advantageous to rapidly reduce harmful pressure rises. obtained.

[0107] One reason why a moving body flies inefficiently through the air at high speed is that the moving body is inefficiently accelerating the air column (from the origin to the final destination) with respect to most of its speed. In addition to the resulting high fuel costs, the large amount of energy applied to the air is associated with further problems such as: a strong sonic boom; a shock wave strong enough to cause damage to the moving body behind the nose; and undesired pressures and heating along the leading edge and stagnation lines due to the frictional forces that occur when accelerating the still air to match the speed of the moving body. is associated with further problems such as: a strong sonic boom; a shock wave strong enough to cause damage to the moving body behind the nose; and undesired pressures and heating along the leading edge and stagnation lines due to the frictional forces that occur when accelerating the still air to match the speed of the moving body. is associated with further problems such as: a strong sonic boom; a shock wave strong enough to cause damage to the moving body behind the nose; and undesired pressures and heating along the leading edge and stagnation lines due to the frictional forces that occur when accelerating the still air to match the speed of the moving body.

[0108] Instead, the moving body is directed along a long (e.g., laser filament-induced) line of energy Resistance is dramatically reduced when passing through the low-density "tube" opened by the energy deposition device. The resistance curve is calculated instantly, and the total energy consumption is significantly reduced. An example is shown in Figure 11. In this graph, the cone is a dense gas at the edge of a "tube". As the cone passes through the tube, a slight increase in resistance from the baseline is observed. Drag drops dramatically when the cone flies through the low density areas of the "balloon." When the shock wave is generated again, the resistance will resume to the nominal resistance, the initial / constant resistance. In effect, when a moving object or projectile passes through a low-density "tube," it is transported to another low-density The density "tube" can be opened and the vehicle / projectile will enjoy a continuous reduction in drag. The exact point at which the next "tube" begins can be determined by optimization for a given application. It is important to regenerate the resistance by depositing energy to create another "tube". The extent to which the resistance can consistently rise before decreasing again is a function of the repetition rate of energy deposition. Determine the strength of the pressure regulation that is driven, which moves until energy is deposited (again Divided by the effective tube length (adjusted to accommodate the distance the body / projectile actually travels) This regulation is approximately equal to the speed of the vehicle. This regulation can be an additional source of aircraft noise and can also be due to the resonance of the vehicle. and tuning by adjusting the "tube" length to avoid unpleasant frequencies. Each successive "tube" also redirects the "tube" slightly. It also presents an opportunity to control a vehicle using a virtual reality camera (as addressed further below).

[0109] The drag reduction and energy savings of implementing this technology will be investigated under various parameters. parameters, such as Mach number, cone angle, and diameter of the "tube" compared to the base of the cone were evaluated. These parameters are shown in Figure 12, and it should be understood that the Mach number is for a nominally invariant flow. When energy is deposited upstream the conventional definitions and concepts of uniform Mach number no longer apply This is because the speed of sound inside the "tube" is many times faster than the speed of sound outside the tube in a nominally invariant free flow In the conventional definition, the Mach number inside the "tube" is significantly lower than the Mach number outside the "tube" In fact, in many cases, the flow inside the tube is subsonic compared to the supersonic / hypersonic flow outside the tube, and is a flow field significantly different from the unregulated flow observed when flying in uniform air, due to energy deposition Some of these dynamics can only be achieved by depositing energy into the flow described herein The results regarding maximum drag reduction and energy savings (return on input energy) in the various cases shown in Figure 12 are summarized in Figure 13, and these results include drag reduction of over 60%, for example

[0110] 80% - 95%, and even up to 96% maximum, and a return of over 30 times the input energy in the total energy balance, for example over 50 times or over 65 times (i.e., for each watt or joule deposited into the air in front of the cone to open the low density "tube" along the cone's wake line 65 times this "input" energy is typically required to counteract the much stronger drag that would be encountered if no energy were deposited in front of the cone ​​​​(in terms of the propulsion force or energy saved).

[0111] Several interesting trends were observed in this result, and the most basic observation is that by opening a larger tube, there is a significant reduction in drag for all Mach numbers and cone angles. The more subtle and interesting observation is that the energy efficiency (i.e., [(saved propulsion energy) - (input energy)] / (input energy)) has the following two regions. This energy efficiency indicates how much energy is saved from the propulsion system for each unit of energy deposited in front of the moving body to open the low-density "tube". One region occurs at higher Mach numbers where the cone is narrower, and in this region, the arcuate shock wave tends to be oblique / attached. In this region, the energy efficiency increases with the Mach number, and the most efficient "tube diameter" transitions from a small diameter to a large diameter in a clear and understandable manner as the Mach number increases. The removal of gas along the stagnation line always provides the greatest advantage, and the advantage of removing gas further away from the stagnation line is a function of the speed of the moving body, with the advantage obtained at higher Mach numbers being greater. In the region of low Mach numbers, the arcuate shock wave tends to be a normal stand-off shock, and a strong increase in efficiency is observed with a small-diameter "tube", which can effectively "drill a hole" in the arcuate shock wave, allowing the flow inside the "tube" to be subsonic (in the case of a high-sonic "tube") and no longer constrained by the arcuate shock wave of the cone, thus releasing the high-pressure gas behind the normal shock wave (Figure 14).

[0112] Efficiency studies involve identifying the energy that can be deposited to achieve optimal performance. However, the effects scale should also be noted, and the specific platform The amount of energy deposited in the foam is also a consideration for the platform / vehicle system. It should be noted that the decision can be made based on what is available. Even if the "tube" is opened wider than optimal, there is still increased range and velocity, lower Better mobility / projectiles in terms of fuel consumption and reduction of exhaust and noise / sonic boom performance (other benefits listed below) even if significantly less than optimal It is particularly useful to be able to obtain significant benefits when depositing energy. The actual capacity of the energy storage and power that can be included in the system depends on the available size, weight, and the amount and power available, and how much of these same parameters are relevant to the This flexible iterative process can be determined by how the technology is improved after adoption. This allows room for adoption of the technology in any system that can benefit from it. In addition, the energy required to open a given volume of low density gas varies depending on the ambient pressure. If we assume that the energy deposited in the air is proportional to the amount of energy encountered in increasing altitude, This effect is seen in the case of a given range of energy powers. The system opens up larger and larger "tube" diameters as the vehicle / projectile gains altitude. Instead of increasing the "tube" diameter, the Increased low density volume can be used to increase tube length, or both length and diameter. The increase in "tube" length is itself results in an increase in speed and, as shown in Figure 13, a larger "tube" diameter can help maximize efficiency at higher Mach numbers.

[0113] A representative density-profile frame from the dramatically altered fluid dynamics resulting from flight through a low-density "tube" is shown in Figure 14. Letters A, B, C, D correspond to the times marked on the drag curve of Figure 11 (D does not represent the time when the cone has moved through the first extent of the "tube" and does not account for the deformation / protrusion of the "tube" resulting from the interaction between the tube and the cone).

[0114] By contrasting the differences resulting from the nearly steady density distribution in frame A with the following dynamics, the inventors notice several points: · In normal flight, strong arc-shaped shock waves and associated sonic booms exist, but flight through a low-density "tube" significantly reduces both the arc-shaped shock waves and the associated sonic booms; · In normal flight, gases accelerated laterally and forward by the cone leave the low-pressure / low-density region at the base of the cone, but when the gases move laterally from in front of the cone by depositing energy to form a low-density "tube", the accumulated gases surrounding the "tube" recirculate behind the cone and serve to repressurize the base; · This repressurized base reduces the drag at the base; · The significantly high gas density at the base can also provide a certain level of confinement of the propulsion product, which can greatly enhance the propulsion effectiveness of the exhaust system and multiply its effective impulse. This is a normally low-density and low-pressure base ​​​​​​​​​​​​ Instead of having a simple exhaust of high-pressure products that cannot be confined to a region, recirculated atmospheric gas prevents the retreat of the propulsion products and utilizes their high pressure over a longer time by doing so.

[0115] Staged implementation of propulsion and energy deposition to optimize kinetics Considering a number of beneficial kinetics, the embodiments described herein improve efficiency and can be flexibly applied to utilize / synchronize the synergy / advantages of various steps / processes This can involve optimizing a number of possible parameters, particularly length scale, ignition, air-fuel ratio, timing, repetition rate, chemical processes, discharge, laser pulses, microwave pulses, electron beams, valve regulation / throttling Some embodiments may include the following : · Laser emission: In an example of the application of laser emission, in one embodiment, the focus of the propulsion laser light is re-aligned by a rear-facing optical component to heat and expand the gas or ablation products and extrude them from the rear end of the launcher. One or more ground lasers as a propulsion source are emitted at the rear end of the launcher accompanied by: - Depositing some laser energy in front of the moving body to open a low-density "tube" and reduce resistance - Sizing the moving body and throttling the internal path to allow sufficient propulsion air to be heated by drive laser pulses (multiple available) - Sizing the moving body to form a high-density reverse prevention device that can flow the regulated gas around the front of the moving body to more efficiently push the propulsion gas - Adjusting the internal path of the moving body to allow sufficient propulsion air to be heated by drive laser pulses (multiple available) - Sizing the moving body to form a high-density reverse prevention device that can flow the regulated gas around the front of the moving body to more efficiently push the propulsion gas - Sizing the moving body to form a high-density reverse prevention device that can flow the regulated gas around the front of the moving body to more efficiently push the propulsion gas can be formed; Before the next laser pulse repeats the process, a drive laser pulse is delivered so that the moving body can fully utilize the low density "tube" and the pressing force for propulsion. ·PDE / Chemical Raging / Pulse Power: This type of system requires consideration of the same type of phase alignment / timing optimization as listed above. However, in this case, the drive energy is a series of pulsed chemical detonations occurring inside the moving body. The timing of these detonations can be controlled by appropriately timed valve regulation and ignition, and the detonations can actually propel the process necessary to deposit upstream energy. ·Industrial and Transportation Applications: In these cases, similar timing and system optimization as in the above applications are applied to achieve the desired level of phase alignment through different propulsion forces, such as electric propulsion, and further potential considerations of magnetic levitation. Adjusting / synchronizing time not only ensures the optimal fluid flow but also reduces the amount of energy for each element used in the mounted system, such as propulsion and levitation systems. As already mentioned, discharge not only offers dramatic advantages but can also be used to control aerodynamics and phase-align to ultimately achieve a flexible geometry that requires strong and efficient control over the moving body. Discharge is one possible technology that can realize a flexible geometry that can be used to achieve strong and efficient control over the moving body by controlling and phase-aligning aerodynamics. When discharge is used, a conductive path must be formed so that current can flow. The ability to "draw" a conductive path using a laser pulse (Figure 6) to induce / initiate a discharge (Figure 7) has been demonstrated in other parts. A filament laser can flexibly create any number of desired patterns.

[0116] As already mentioned, discharge not only offers dramatic advantages but can also be used to control aerodynamics and phase-align to ultimately achieve a flexible geometry that requires strong and efficient control over the moving body. Discharge is one possible technology that can realize a flexible geometry that can be used to achieve strong and efficient control over the moving body by controlling and phase-aligning aerodynamics. When discharge is used, a conductive path must be formed so that current can flow. The ability to "draw" a conductive path using a laser pulse (Figure 6) to induce / initiate a discharge (Figure 7) has been demonstrated in other parts. A filament laser can flexibly create any number of desired patterns. When discharge is used, a conductive path must be formed so that current can flow. The ability to "draw" a conductive path using a laser pulse (Figure 6) to induce / initiate a discharge (Figure 7) has been demonstrated in other parts. A filament laser can flexibly create any number of desired patterns. The ability to "draw" a conductive path using a laser pulse (Figure 6) to induce / initiate a discharge (Figure 7) has been demonstrated in other parts. A filament laser can flexibly create any number of desired patterns. The ability to "draw" a conductive path using a laser pulse (Figure 6) to induce / initiate a discharge (Figure 7) has been demonstrated in other parts. A filament laser can flexibly create any number of desired patterns. Such an ionization path having sufficient accuracy and length for drawing can be formed.

[0117] An example is shown in FIG. 15, in which the conductive paths (108a, b) are formed to connect the electrodes 106 and 107 that intersect at point P. I electric The second examples of FIGS. 16 and 17 show further details of an actual discharge device. In this example, the laser pulse 111 is induced in three separate electrically insulated lens / electrode assemblies 102 (FIG. 17). The adjustable (122) optical element 121 focuses different pulses passing through the respective metal cones 123 so that filamentation starts as close as possible to the top of the metal cones.

[0118] This enables the best electrical connection. The metal cones are electrodes connected to the appropriate poles of the capacitor bank. When forming the ionization path, the capacitor discharges its energy along the path. As a result, the electrical energy stored in the capacitor is deposited in the air along the conductive path in the form of ohmic heating. Another embodiment can achieve the control of the desired flow using several energy emission devices arranged / phased for several purposes (FIGS. 18 and 19).

[0119]

[0120] An array of energy emission devices is illustrated in FIG. 18. An array of energy emission mechanisms or elements 106a, 106b, 106c is arranged in the body 101. The body 101 includes a central element 106a surrounded by an inner annular array of elements 106b and an outer annular array of elements 106c. The element

[0120] The entire array of elements 106 can be used to sequentially fire individual elements 106 or groups of elements 106. This increases the efficiency and magnitude of energy deposition. After expanding outward from the central heated core created by core element 106a, element 106 This is achieved by continuously pushing the fluid 105 outward in a cylindrical shape using an array of In this example, when the discharge is performed, the current flows through the other two elements 106b and 106a. The ionization path 108 that completes this conductive circuit is then followed by the next set of conductive paths and The discharge may be between 106c and 106a (or 106b).

[0121] In operation, as illustrated in FIG. 18 (top), the central element 106a and one or more of the inner arrays The upper element 106b can be fired to create a central heating core 160a. The cylindrical shock wave expands outward and may weaken as it expands. To add energy to the weakened cylindrical expansion, the example shown in Figure 18 (bottom) is Element 106b can be fired as shown. Further expansion will cause the outer array Element 106c may also be fired to maintain strong, continued expansion of heating core 160b.

[0122] A schematic diagram of a similar application involving a linear array of energy emitting devices 102 is illustrated in FIG. The energy emitting device 102 is attached to the moving body 101 and emits the energy from the innermost From the emission device 102a, the outermost energy emission device 102f, which is the furthest from the center line of the moving body 101 The continuous firing of the suction nozzles 140 causes the incoming fluid 105 to move outward along the wings 150 in a wave-like motion. Push out.

[0123] The energy release device 102 will typically be electrically insulated, similar to the connection charging unit and the switch. Additionally, as already described in connection with FIGS. 16 and 17, adjacent energy release devices can be efficiently fired simultaneously to generate the conductive path 108. The energy release device 102 can also be fired continuously in pairs to sweep the fluid 105 outward toward the tip of the wing 150 using the discharge. This method of sweeping the fluid toward the tip of the wing also induces the fluid above and below the wing 150. Also, environmental sensors can be included to monitor performance, and the environmental sensors can be coupled to the energy release device to vary various parameters of

[0124] the energy deposition. In addition to the reduction in resistance, there are several related

[0125] advantages associated with the use of the described energy deposition techniques. To examine the control forces and moments associated with this technique, a 3D simulation was performed using the Cobalt CFD solver to generate a low-density core impinging on the moving body over a continuous range of off-axis positions. The offset of the core position is shown as upward in FIG. 20. In these implementations, the initial position of the core is coaxial with the moving body and then gradually moves upward (while maintaining parallelism with the cone axis without an angle of They performed this series of operations to examine the full response range resulting from the core aligned with the flight direction. was performed.

[0126] Figure 21 shows the density, pressure, and temperature on the surface of the body. Moments and forces are entered as coefficients on the same graph. The two moments are calculated as examples of different centers of mass that produce stable flight for different payloads / missions. The inventors also demonstrated that a normally unstable vehicle (center of mass behind the center of pressure) becomes stable when flying through a low-density core. This is because the higher-density gas at the outer edge of the bottom significantly moves the center of pressure behind the rear of the vehicle and behind the center of mass. This advantage of stabilizing a normally unstable design makes the guarantee of a stable hypersonic vehicle much more flexible and can eliminate conventional constraints on the position of the center of mass. Other advantages of this technology include reducing design constraints by allowing a much wider performance envelope, using much lower-cost materials, significantly relaxing the requirements for the fineness of the body, and significantly reducing the weight due to relaxation of the thermal protection system (TPS) requirements, easier inlet (re)start, and significantly reduced control / actuator hardware are further included. The analytical upper bound estimates and calculated lower bounds for a general cone provided control forces from several G to several tens of G depending on altitude and Mach number. These upper and lower bounds provide limits useful for evaluating the practicality of this technology in various applications. In some embodiments, for example, a launch vehicle with a 1 m base obtains useful effects over the entire range of Mach 6 to 20 in order to achieve useful effects over the entire range of Mach 6 to 20. achieve useful effects over the entire range of Mach 6 to 20. achieve useful effects over the entire range of Mach 6 to 20.

[0127] The analytical upper bound estimates and calculated lower bounds for a general cone provided control forces from several G to several tens of G depending on altitude and Mach number. These upper and lower bounds provide limits useful for evaluating the practicality of this technology in various applications. In some embodiments, for example, a launch vehicle with a 1 m base obtains useful effects over the entire range of Mach 6 to 20 in order to evaluate the practicality of this technology in various applications. In some embodiments, for example, a launch vehicle with a 1 m base obtains useful effects over the entire range of Mach 6 to 20 in order to It is possible to utilize a deposition power of 480 kW. This power can be applied: at a distance of 15 km from a hypersonic mobile for a core with a diameter of 1 / 5; at a distance of 30 km for a core with a diameter of 1 / 2; and for a core with the full diameter at an altitude of 45 km. If only 10% of this power is available, the inventors can open a "tube" with a diameter of approximately 1 / 3 of the described diameter and still obtain excellent advantages in terms of efficiency, control, and a significantly simplified design.

[0128] One of the current limiting factors in hypersonic vehicles is the mitigation of the thermal effects of sustained hypersonic flight. In addition to enabling drag reduction and vehicle control, the inventors' approach reduces the temperature of the vehicle's surface and the heat generated. This enables a significant reduction in the weight of the TPS and the special materials required at the leading edge. It also enables a significant improvement in the performance of the vehicle until the limits of the materials are reached. Opening a small-diameter "tube" in front of the vehicle demonstrates significant advantages and helps to guide the vehicle in the same way that pre-drilled holes help to guide a large nail. Nevertheless, it is useful to consider the extreme case of opening a "tube" that can conform to the entire vehicle. This allows for an intuitive understanding of the vehicle as being fixed within the "tube" in the same way as a luge in the Olympic luge competition. When the vehicle begins to collide with the "tube" wall, the vehicle experiences a very strong force that pushes it back around the vehicle. This functions in the vertical direction and in all other directions as well, and the vehicle finds its position, and the weight of the vehicle is balanced at an appropriate position by the upward resistance force. As a result, the entire body functions as a lifting surface, and the relevant vehicle experiences a very strong force that pushes it back around the vehicle. This functions in the vertical direction and in all other directions as well, and the vehicle finds its position, and the weight of the vehicle is balanced at an appropriate position by the upward resistance force. As a result, the entire body functions as a lifting surface, and the relevant The forces and temperatures that are connected can be evenly dispersed. Similarly, the same phenomenon that maintains the balance of gravity is such that by constantly applying a restoring force to restrain the moving body within the tube, the entire body functions as a control surface and can function. On the other hand, this involves that the control can simply guide the "tube" in the desired direction (which can be as easy as guiding the start / inducing laser pulse), along with the fact that the fluid force causes the moving body to follow and, if necessary, disperses the control force across the entire body, guaranteeing this makes the control very attractive. This indicates that it can be traded to help accommodate the hardware required by the inventors' approach by eliminating the need for heavy hypersonic actuators / control surface systems for additional weight and volume requirements. In certain cases, each flap can have a significant associated volume and can weigh approximately 20 kg. These actuators may require power from gas cylinders or the moving body, and since these have additional weight, volume requirements, and risks, they can be eliminated to offset the requirements of the energy deposition system. As described above, the best approach to fully utilize the beneficial points of the technology described in this specification is to design the moving body entirely based on hydrodynamics, which enables the full utilization of the many advantages it provides, including reduction of resistance, stabilization of flight, reduction of design constraints, promotion of lift / control / inlet / thrust, and dramatic improvements in speed, performance, distance, payload, and fuel efficiency. Nevertheless, by enabling a gradual improvement in performance that cannot usually be achieved in systems optimized in other ways, this technology can be integrated into existing platforms

[0129] As described above, the best approach to fully utilize the beneficial points of the technology described in this specification is to design the moving body entirely based on hydrodynamics, which enables the full utilization of the many advantages it provides, including reduction of resistance, stabilization of flight, reduction of design constraints, promotion of lift / control / inlet / thrust, and dramatic improvements in speed, performance, distance, payload, and fuel efficiency. Nevertheless, by enabling a gradual improvement in performance that cannot usually be achieved in systems optimized in other ways, this technology can be integrated into existing platforms and can be used to gradually improve performance that cannot usually be achieved in systems optimized in other ways, thereby enabling a gradual improvement in performance that cannot usually be achieved in systems optimized in other ways, There are a number of ways to gradually "buy its way" into the toform. Some of these examples include: depositing energy along the surface to reduce the resistance of inevitable protrusions (such as vertical tails, joints, rivets, wipers, seams, etc.), and depositing energy at the leading edge or in front of it. In addition to the performance improvements that these technologies can provide, these technologies can also enable capabilities that are not normally achievable. A set of application examples includes, as shown in FIG. 22, opening holes in the side of a moving body into a tube by an oblique shock wave to facilitate the passage of a projectile / sub-moving body, as well as optical imaging and communication capabilities. Opening holes in the shock wave of the main moving body in this way can be particularly valuable in certain hypersonic flight applications. This is because opening the holes enables the formation of a path through which images can be recorded more clearly and a secondary body can be launched from the primary moving body without the strong interaction with the non-open holes in the shock wave that would normally be encountered.

[0130] Further examples of high-speed flow control and supersonic / hypersonic propagation / movement facilitation include propulsion and internal flow applications, particularly starting supersonic inlets, and reducing the noise of engines / augmentors that include key sounds and other resonance sounds. These include surface discharges achieved by the inventors using various types of electrodes, with or without lasers, depending on the specific details. The inventors have also applied energy deposition along the surface and / or in the ambient air for ground applications to improve wind tunnel performance, industrial / manufacturing processes, and transportation.

[0131] transportation. Examples of propulsion and internal flow applications, particularly starting supersonic inlets, and reducing the noise of engines / augmentors that include key sounds and other resonance sounds. These include surface discharges achieved by the inventors using various types of electrodes, with or without lasers, depending on the specific details. The inventors have also applied energy deposition along the surface and / or in the ambient air for ground applications to improve wind tunnel performance, industrial / manufacturing processes, and transportation. is applied to.

[0132] In the above application examples of flight, the primary concern of the inventors is to enable dramatic improvements in capabilities and efficiency. In the application examples of terrestrial industries / manufacturing / transportation, the constraints on size, weight, and power can be more relaxed. The desire to remotely control non-cooperative moving objects has also led the inventors to deposit energy on the remote platform. In this application example, the hydrodynamics resulting from the deposition of energy remain the same. However, rather than carefully designing its own platform to reduce size / weight / power requirements and deposit energy most efficiently into the flow, the main task currently is to deliver energy to the remote platform to control the dynamics of the remote platform. In this case, rather than depositing energy through efficient discharge, the inventors ultimately use relatively inefficient laser (and / or microwave) energy to rapidly / instantaneously deposit energy on or near the surface of the remote platform. The cost of this energy (in terms of the efficiency of its generation) is much higher than simply using onboard discharge as the primary energy deposition source. However , in return, the ability to deliver this energy over long distances remotely is obtained to significantly control the projectile / moving object by locally changing the resistance and lift on the remote projectile / moving object. FIG. 23 shows schlieren images of laser energy deposited on the surface of a remote object in both still air and flowing air. In the inventors' wind tunnel tests, the inventors are concerned with their ability to disrupt the surface flow and boundary layer related to and deposit energy on or near the surface of the remote platform using relatively inefficient laser (and / or microwave) energy. The cost of this energy (in terms of the efficiency of its generation) is much higher than simply using onboard discharge as the primary energy deposition source. However by depositing energy through efficient discharge. Instead, the inventors ultimately use relatively inefficient laser (and / or microwave) energy to rapidly / instantaneously deposit energy on or near the surface of the remote platform. The cost of this energy (in terms of the efficiency of its generation) is much higher than simply using onboard discharge as the primary energy deposition source. However by depositing energy through efficient discharge. Instead, the inventors ultimately use relatively inefficient laser (and / or microwave) energy to rapidly / instantaneously deposit energy on or near the surface of the remote platform. The cost of this energy (in terms of the efficiency of its generation) is much higher than simply using onboard discharge as the primary energy deposition source. However and Moreover, a significant effect on both lift and drag on the wing could be measured.

[0133] Deposition into rapid / instantaneous energy flows, faster than the flow can mechanically respond, can be achieved by generating a blast wave that thins a quantity of gas using a number of embodiments and mechanisms, including lasers, discharges, microwaves, electron beams, etc. This energy can be deposited into various useful geometries that significantly adjust / deform the density of the fluid to achieve excellent control. This control can result from a large difference between the forces that occur when the body interacts with the surrounding fluid density and the forces that occur when the body interacts with a region of dramatically reduced density. Common geometries are combinations of spherical and cylindrical low-density regions ( "tubes") formed outside the body and "hemispherical" and "semicylindrical" low-density regions formed along the surface. These geometries enable a dramatic increase in speed, efficiency, control, and overall performance directly resulting from a significant reduction in resistance, heating, pressure, and shock waves when moving through a fluid of extremely low density (relative to the ambient density). The most advantageous use of the inventors' innovative approach is to design systems based on beneficial dynamics by adjusting the inlet; timing; and propulsion to maximize the effect over the desired full operating range. It is also possible to pursue a reduction in effort by "adopting" existing or near-future platform technologies and / or incorporating these advantages to enable specific capabilities. Such efforts include, among others: the individual reduction of strong shock / drag / heating / pressure; the internal flow of high-speed propulsion units ​​​​​​​​​​​​​​such control; inlet (re)start at low Mach numbers; ground testing; manufacturing; ground transportation; and drilling holes in shock waves generated by a supersonic / hypersonic platform to facilitate the passage of optical signals and sub-mobile bodies may be included.

[0134] Several basic physical mechanisms are the basis for various embodiments in the deposition of energy to achieve the dramatic progress these provide in the control of high-speed flows. The approach of the inventors, which revolutionizes high-speed flight and flow control, is that the inventors, in certain embodiments prioritize moving air to optimize the way air acts. When energy is deposited efficiently and instantaneously (''sharply'') at a point, a spherical shock wave is generated, pushing open a low-density sphere with only 1-2 % of the ambient air density remaining inside. When energy is deposited instantaneously along a line, this same expansion occurs, opening a low-density cylinder containing about 1-2% of the ambient air density. The volume that the inventors will ''open'' is directly proportional to the energy they deposit and directly proportional to the pressure of the ambient air, and thus less energy is required to open a given low-density volume at higher altitudes ( where hypersonic flight is typically conducted) than at lower altitudes. The advantages of flying through 1-2% of the ambient density in the ambient density are numerous and include: significant reduction in drag; enhanced stability; substantial reduction in energy use; no sonic boom; reduction in stagnation temperature and pressure; reduction in noise; re-pressurization of the base ( eliminating base drag and significantly enhancing the propulsion effectiveness of the propulsion system); reduction in exhaust; and a dramatic increase in the flight envelope at each altitude. altitude. The volume that the inventors will ''open'' is directly proportional to the energy they deposit and directly proportional to the pressure of the ambient air, and thus less energy is required to open a given low-density volume at higher altitudes ( where hypersonic flight is typically conducted) than at lower altitudes. The advantages of flying through 1-2% of the ambient density in the ambient density are numerous and include: significant reduction in drag; enhanced stability; substantial reduction in energy use; no sonic boom; reduction in stagnation temperature and pressure; reduction in noise; re-pressurization of the base ( eliminating base drag and significantly enhancing the propulsion effectiveness of the propulsion system); reduction in exhaust; and a dramatic increase in the flight envelope at each altitude. The volume that the inventors will ''open'' is directly proportional to the energy they deposit and directly proportional to the pressure of the ambient air, and thus less energy is required to open a given low-density volume at higher altitudes (

[0135] The main effect we exploit when developing new applications is the instantaneous release of It is our ability to add energy and change the shape of that density. The evolution of large amounts of energy concentrated along point and line sources has been thoroughly characterized. In Plooster's detailed computer studies, he found that the instantaneous deposition of energy We present his data in dimensionless units for an infinite source of radiation (Figs. 24 to 26). In this case, the energy is deposited at r=0, the distance from the origin (in 1D cylindrical coordinates) is In each graph, λ is plotted along the abscissa. , the characteristic radius R of the actual distance r o =(E o / bγp o ) 1 / 2 where E represents the ratio of 0 is simply is the energy deposited per unit length, P 0 is the pressure ahead of the shock, γ=1.4 and b is 3.94. Several plots are drawn on each graph, and above each line These numbers represent the dimensionless time τ, which is a characteristic time of real time t. Time t o =R o / a o where a is the ratio of o is the speed of sound in the surrounding air ahead of the shock wave All fluid parameters are calculated based on the fluid parameters of the surrounding atmosphere ahead of the cylindrical shock wave. The pressure (p / p o ), radial velocity (u / a o ), and the density (ρ / ρ 0 ).

[0136] The further usefulness of these results stems from the fact that Plooster verified these results with various initial conditions (e.g., slight variations in an ideal line source). (Of interest to the inventors) Long-term dynamics, where the initial conditions are essentially the same, range from an ideal line source to a more diffused source, e.g., a deposited energy with a finite spread that includes multiple line sources. This result is considered to be sufficiently robust to further encompass any way the inventors might consider depositing energy along a wide region in front of the shock wave that the inventors want to reduce / control. This fact is derived from the fact that Plooster verified these results with various initial conditions (e.g., slight variations in an ideal line source). (Of interest to the inventors) Long-term dynamics, where the initial conditions are essentially the same, range from an ideal line source to a more diffused source, e.g., a deposited energy with a finite spread that includes multiple line sources. This result is considered to be sufficiently robust to further encompass any way the inventors might consider depositing energy along a wide region in front of the shock wave that the inventors want to reduce / control. Long-term dynamics, where the initial conditions are essentially the same, range from an ideal line source to a more diffused source, e.g., a deposited energy with a finite spread that includes multiple line sources. This result is considered to be sufficiently robust to further encompass any way the inventors might consider depositing energy along a wide region in front of the shock wave that the inventors want to reduce / control. This result is considered to be sufficiently robust to further encompass any way the inventors might consider depositing energy along a wide region in front of the shock wave that the inventors want to reduce / control. This result is considered to be sufficiently robust to further encompass any way the inventors might consider depositing energy along a wide region in front of the shock wave that the inventors want to reduce / control. This result is considered to be sufficiently robust to further encompass any way the inventors might consider depositing energy along a wide region in front of the shock wave that the inventors want to reduce / control.

[0137] Figure 25 shows the expansion shock wave rotation acoustic wave at about τ = 0.147 when the cylindrical shock wave propagates radially outward. This is when the expanding cylinder is relaxed from the blast wind that pushes open the low-density tube, resulting in characteristic compression and rarefaction, which approximately coincides with the time when it starts to become apparent in the pressure trace of Figure 24 at about τ = 0.2. As a result, this time is approximately the same time when the rapid expansion of the low-density tube stops and it remains almost stationary, well exceeding from about τ = 0.14 to τ = 6.0. Figure 26 shows that a very low-density core remains effectively stationary as the acoustic shock wave continues to propagate radially outward, with no change from radius λ = 0 to about λ = 0.5. The beauty and usefulness of this long low-density cylindrical core lie in the fact that the low-density cylindrical core persists for a very long time and can be used as a low-density passage through which a moving body (and / or the high-pressure air pushed forward by the moving body, and / or the accumulation of high-pressure gas that needs to be relieved) can pass with virtually no resistance. Figure 25 shows the expansion shock wave rotation acoustic wave at about τ = 0.147 when the cylindrical shock wave propagates radially outward. This is when the expanding cylinder is relaxed from the blast wind that pushes open the low-density tube, resulting in characteristic compression and rarefaction, which approximately coincides with the time when it starts to become apparent in the pressure trace of Figure 24 at about τ = 0.2. As a result, this time is approximately the same time when the rapid expansion of the low-density tube stops and it remains almost stationary, well exceeding from about τ = 0.14 to τ = 6.0. Figure 26 shows that a very low-density core remains effectively stationary as the acoustic shock wave continues to propagate radially outward, with no change from radius λ = 0 to about λ = 0.5. The beauty and usefulness of this long low-density cylindrical core lie in the fact that the low-density cylindrical core persists for a very long time and can be used as a low-density passage through which a moving body (and / or the high-pressure air pushed forward by the moving body, and / or the accumulation of high-pressure gas that needs to be relieved) can pass with virtually no resistance. This is when the expanding cylinder is relaxed from the blast wind that pushes open the low-density tube, resulting in characteristic compression and rarefaction, which approximately coincides with the time when it starts to become apparent in the pressure trace of Figure 24 at about τ = 0.2. As a result, this time is approximately the same time when the rapid expansion of the low-density tube stops and it remains almost stationary, well exceeding from about τ = 0.14 to τ = 6.0. As a result, this time is approximately the same time when the rapid expansion of the low-density tube stops and it remains almost stationary, well exceeding from about τ = 0.14 to τ = 6.0. Figure 26 shows that a very low-density core remains effectively stationary as the acoustic shock wave continues to propagate radially outward, with no change from radius λ = 0 to about λ = 0.5. The beauty and usefulness of this long low-density cylindrical core lie in the fact that the low-density cylindrical core persists for a very long time and can be used as a low-density passage through which a moving body (and / or the high-pressure air pushed forward by the moving body, and / or the accumulation of high-pressure gas that needs to be relieved) can pass with virtually no resistance. Figure 26 shows that a very low-density core remains effectively stationary as the acoustic shock wave continues to propagate radially outward, with no change from radius λ = 0 to about λ = 0.5. The beauty and usefulness of this long low-density cylindrical core lie in the fact that the low-density cylindrical core persists for a very long time and can be used as a low-density passage through which a moving body (and / or the high-pressure air pushed forward by the moving body, and / or the accumulation of high-pressure gas that needs to be relieved) can pass with virtually no resistance. Figure 26 shows that a very low-density core remains effectively stationary as the acoustic shock wave continues to propagate radially outward, with no change from radius λ = 0 to about λ = 0.5. The beauty and usefulness of this long low-density cylindrical core lie in the fact that the low-density cylindrical core persists for a very long time and can be used as a low-density passage through which a moving body (and / or the high-pressure air pushed forward by the moving body, and / or the accumulation of high-pressure gas that needs to be relieved) can pass with virtually no resistance. The beauty and usefulness of this long low-density cylindrical core lie in the fact that the low-density cylindrical core persists for a very long time and can be used as a low-density passage through which a moving body (and / or the high-pressure air pushed forward by the moving body, and / or the accumulation of high-pressure gas that needs to be relieved) can pass with virtually no resistance. The beauty and usefulness of this long low-density cylindrical core lie in the fact that the low-density cylindrical core persists for a very long time and can be used as a low-density passage through which a moving body (and / or the high-pressure air pushed forward by the moving body, and / or the accumulation of high-pressure gas that needs to be relieved) can pass with virtually no resistance. The beauty and usefulness of this long low-density cylindrical core lie in the fact that the low-density cylindrical core persists for a very long time and can be used as a low-density passage through which a moving body (and / or the high-pressure air pushed forward by the moving body, and / or the accumulation of high-pressure gas that needs to be relieved) can pass with virtually no resistance. The beauty and usefulness of this long low-density cylindrical core lie in the fact that the low-density cylindrical core persists for a very long time and can be used as a low-density passage through which a moving body (and / or the high-pressure air pushed forward by the moving body, and / or the accumulation of high-pressure gas that needs to be relieved) can pass with virtually no resistance.

[0138] To conduct parameter studies to characterize the effect of the low-density tube on the body during flight, the parameters and scales from Plooster's results were used to estimate the energy required to open low-density tubes of various radii. Specifically, the simulation was to demonstrate the beneficial points in reducing shock and resistance when heat is suddenly deposited along the streamlines in front of the arc-shaped shock wave generated by a supersonic / hypersonic cone (in this case, along the stagnation streamline). The continuous beneficial points demonstrated by the line-deposition geometry extend the period of shock reduction / resistance reduction without continuously adding energy. This allows the instantaneous energy deposition mechanism to be repeated in the form of continuous pulses. When energy is suddenly / instantaneously deposited, the air expands as described above to open the low-density "tube". Two mechanisms that function to disrupt this ideal stationary low-density tube (and the spherical or other shapes formed by the expansion of the deposited energy) are: (i) thermal buoyancy; and (ii) heat diffusion. In fact, because these two mechanisms act on a non-uniform density distribution, both interfacial and volumetric fluid instabilities also occur. Similar to a hot air balloon (without a balloon), thermal buoyancy is driven by the buoyancy of the high-temperature low-density gas inside the "tube" or "bubble". Ignoring viscosity, instability, other dissipative forces, and the very low terminal velocity of light objects such as air, the highest upward acceleration that the low-density gas can encounter is the acceleration due to gravity (9.8 m / s ). At the length scales generally of interest to the inventors, 1 cm can be considered small, but it represents a meaningful movement for the low-density gas.

[0139] (Without a balloon), similar to a hot air balloon, thermal buoyancy is driven by the buoyancy of the high-temperature low-density gas inside the "tube" or "bubble". Ignoring viscosity, instability, other dissipative forces, and the very low terminal velocity of light objects such as air, the highest upward acceleration that the low-density gas can encounter is the acceleration due to gravity (9.8 m / s ). At the length scales generally of interest to the inventors, 1 cm can be considered small, but it represents a meaningful movement for the low-density gas. 2 ) ​​​​​​​​​​​​​At the unrealistic upper limit of full gravitational acceleration, the gas would move 1 cm in about 0.05 seconds. This movement is generally characterized by fairly low density features on the order of centimeters or larger. This is much faster than thermal diffusion, which should have a significant effect on the To account for a number of assumptions that make this possible, we assume that significant low density features are at least 0. During this time, even if the vehicle is moving at Mach 0.9, it will move about 30 m. This means that any target moving object can interact with any low-density structure that the inventors wish to form. Provide sufficient time to complete the interaction.

[0140] For low density features of significant size (e.g. features larger than a few centimeters), these features The time scale for the signature to dissipate by thermal diffusion is longer than the time scale of thermal buoyancy estimated above. Thermal diffusion is essentially the flow of thermal energy along a temperature gradient, Eventually, thermal equilibrium is reached (i.e., heat is transferred from the hot gas to the adjacent cooler gas). As can be seen from Fig. 26, the interface of the “tube” has a very strong density gradient, which is very This corresponds to a very strong temperature gradient at the interface of the low density "tube". Because this effect occurs at the surface and acts on small length scales, this effect is extremely Small features on the ends, e.g., very small diameter spheres or very small diameter "tubes" Most notable in.

[0141] A prime example where small, low-density features play a major role is the laser pulse blasting a sample of the material in air. The energy deposited in the plasma creates a very small diameter nucleus that acts as a precursor to the discharge. It occurs when generating a density tube. In this case, the diameter of the low-density tube can be approximately several tens to several hundreds of micrometers or more, as measured by a pulse parameter meter. In such cases, we imaged the dynamics of the "tubes" to evaluate their lifetimes of 100 microseconds to 1 millisecond (Figure 8) and used further diagnostics to confirm these timescales. The main role played by such very small low-density "tubes" formed by intense laser pulses is to help induce and initiate discharges that can deposit a large amount of energy along the path. These discharges are generated along small precursor nuclear paths at speeds of about 10 m / s or more and have a "tube" lifetime sufficient to easily propagate discharges of tens of meters. One additional problem that can be caused by the ionization paths generated by the laser and the small "tubes" is the effect of turbulence. In fact, it has been shown that this is not such a big problem for several reasons: (i) It takes several tens of nanoseconds for the laser pulse to propagate; (ii) It has been demonstrated that filaments and focused pulses can continue to propagate through complex high-speed shocks / turbulence, not just simple turbulence (an example of which is described in more detail in our section on the aerodynamic window); (iii) It takes several microseconds for the expected discharge to develop. For these timescales and dynamics that are essential for the formation using larger operationally useful "tube" discharges, turbulence does not pose a major obstacle because of the much slower timescale than when the turbulence develops.

[0142] 6

[0143] ​​​​​​​​​​​​​​​​​

[0144] The standard feature we use to consider aerodynamic advantage is Plooster's approximately This is a low-density core that has been shown to extend down to λ = 0.5 (Figure 26). If we want the radius of the a to be a certain value, we use λ=r / R o Using the definition of E o ) can be calculated, where R o =(E o / 5.34×p o ) 1 / 2 and p o is the ambient air pressure (the constant 5.34 is derived using the value of γ, which is the water vapor pressure). (It is slightly different from 1.4 to account for the temperature difference in air, and can be calculated for dry air.) Therefore, we can determine the energy per length required to form a low-density core of radius r. First, the inventors o =5.34×po × R o 2 Then, rearrange the data so that , R o Denoting by terms λ and r, we say: E o =5.34×p o ×(r / λ) 2 The inventors obtain The main value of λ that we consider important is λ=0.5, since this is the approximate dimensionless width of the low-density core. The main dimensions that provide us with physical information are the dimensions that we want to create. is the actual radius r of the low-density core. As can be expected, to form a given low-density core, The energy required per unit length to For example, E o =21.5×p o ×(r)2 To explain the additional factor of 1 / 2 (squared), the formula for calculating the actual energy / length is as follows. The formula for calculating the actual energy / length is as follows. E o = 5.34 × p o × (r) 2

[0145] To obtain the total required energy, the inventors must simply multiply E o by the length of the heating path. This length is one of the system parameters that should be optimized during the test phase and is also useful in determining the pulse repetition rate (which must also be optimized). However, the inventors consider here some nominal values in order to be able to determine some nominal gas heating requirements for the pulse energy and average power ranges. However, the inventors consider here some nominal values in order to be able to determine some nominal gas heating requirements for the pulse energy and average power ranges. nominal values in order to be able to determine some nominal gas heating requirements for the pulse energy and average power ranges.

[0146] In one approach to heating the gas in front of the moving body, "interruptions" in the high-temperature path are prevented by forming each new low-density "core" such that its front part collides with the rear part of the preceding core. However, in a way to save power and total energy deposition an interruption of non-heated air remains between consecutive individual cores. This allows the inventors to utilize a part of the time actually required to regenerate an arcuate shock wave in front of the moving body. When the arcuate shock wave of the moving body is regenerated, the next heating core serves to dissipate the arcuate shock wave again. After the moving body exits the low-density core, the actual distance for effectively regenerating a shock wave that can interfere depends on the shape, angle of attack, and flight parameters of the moving body, but regardless of this length, the inventors consider the energy deposition length and the repetition rate. rate. By adjusting the repetition rate, this distance can be accommodated. As an example, in the present invention when we adjust these values so that we can form a tube, the length of the tube is the same as the distance required for a new arcuate shock wave to occur, (since we have a 1:1 ratio of non-heated gas:heated gas along the stagnation line) we can halve the power requirement for energy deposition. A similar phenomenon has been demonstrated when spot heating is used ahead of a moving body. In fact, the optimal ratio of non-heated length to heated length of the hot core is determined by wind tunnel tests and more detailed simulations. Our main motivation for very carefully testing this parameter and using it optimally is that the shock wave seems to require an especially long time for "regeneration" after the moving body exits a low-density "tube". In the above conceptual case (which is consistent with the simulations we have performed), such an approach can save 50% of the energy we deposit, and we can double the current efficiency by (obtaining the same advantages by halving the energy input). The reason for considering the above method(s) of heating an extended air path is for its potential application to shock wave control / mitigation. We start by judging from time-resolved studies of point heating ahead of the shock wave, and then summarize the experiments we have performed to time-stamp the extended heating region.

[0147] The beautiful time-resolved wind tunnel studies by Adelgren et al. (Figs. 27 and 28) show that for a spherical model at Mach 3.45 starting from our judgment from time-resolved studies of point heating ahead of the shock wave, and then summarizing the experiments we have performed to time-stamp the extended heating region.

[0148] at Mach 3.45, for a spherical model It became possible to observe the effect of energy deposition on the arc-shaped shock wave of Dell. The region of laser heating is approximately a point source, but is slightly elongated along the propagation direction of the pulse and occurs transversely with respect to the airflow in the wind tunnel (the beam enters from the side of the wind tunnel). The resulting heat can be effectively approximated as a point source, and the development of this as an expanding spherical shock wave has been widely discussed. The main feature of this expansion is a spherical blast wave that moves the high-density / high-pressure wave outward and leaves a high-temperature low-density "bubble" at the center. This low-density "bubble" expands to a given size (depending on the amount of energy deposited in the air) and then stops when the sonic shock wave continues to expand outward and attenuates. This low-density "bubble" is spherical and similar to the cylindrical low-density "tube / core" formed when energy is deposited along a line, as quantified by Plooster. The expansion of the resulting spherical shock wave is observed as it advances downstream. The low-density "bubble" is found to maintain its virtually constant radius as the decaying sonic shock wave continues to expand.

[0149] Figure 27 shows the addition to a flow of about several tens of mJ using a 10-nanosecond infrared pulse. The expansion of the resulting spherical shock wave is observed as it advances downstream. The low-density "bubble" is found to maintain its virtually constant radius as the decaying sonic shock wave continues to expand. This low-density "bubble" is spherical and similar to the cylindrical low-density "tube / core" formed when energy is deposited along a line, as quantified by Plooster. The fact that it maintains its virtually constant radius as the decaying sonic shock wave continues to expand can be seen. This low-density "bubble" is spherical and similar to the cylindrical low-density "tube / core" formed when energy is deposited along a line, as quantified by Plooster. This low-density "bubble" is spherical and similar to the cylindrical low-density "tube / core" formed when energy is deposited along a line, as quantified by Plooster. when energy is deposited along a line.

[0150] Figure 28 shows the same geometry with a spherical wind tunnel model placed in the flow behind the energy deposition. When overlaid on a schlieren image, the pressure distribution when the laser-induced spherical expansion interacts with the shock wave of the model is shown. Using the surface of the model as the zero axis, the "circular" line in front of the model is the reference surface pressure measured when the flow is not disturbed. The other line is the surface pressure measured when the photograph was taken. These three When the surface of the model is used as the zero axis, the "circular" line in front of the model is the reference surface pressure measured when the flow is not disturbed. The other line is the surface pressure measured when the photograph was taken. These three lines are the surface pressure measured when the photograph was taken. The frame demonstrates the instantaneous pressure drop when the flow of low-density laser-heated "bubbles" passes through the pressure ports on the surface of the model. when it does.

[0151] Figure 29 shows the time evolution of the pressure at the stagnation point (the point with the largest pressure fluctuations) of the model. As the low-density "bubbles" interact with the model and its shock wave, an increase in pressure is seen when the high-density expanding shock wave first interacts with the shock wave and pressure sensors of the model. Subsequently, when the low-density "bubbles" follow, a pressure drop occurs. This results in the outward plume shown in Figure 30, and then this plume destroys the remainder of the arc-shaped shock wave structure This result demonstrates the simple nature of the interaction between the laser-heated gas and the arc-shaped shock wave and flow field of the supersonic object. of the supersonic object.

[0152] To investigate the more efficient cylindrical geometry in detail, PM&AM Research conducted some preliminary experimental studies to evaluate what is required for wind tunnel experiments, and the inventors also performed analytical calculations and numerical simulations on the shock wave-tube geometry by impinging normal shock waves on various low-density geometries. These considerations suggested a significant advantage in using a tube-shaped geometry. A given amount of energy was deposited along a line in front of the shock wave, either at a point in front of the shock wave or along the same line in front of the shock wave (oriented in the direction of shock wave propagation). Compared to point heating, the gas was somewhat mixed, and the overall impact on the shock wave was minimal. For a supersonic vehicle, only a very small amount of air is pushed out of the path of the vehicle with a "point-heated" geometry. Approximately half of the gas expands towards the vehicle and interacts with the shock wave of the vehicle. impinged normal shock waves on various low-density geometries to perform analytical calculations and numerical simulations on the shock wave-tube geometry. These considerations suggested a significant advantage in using a tube-shaped geometry. A given amount of energy was deposited along a line in front of the shock wave, either at a point in front of the shock wave or along the same line in front of the shock wave (oriented in the direction of shock wave propagation). Compared to point heating, the gas was somewhat mixed, and the overall impact on the shock wave was minimal. For a supersonic vehicle, only a very small amount of air is pushed out of the path of the vehicle with a "point-heated" geometry. Approximately half of the gas expands towards the vehicle and interacts with the shock wave of the vehicle. of the shock wave-tube geometry. These considerations suggested a significant advantage in using a tube-shaped geometry. A given amount of energy was deposited along a line in front of the shock wave, either at a point in front of the shock wave or along the same line in front of the shock wave (oriented in the direction of shock wave propagation). Compared to point heating, the gas was somewhat mixed, and the overall impact on the shock wave was minimal. For a supersonic vehicle, only a very small amount of air is pushed out of the path of the vehicle with a "point-heated" geometry. Approximately half of the gas expands towards the vehicle and interacts with the shock wave of the vehicle. suggested a significant advantage in using a tube-shaped geometry. A given amount of energy was deposited along a line in front of the shock wave, either at a point in front of the shock wave or along the same line in front of the shock wave (oriented in the direction of shock wave propagation). Compared to point heating, the gas was somewhat mixed, and the overall impact on the shock wave was minimal. For a supersonic vehicle, only a very small amount of air is pushed out of the path of the vehicle with a "point-heated" geometry. Approximately half of the gas expands towards the vehicle and interacts with the shock wave of the vehicle. either at a point in front of the shock wave or along the same line in front of the shock wave (oriented in the direction of shock wave propagation). Compared to point heating, the gas was somewhat mixed, and the overall impact on the shock wave was minimal. For a supersonic vehicle, only a very small amount of air is pushed out of the path of the vehicle with a "point-heated" geometry. Approximately half of the gas expands towards the vehicle and interacts with the shock wave of the vehicle. Compared to point heating, the gas was somewhat mixed, and the overall impact on the shock wave was minimal. For a supersonic vehicle, only a very small amount of air is pushed out of the path of the vehicle with a "point-heated" geometry. Approximately half of the gas expands towards the vehicle and interacts with the shock wave of the vehicle. For a supersonic vehicle, only a very small amount of air is pushed out of the path of the vehicle with a "point-heated" geometry. Approximately half of the gas expands towards the vehicle and interacts with the shock wave of the vehicle. from the path of the vehicle with a "point-heated" geometry. Approximately half of the gas expands towards the vehicle and interacts with the shock wave of the vehicle. On the one hand, it hits the "front", while the latter half moves in the direction away from the moving body, and is only "caught up" by the shock wave of the moving body and absorbed by the shock wave. In contrast, in the case of rapid line heating, almost all of the gas expanding in a cylindrical shape is pushed laterally from the path of the moving body (or at least deviates from its stagnation line). The moving body is observed to preferentially move along the low-density tube and enjoys a long-term decrease in temperature, pressure, and density at the leading edge and along the entire front surface of the moving body. Furthermore, if the gas moves laterally before the moving body encounters it, instead of accelerating the moving body forward and laterally, the gas instead comes to the position where it should recirculate behind the moving body. This recirculation usually recompresses the bottom that is normally in a vacuum, which not only eliminates the resistance at the bottom but also provides a denser medium that can push the propulsion system, thus dramatically improving the propulsion efficiency. These dynamics are shown in Figure 14, and a parametric study of dramatic resistance reduction and energy savings is reported in the attached documents and references of this overview. It is only "caught up" by the shock wave and is absorbed by the shock wave as a result. In contrast, in the case of rapid line heating, almost all of the gas expanding in a cylindrical shape is pushed laterally from the path of the moving body (or at least deviates from its stagnation line). The moving body is observed to preferentially move along the low-density tube and enjoys a long-term decrease in temperature, pressure, and density at the leading edge and along the entire front surface of the moving body. Furthermore, if the gas moves laterally before the moving body encounters it, instead of accelerating the moving body forward and laterally, the gas instead comes to the position where it should recirculate behind the moving body. This recirculation usually recompresses the bottom that is normally in a vacuum, which not only eliminates the resistance at the bottom but also provides a denser medium that can push the propulsion system, thus dramatically improving the propulsion efficiency. These dynamics are shown in Figure 14, and a parametric study of dramatic resistance reduction and energy savings is reported in the attached documents and references of this overview.

[0153] When the moving body makes full use of the heating path (core), it can form another instantaneously heated path, with a repetition rate based on the size and speed of the moving body, as well as the length of the heating core and the length of any non-heated space allowed between consecutive cores where the remaining is allowed.

[0154] The technology proposed by the present inventors depends greatly on the coupling of electromagnetic energy into the air in an accurately defined extended geometry in front of the shock wave of the moving body. Laser "discharges" or "sparks" have been continuously studied since the great success in the 1960s. Similar relationships exist at various wavelengths and ​has been obtained, and mechanisms contributing thereto, such as the diffusion of dust and carriers, have also been confirmed. However, in the application examples of the present inventors, the present inventors require a non-simple spark in air. The present inventors require a sufficiently controlled and extended band of air that should be heated as efficiently as possible. These methods can still be optimized, and one of the main concerns of the present inventors is the ionization and energy deposition resulting from laser pulses propagating in the atmosphere.

[0155] The advantage of using ultraviolet wavelengths is controllable ionization and energy deposition. A number of researchers have deposited energy in air using infrared lasers, and the infrared lasers also have their merits. One advantage is that the materials of available infrared laser amplifiers are widespread, and another is the very strong heating and ionization capabilities. Conversely, a fairly large amount of secondary light generated by infrared absorption reduces the energy available for heating the air.

[0156] Comparing ultraviolet laser-induced ionization and infrared laser-induced ionization, the actual mechanisms are quite different. One of the main differences is that the higher frequency of ultraviolet light allows the ultraviolet light to penetrate a wider range of plasmas. This occurs because the laser frequency must exceed the plasma frequency of ionization so as not to be reflected by the ionized gas. Therefore, as soon as an (infrared, low-frequency) laser begins to ionize the gas, the infrared laser is strongly reflected, scattered, and absorbed by the newly generated plasma. The result is generally that the energy remaining in the pulse is less than before. A single-ionization spot that prevents propagation in a direction, or along the path of the pulse is a series of plasma "balls". In the case of a single-ionization spot, the general elongation is due to various mechanisms associated with a laser-induced detonation wave that propagates backward toward the laser and can occur along the pulse width. This detonation wave can propagate at a speed of 10 m / s, thereby providing a means for forming an extended high-temperature path in front of the moving object 5 . Unfortunately, the inventors have only seen reports of relatively short paths (on the order of centimeters) that are effective only for applications that are significantly smaller than what is currently considered . However, the formation of a series of plasma balls by infrared induction has been observed over several meters, and even this "dot" line can serve as an approximation for the formation of the "extended high-temperature path" required by the inventors . . . Another difference in the ionization mechanisms of infrared and ultraviolet light is the competition between "avalanche" or "cascade" ionization and multi-photon ionization . The results of these analyses show that all of shorter wavelengths, shorter pulses, and lower-pressure gases promote multi-photon ionization, while longer wavelengths, longer pulses, and higher gas pressures promote cascade ionization . Cascade ionization occurs in the presence of a high photon density by bremsstrahlung radiation. This process is assisted by the atoms / molecules of the gas and accelerates the electrons forward after absorbing the momentum of the laser photons

[0157] . The increase in the momentum of the free electrons continues until they have sufficient kinetic energy to ionize another electron bound to the atoms / molecules of the gas by impact . . . . . . . This thereby Two electrons that absorb photons and increase their kinetic energy. These dynamics are Continued, as long as one electron has enough photons, gas molecules sufficient to interact, and enough time for a number of steps, the one electron can be multiplied any number of times The estimated threshold intensity required to achieve such dissociation is as follows: I th ≒(ω 2 +ν eff 2 )×(τ p ×ν eff ) -1 where ν eff is the effective rate of momentum transfer between the electron and the gas particles (proportional to the gas pressure ); ω is the laser frequency; τ p is the pulse width. It is obvious that I th becomes lower with lower laser frequency, higher pressure, and longer pulse length.

[0158] In the case of multiphoton ionization, high-order collisions occur among non-ionized gas atoms / molecules and n photons (sufficient to supply the ionization energy). As an example, the first ionization potential of nitrogen molecules is 15.5 eV, and 248 nm KrF radiation has a photon energy hν of 5 eV. Since at least 4 such photons are required to provide 15.5 eV, ionization is considered a 4-photon process (i.e., n = 4). For photons of 1.06 μm, hν = 1.165 eV, n = 13, and for photons of 10.6 μm, hν = 0.1165 eV, it becomes an n = 134 photon process (a very low-probability collision). Using further empirical rules, a pulse length where multiphoton ionization is dominant can be shown: P×τ <10 p ​​​​​​-7 (Torr×s)

[0159] This is, at atmospheric pressure, τ p should be less than 100 picoseconds in multiphoton ionization which should be dominant, and longer pulses with higher energy can be used at lower pressures (higher altitudes ) as suggested.

[0160] As already mentioned, the cascade ionization occurring with long infrared pulses strongly reflects and scatters most of the light in the pulse. In the case of ultraviolet pulses, the ionization region can be kept relatively transparent to the pulse and can ionize an extended region of the gas. In fact, it is possible to ionize a region centered on the optical focus of the system, one "Rayleigh range" (z ) extending in either direction:

Number

Number

[0161] Comparing the energies required by two different ionization mechanisms, the inventors find that short ultraviolet pulses are much more efficient / effective in forming conductive paths. 248 Using radiation of nm, 10 13 e - / cm 3 to ionize air with a diameter of 1 cm 2 and a length of 1 meter to create an air passage, only 2.4 mJ of pulse energy is required. On the other hand , the problem of plasma reflection can be avoided, and if an infrared laser can be used for ionization of the same passage almost completely (2.7×10 19 e - / cm 3 ), about 6.4 J of pulse energy is required. The use of this total amount of energy from the laser is , generally very costly due to the inefficient conversion of electricity to laser light. If instead , a laser filament that couples energy to a gas to open a very small diameter low-density passage is formed in air, a high-energy discharge can be performed using this low-density passage , and the low-density passage couples its energy to air much more efficiently than a laser . The energy radiated by the discharge is also generated much more inexpensively than the energy emitted by the laser . When combining and matching the most useful elements of each deposition method, the inventors noticed that the ionization of air by a 1.06 μm laser pulse is enhanced when pre-ionization is performed . One possible application of this phenomenon is to strategically couple infrared light to air using ionization from an ultraviolet laser species to show where infrared energy deposition occurs. To facilitate this process , ultraviolet light can be generated as a harmonic of infrared light. Ultraviolet light exceeds the ionization generated by a conductive laser pulse and couples energy to air to form a low-density passage . Ultraviolet light can be generated as a harmonic of infrared light. Ultraviolet light exceeds the ionization generated by a conductive laser pulse and couples energy to air to form a low-density passage It has great significance in that it also forms a path. In this low-density passage, charges can be accelerated more easily, and thereby, discharge along the path of the ionization laser pulse occurs much more easily. The associated short time scale also increases the promoting effect that metastable species, such as , metastable oxygen can have. A potential alternative way to couple low-cost energy to a pre-ionized and then rarefied gas region is the use of microwave energy. This study of this coupling is currently in its initial stage. The main advancement in the laser pulse technology that significantly expands the options for the inventors to heat an extended path is the advancement of filament formation. Filaments have been investigated in detail by many researchers

[0162] and most of this research has been about infrared filaments. Ultraviolet filaments are recommended to eliminate / complement many drawbacks of using infrared wavelengths . According to one theory, ultraviolet filaments can be kilometers long, can contain several joules of energy, have a radius of about 100 μm, and ionize gas between about 1×10 and 1×10 e / cm 12 - e 3 / cm 16 - 3 e - / cm 3 of . In contrast, infrared filaments cannot contain energy exceeding several mJ, and when this energy is depleted (due to propagation loss), the filament is destroyed and diffracts very strongly. Brodeur states that when most of the filament energy diffracts from a higher ionization inner core, it has a boundary diameter of 1 mm (penumbral diam eter) ​suggests intermittent movement to the (eter), and later shows this by simulation This light remains as a reservoir for the formation of new filaments when the previous filament is destroyed

[0163] Comparing ultraviolet and infrared light, the ultraviolet filaments were shown to lose about 40 μJ / m and cause ionization of about 2 × 10 15 e - / cm 3 This is more than 20 times the ionization measured in the infrared filaments and is reported as a 20-fold increase in conductivity. Another beneficial point is that ultraviolet filaments do not lose energy by "conical emission" of light and thus use their energy more efficiently to ionize and heat the gas. This can be rephrased as more efficient formation of small low-density tubes that facilitate the generation of discharges

[0164] The theoretical results are shown in Fig. 30 and demonstrate the oscillatory exchange over meter-length scales between field intensity and ionization. Assuming sufficient initial energy and pulse width these oscillations occur within an envelope that can extend over kilometers. In both Figs. 30 and 31, the vertical axis is in μm and the horizontal axis is in meters The line in Fig. 31 represents the filament boundary for an initial power of 160 MW and shows that the beam is virtually non-spreading, and the predictions of this model are in good agreement with the experiment. The similarity to infrared filaments in the oscillation between ionization and photon density suggests potentially interesting interactions between the filament arrays. In this case, the individual "boundary" fields overlap, which is possible ​​​​​​​​​There is a possibility that crosstalk or energy exchange between the array filaments becomes possible. This kind of array will be formed by creating an initial beam profile that has a maximum local intensity at specific points with respect to the core filaments. An array of filaments one meter in length will be an effective way to deposit energy in a very concentrated and controlled manner. One possibility for combining the two would be to use an ultraviolet filament array that functions as a waveguide for infrared light. The intensity of the infrared light can be made lower than the intensity normally required to ionize the gas, but the ionization region between the ultraviolet filaments will help couple the infrared light to the gas. This will make it possible to efficiently couple the infrared light to the gas without the normally required high field intensity. Such a complementary approach can mitigate infrared ionization and the associated wasteful generation of bright light (which is typically too strong). The low-density channels formed by the ultraviolet filaments can also more effectively guide the infrared light. In the method that the inventors first focused on for cost - effectively increasing heat accumulation, a low - density region generated by a laser - ionized gaseous strip or filament is used to form the core of a discharge and induce the discharge. This was done by inducing an 80 mJ, 1 - picosecond laser pulse between two toroidal electrodes to form an ionization path between these electrodes. The electrodes were maintained at a voltage lower than their normal discharge voltage, and the path ionized by the laser served as the nucleation site for the discharge. The intensity of the infrared light can be made lower than the intensity normally required to ionize the gas, but the ionization region between the ultraviolet filaments will help couple the infrared light to the gas. This will make it possible to efficiently couple the infrared light to the gas without the normally required high field intensity. Such a complementary approach can mitigate infrared ionization and the associated wasteful generation of bright light (which is typically too strong). The low - density channels formed by the ultraviolet filaments can also more effectively guide the infrared light. This will make it possible to efficiently couple the infrared light to the gas without the normally required high field intensity. Such a complementary approach can mitigate infrared ionization and the associated wasteful generation of bright light (which is typically too strong). The low - density channels formed by the ultraviolet filaments can also more effectively guide the infrared light. This will make it possible to efficiently couple the infrared light to the gas without the normally required high field intensity. Such a complementary approach can mitigate infrared ionization and the associated wasteful generation of bright light (which is typically too strong). The low - density channels formed by the ultraviolet filaments can also more effectively guide the infrared light. Such a complementary approach can mitigate infrared ionization and the associated wasteful generation of bright light (which is typically too strong). The low - density channels formed by the ultraviolet filaments can also more effectively guide the infrared light. The low - density channels formed by the ultraviolet filaments can also more effectively guide the infrared light. The low - density channels formed by the ultraviolet filaments can also more effectively guide the infrared light.

[0165] In the method that the inventors first focused on for cost - effectively increasing heat accumulation, a low - density region generated by a laser - ionized gaseous strip or filament is used to form the core of a discharge and induce the discharge. This was done by inducing an 80 mJ, 1 - picosecond laser pulse between two toroidal electrodes to form an ionization path between these electrodes. The electrodes were maintained at a voltage lower than their normal discharge voltage, and the path ionized by the laser served as the nucleation site for the discharge.

[0166] This was done by inducing an 80 mJ, 1 - picosecond laser pulse between two toroidal electrodes to form an ionization path between these electrodes. The electrodes were maintained at a voltage lower than their normal discharge voltage, and the path ionized by the laser served as the nucleation site for the discharge. nucleation site for the discharge. A low-density path was formed between the electrodes, and this low-density path became the core of the discharge, guiding the discharge linearly (Fig. 32). This pre-ionizing laser pulse can reduce the breakdown voltage by 25 - 50% (the breakdown voltage is usually about 20 - 30 kV / cm at sea level). This improvement in the breakdown voltage results from multiple mechanisms, and the main advantage is obtained from a small low-density region / tube opened by a small amount of energy deposited by the laser pulse itself. Longer filament -initiated / induced discharges have been demonstrated as shown in Fig. 7, with an intermediate length of 2 m being generated .

[0167] The inventors also generated a discharge by connecting multiple paths formed by multiple laser pulses as shown in Fig. 6 (Fig. 33).

[0168] To further pursue the practical implementation of this technology on an actual platform, the filament-forming laser was propagated through an aerodynamic window. Aerodynamic windows have historically been used to "separate" two regions that must transmit high-intensity laser energy. This is necessary when the laser intensity is high enough that the energy cannot pass through the solid window without catastrophic destruction of both the solid window and the beam. Instead of separating different regions with a solid window, an aerodynamic window separates them with a cross-flow of air . High-pressure air passes through a nozzle / throat and expands, generating shock waves and rarefaction waves on both sides of the window . This creates a strong pressure gradient in front of and behind the window (perpendicular to the direction of the flow). When the respective high and low pressures match the external pressures on both sides of the window, the laser pulse can pass through . ​​​​​When small holes are drilled (see Fig. 34), there is little or no flow passing through or flowing into / out of the window.

[0169] The use of the aerodynamic window allows for a clean separation between the energy release device and any external atmospheric conditions. This can range from stationary applications at sea level to supersonic / hypersonic applications at various altitudes. Indeed, the flow within the aerodynamic window can be adjusted to accommodate changing external conditions (e.g., altitude and fluctuations in external pressure due to the speed / geometry of the moving body).

[0170] In the demonstrations by the inventors, filaments were formed by the propagation of plasma from the vacuum side of the aerodynamic window (Fig. 34) into the ambient atmosphere. Filaments also propagated through the turbulent / shocked flow within the aerodynamic window from the atmosphere and reached pressures in the range of 4 Torr to 80 Torr (approx. 0.53 kPa to 10.67 kPa). At these low pressures, the filaments became defocused and exited the low-pressure chamber through the solid window. Subsequently, it was reported that filaments were reformed again under atmospheric conditions. These geometries demonstrate the robust nature of the ultraviolet filaments and remove the concern that they are too fragile to be implemented and deployed from platforms in any range, including supersonic / hypersonic applications.

[0171] As a cost-effective way to deposit large amounts of "low-cost" energy into the air, similar to the inventors' technique of coupling electrical discharges to laser plasmas, microwave energy is also more cost-effective than laser energy and a cost-effective way to increase the energy deposited into the air along the geometry of the plasma set by the laser. ​​​​​​​ can be similarly useful. Energy is emptied into the air by the plasma generated by the laser Two related beneficial points of using microwaves to more efficiently couple energy into the air are: (i ) there is no need to close a circuit to couple the energy; (ii) the energy can be deposited remotely which can be fast and beneficial. By combining multiple energy deposition techniques, additional flexibility can be provided, especially with respect to laser pulses and / or fila ments of various wavelengths, discharges, microwave pulses, and / or electron beams. Certain conceptual geometries and resulting couplings have been reported, and the inventors are also investigating the details of the coupling of short microwave pulses to laser plasmas and filaments .

[0172] In the various individual mechanisms that occur sequentially, Table 1 presents the appropriate context that takes into account the response times of all sensors and electronics used in the entire system, summarizing the conceptual time scales associated with each step of a conceptual application example that provides the desired aerodynamic advantages. The table shows two relaxation mechanisms, thermal diffusion and thermal buoyancy, and compares the regions where they are dominant . In the very small "tubes" formed by the filaments themselves (which enable the generation of discharges), thermal diffusion is the fastest mechanism that functions to eliminate the high-temperature, low-density tubes . In this case, the tubes persist over a time scale longer than a few microseconds, which is required to generate a discharge . In the larger "tubes" formed by the large amount of energy deposited by the discharge, thermal diffusion (acting at the interface of the low-density and high-density gases that define the tube) is negligible, and the rate-limiting step that destroys the tube is thermal buoyancy​​​ The mechanism is thermal buoyancy and instability, which impart a significant shock to the tube within milliseconds, and this time is sufficient for propagation through the tube even for the slowest moving object. The time scale required to actually open the tube is also estimated, and this estimate is fast enough to open the tube in a time sufficient to gain the advantage of flying through the tube even for the fastest moving object. (Often no laser is required) Many applications are possible, including flow control by depositing energy on the surface, and during this energy deposition, the applicable time scale remains approximately the same. Table 1 does not address this time scale because the time scale for the coupling of microwave energy to a laser plasma has not yet been clearly quantified. Table 1: Basic time scales for conceptual applications Ultra-short pulse lasers form filaments at plasma densities of about 10 13 ~10 16 e - / cc. a. Speed of light: (3×10 8 m / s) → 1 foot / nanosecond (30.48 cm / nanosecond) Electrons recombine: transfer energy (i.e., heat) to the gas b. Plasma recombines in about 10 nanoseconds (up to 100 nanoseconds) Open a small low-density passage (enable discharge) c. Open in tens of nanoseconds (destruction begins by thermal diffusion over 100 microseconds to 1 millisecond) Generate a discharge d. 10 6 ~10 7 m / s → 10 feet / microsecond (304.8 cm / nanosecond) The discharge persists for several microseconds e. Pass an electric current to ohmically heat the gas (linear lightning) Open a large low-density passage f. From several tens of microseconds to several hundreds of microseconds (destruction due to thermal buoyancy several tens of milliseconds later, which enables low-resistance propagation over several tens of meters for a moving object moving at 1 km / s) 1 km / second moving object can have low-resistance propagation over several tens of meters) The total time of this entire process is approximately equal to the time to open a large tube (about 100 microseconds) Equal g. Fast enough compared to the flight speed (a moving object moving at 1 - 3 km / s moves only 10 - 30 cm in the time it takes to open a large tube, and the moving object can move several tens of meters through the tube in several tens of milliseconds) open a large tube, and the moving object can move several tens of meters through the tube in several tens of milliseconds) )

[0173] In considering various applications, hardware and latency are important factors to consider, and in this specification, it is suggested to emphasize their consideration in determining the timing chain of a specific application. Because in order to construct a working system with realistic estimations, (in addition to the basic time scales summarized in Table 1) these hardware time scales must also be considered. For example, in the relaxation of inlet unstart, the physical time scale is important, but sensors, signals, and any processing (the inventors prefer to eliminate, if possible, by purely using hardware solutions) can add latency (especially for pressure sensors, because other hardware items are typically fast). Looking into an example of a specific system, compared to other currently available technologies, the fast response time of the inventors' flow control approach stands out. and in this specification, it is suggested to emphasize their consideration in determining the timing chain of a specific application Because in order to construct a working system with realistic estimations (in addition to the basic time scales summarized in Table 1) these hardware time scales must also be considered (inlet unstart), the physical time scale is important, but sensors, signals and any processing (the inventors prefer to eliminate, if possible, by purely using hardware solutions) can add latency (especially for pressure sensors, because other hardware items are typically fast) ). Looking into an example of a specific system compared to other currently available technologies, the fast response time of the inventors' flow control approach stands out .

[0174] The inventors include a mechanism for coupling a low-cost discharge and / or a microwave source, energy Some subtle issues of deposition in the flow of water are discussed. A more physical / intuitive understanding of the dynamics is presented. To help deepen the understanding and stimulate future development of this broad range of innovative technologies, They're working on a ton of details to fundamentally change how people fly.

[0175] So far, energy has been used to move fluid, e.g., air, laterally out of the path of an object. The deposition of ions reduces resistance, thereby promoting forward motion of the object. The energy deposition is disclosed in various other patents [citing the Kremeyer patent]. In one embodiment of the drag reduction, the object is Energy is deposited to create a moving low density region. This low density region has a finite range, and as the object moves to maintain the advantage of propagation through low density areas. Additional low density regions can be formed in the vicinity of the surface of the substrate. These regions can be formed very close to each other. If this is achieved, it is possible to form a nearly continuous low-density region and enjoy the benefits of nearly continuity. Low density regions require energy to establish, which reduces their benefits. It is more effective to make optimal use of the “best advantage” definition / goal depending on the application and These benefits may vary based on the relative value of the benefits and resources involved. Although not guaranteed, it is possible to choose a combination of speed, range, energy, weight, and sound, among other possibilities. These include acoustic characteristics, momentum, time, power, size, payload, effectiveness, accuracy, and maneuverability. These advantages vary depending on the application and the specific parameters. must be tailored to a given implementation and its specific conditions and goals. 。The inventors of the present invention disclose the concept of adjusting specific embodiments and the concept of incorporating pulse energy deposition synchronized with other pulse events or unique events to optimize the desired advantages in this specification. Some examples are shown below.

[0176] (Synchronized Pulse Operation for Application Examples of High-Speed Projectiles / Launch Vehicles) In previous disclosures, the dynamics of a moving body moving through a low-density tube have been disclosed, and the pulse effect that starts when the moving body enters the low-density tube has been demonstrated. This effect persists for a specific period, which depends to some extent on the length of the low-density tube and the speed of the moving body. FIGS. 14A to 14D are arranged in sequence continuously, and the approximate relative time of each is separated by the resistance trace of the insertion diagram. One aspect of the dynamics to note is that when a conical conceptual moving body passes through a higher-density sheath of air surrounding the low-density tube formed by the deposited energy line, the resistance of the conceptual moving body slightly increases. This higher-density sheath contains gas that has been extruded outward cylindrically to dilute the low-density tube. When the moving body enters the low-density portion of the tube, it encounters a significantly reduced resistance. At time D, the moving body has traversed the first length of the tube, and as is clear from the resistance curve, additional time is required to re-establish the conditions of steady-state flow. A further point to note is the apparent complete removal of the arcuate shock wave and the associated sonic boom of the far-field during the passage of the moving body through the low-density tube. Beyond these very interesting aspects, one important aspect of the dynamics is the pressure distribution around the moving body resulting from the redistributed density.

[0177] ​​​​​​​​​​​

[0178] As can be seen in FIG. 14A, before the migrating body enters the low density portion of the tube, the migrating body The density at the base of the moving body is extremely low. This rarefied low density / low pressure region at the base of the moving body is a typical ultra-low pressure region. This is the result of sonic / hypersonic fluid dynamics. This region is responsible for throwing snow out of the path of the snowplow. The snowplow (leaving a cleared area behind it) is also moving forward and to the side from the vehicle. This dynamic also arises from the gas in the path of the moving object being pushed in the opposite direction. This is similar to the kinetics we use to deposit energy to form low density regions. In either case, the gas is forced outwards, leaving behind a rarefied region. This is in contrast to the typical case of supersonic / hypersonic flight, where no energy is deposited in front of the moving object. In contrast, the mechanical energy imparted by the moving body to the upstream gas is This results in a high pressure region and shock wave, and the high pressure behind the shock wave, known as wave drag, acts on the transition. The moving body mechanically pushes the gas forward and laterally outward from the moving body. The vacuum remaining after the movement creates a low pressure area of ​​vacuum at the bottom of the moving body, causing the moving body to move backwards. Both of these forces are the forces we have been trying to overcome by applying energy to the front of the moving object. The gas is then pushed laterally out of the path of the moving object, resulting in a large reduction in the amount of gas that can be pumped through the gas. The extent to which these forces are relaxed is based on the length of the material that we deposit in front of the moving body. The amount of energy in the moving body is determined by the amount of gas in the moving body. Removal of gas from the front of the moving body reduces wave drag. Also, the gas that is mechanically pushed outward when pushed by the moving body is minimized. (which also minimizes the sonic boom). As mentioned above, bottom drag is typically It arises from a low pressure area that remains when a moving object or projectile mechanically pushes gas outward from it. In contrast, the gas in front of the moving object / projectile absorbs the energy in front of the moving object / projectile. When pushed to the side by the pile, the mobile object / projectile This leaves a low density region behind the moving object that acts as a drag at the bottom, and this gas flows just outside the moving object's path. It may be more stationary, or if in the path of the moving object, it may be more likely to be detected by the moving object itself. are not mechanically accelerated and, as a result, the lateral force exerted on the gas by the moving object / projectile is The less transverse momentum is added to the gas, the Sonic booms are reduced and the bottom is not thinned. Gas from the front of the moving body is absorbed by the moving body. It is completely removed at the edge of the body (for example, opening a tube whose radius is the same as the radius of the moving body). In this limit, the high-density region of gas pushed out of the low-density tube immediately follows the mover. The bottom is almost completely recirculated and repressurizes the bottom. This repressurized bottom is the total resistance of the moving body. In addition to contributing significantly to the reduction of drag, this effect, in combination with the pulse propulsion process, The overall efficiency of the movement of the moving object can be maximized. Considering aerodynamic characteristics, propulsion force, and the actual pulse propulsion process. highly compressible flight regimes, particularly the supersonic and hypersonic regimes, and the high subsonic / transonic regimes This allows for even further optimization of the vehicle in the region. In one embodiment, the best advantage is that Design aircraft with this concept to produce the simplest and most cost-effective vehicle. Other best advantages are those already mentioned, e.g. the shortest possible flight. The time it takes to move the aircraft is one example of this. In addition to depositing the lug, the inventors have, in order to achieve the desired effect(s), synchronized these dynamics with a pulse propulsion system (which is far more efficient than steady propulsion, for example, among several other pulse propulsion options, a pulse detonation engine). Other and / or additional processes can also be synchronized with these dynamics to achieve further advantages, and the inventors first consider pulse propulsion using the example of a pulse detonation engine. Two conceptual representations of the dynamics of a pulse detonation engine are shown in FIG. 18.

[0179] One very important aspect of pulse propulsion is the pressure at the exit / exhaust plane of the system. In a typical case of very low base pressure that creates a very low pressure at the exit / exhaust plane of the propulsion system, the detonation tube (the combustion part of the pulse detonation engine) is very rapidly filled with reactants. Assuming a very low backpressure, the high-pressure part of the propulsion cycle (the blow-down time) also does not last very long. The typical propulsion cycle time is determined by the engine design, and its geometry can be varied to change that cycle time. Additional important factors that affect the cycle time are: the mass flow rate at the inlet (more specifically, typically the mass flow rate and pressure at the inlet plane of the detonation tube, which is opened and closed by a valve) that affects the rate at which the tube is filled with reactants; the residence time of the high-pressure detonation products and the pressure at the exit / exhaust plane that affects the thrust obtained from them. It is determined by parameters. When the present inventors add the above energy deposition dynamics , it becomes possible to very conveniently change the conditions at both the inlet and outlet of the pulse detonation engine .

[0180] In a basic approach, air from the front wraps around the moving body to repressurize the outlet(s) of one or more propulsion units , and higher density air that enhances the confinement of the exiting gas is adjusted in time with the energy deposition pulse in front of the moving body using a propulsion pulse to coincide with the propulsion part of the pulse propulsion (e.g., pulse detonation) cycle. In other words, the dynamics result in a bottom pressure rise (i.e., a pressure rise at the propulsion unit / unit outlet / exhaust plane(s)) from the energy deposited in front of the moving body to optimize the propulsion force / thrust generated by one or more pulse detonation engine cycles . The synchronization / phasing / time adjustment includes that. The additional confinement provided by the increase in density at the propulsion unit or unit outlet(s) significantly enhances the propulsion effectiveness for unaugmented operation. Similarly, the establishment of a low bottom pressure when the arc shock wave of the moving body is re-established (after being reduced by the low density tube) can be synchronized / phased / time adjusted to facilitate the purge and fill stages of the propulsion cycle. The lower bottom pressure enables a more rapid purge of combustion products and the filling of new reactants for combustion. This can be done in air breathing or rocket mode

[0181] (where an oxidizer is carried and outside air is not used). Rocket mode is used when maximum power / thrust is desired regardless of external conditions, especially when speed and power are critical . The lower bottom pressure enables a more rapid purge of combustion products and the filling of new reactants for combustion. This can be done in air breathing or rocket mode (where an oxidizer is carried and outside air is not used). Rocket mode is used when maximum power / thrust is desired regardless of external conditions, especially when speed and power are critical It can be applied when evaluated against the reduction of the weight and volume of a moving body.

[0182] When the propulsion process is air bleeding, the inventors can adjust the energy deposition time to preferentially direct a certain amount of air moved from the front of the moving body to the inlet. All of these details can be optimized by the design of the moving body, where the times are adjusted relative to each other and utilize various dynamics. The coincidence between the repressurization period and the maximum exhaust pressure period is determined by the inventors by changing the lengths of the low-density tube and the PDE respectively, and adjusting the timing between the two. In particular, all of these parameters can be adjusted to optimize the performance of the moving body for a given application. Similarly, the inlet can be designed to allow air to enter for supplying a propulsion cycle that has already been specified to some extent by previous coincidence conditions. To add flexibility, the inventors do not need to match the same cycle (for example, if a slug of high-density gas around the body is moving too slowly due to surface friction to repressurize the bottom, the inventors can adjust the size of the moving body so that the high-pressure period generated by the inventors at the bottom does not necessarily start when the low-density tube is initiated, and can adjust the kinetic time to match the thrust generation stage of a certain PDE cycle). For example, if the inventors desire a shorter low-density tube or a shorter engine (or a shorter detonation tube of the engine), additional flexibility can be added, like a Gatling gun (or in any pattern that provides the most advantageous forces and dynamics). All of these details can be optimized by the design of the moving body, where the times are adjusted relative to each other and utilize various dynamics. The coincidence between the repressurization period and the maximum exhaust pressure period is determined by the inventors by changing the lengths of the low-density tube and the PDE respectively, and adjusting the timing between the two. In particular, all of these parameters can be adjusted to optimize the performance of the moving body for a given application. Similarly, the inlet can be designed to allow air to enter for supplying a propulsion cycle that has already been specified to some extent by previous coincidence conditions. To add flexibility, the inventors do not need to match the same cycle (for example, if a slug of high-density gas around the body is moving too slowly due to surface friction to repressurize the bottom, the inventors can adjust the size of the moving body so that the high-pressure period generated by the inventors at the bottom does not necessarily start when the low-density tube is initiated, and can adjust the kinetic time to match the thrust generation stage of a certain PDE cycle). For example, if the inventors desire a shorter low-density tube or a shorter engine (or a shorter detonation tube of the engine), additional flexibility can be added, like a Gatling gun (or in any pattern that provides the most advantageous forces and dynamics). The coincidence between the repressurization period and the maximum exhaust pressure period is determined by the inventors by changing the lengths of the low-density tube and the PDE respectively, and adjusting the timing between the two. In particular, all of these parameters can be adjusted to optimize the performance of the moving body for a given application. Similarly, the inlet can be designed to allow air to enter for supplying a propulsion cycle that has already been specified to some extent by previous coincidence conditions. To add flexibility, the inventors do not need to match the same cycle (for example, if a slug of high-density gas around the body is moving too slowly due to surface friction to repressurize the bottom, the inventors can adjust the size of the moving body so that the high-pressure period generated by the inventors at the bottom does not necessarily start when the low-density tube is initiated, and can adjust the kinetic time to match the thrust generation stage of a certain PDE cycle). For example, if the inventors desire a shorter low-density tube or a shorter engine (or a shorter detonation tube of the engine), additional flexibility can be added, like a Gatling gun (or in any pattern that provides the most advantageous forces and dynamics). The coincidence between the repressurization period and the maximum exhaust pressure period is determined by the inventors by changing the lengths of the low-density tube and the PDE respectively, and adjusting the timing between the two. In particular, all of these parameters can be adjusted to optimize the performance of the moving body for a given application. Similarly, the inlet can be designed to allow air to enter for supplying a propulsion cycle that has already been specified to some extent by previous coincidence conditions. To add flexibility, the inventors do not need to match the same cycle (for example, if a slug of high-density gas around the body is moving too slowly due to surface friction to repressurize the bottom, the inventors can adjust the size of the moving body so that the high-pressure period generated by the inventors at the bottom does not necessarily start when the low-density tube is initiated, and can adjust the kinetic time to match the thrust generation stage of a certain PDE cycle). One approach that can be applied is to form a plurality of engines that operate continuously and provide. Each detonation tube can have its own inlet, and the inlet can be provided by a similar continuous application of ring electrodes that arc discharge alternately with respect to the central electrode. These discharges form a V-shape that is initiated / induced by a laser. The V-shape not only removes air from in front of the moving body to reduce total resistance, but also compresses the air between the legs of the V-shape to facilitate its intake through an inlet that is smaller than normally required. To supply higher pressure and oxygen to the engines at their inlets, the inlets fire in the same order as the detonations in the plurality of engine tubes, but are delayed by an amount of time determined to best match the advantage of bottom re-pressurization combined with the presentation of high-density gas at the inlet with the overall engine cycle designed for the platform. It is common to consider valves that open when taking in air and close during detonation. By adding a rotary valve (e.g., following the same spirit as the Gatling gun concept), its rotation can be adjusted / changed to appropriately facilitate the propulsion sequence. Such a rotational movement can similarly be utilized to facilitate the generation of laser filaments. The upstream energy deposition and the timing of the engine cycle affect both the system design and the operating parameters that adjust the length and diameter of the engine tubes. Together, the number of engines themselves can also be determined such that the cycle time of the propulsion pulse is equal to the cycle time of the energy deposition. These cycle times can range from less than 1 millisecond to several.

[0183] can be in the range of milliseconds. In particular, one interesting range is high speed (conceptually Mach 6 to Mach 12, resulting in a cycle time of 0.025 milliseconds to 0.2 milliseconds) for energy deposition with a short line (conceptually 10 cm to 40 cm). To match these energy deposition cycle times with equivalent propulsion cycle times, it is possible to adapt to this match using an appropriate number of shorter engine tubes with appropriately adjusted diameters. To utilize both the high-pressure cycle and the low-pressure cycle resulting from the dynamics of the resistance-reducing tubes, the tubes can be adjusted to generate a propulsion pulse shorter than this cycle time. A perfect match between energy deposition and the propulsion cycle may be sought if the timing requirements become overly constraining. Further variables that help achieve the best possible match, including or excluding matching the duration of the propulsion pulse with the pressure cycle at the bottom of the energy deposition, are the extent to which air is conditioned and enters the inlet of the potential array to potentially drive the potential array of engine tubes. To better match the dynamics, there is also flexibility to discharge each of a potential number of engine tubes at its own separate exhaust plane, or to discharge the engine tubes into one or more common exhaust planes. At the other end of the potential cycle time, longer cycle times can be obtained when flying at lower speeds (e.g., Mach 0.8 to Mach 6) using longer tubes (e.g., 1 to 10 m) for the deposited energy, resulting in a certain range of resistance reduction and a cycle time of the bottom pressure of about 40 milliseconds to 0.5 milliseconds (to match the propulsion cycle time). These longer cycle times Using a small number of engine tubes including elbows, it is possible to match the details that depend greatly on the design and operating conditions of the moving body and the engine (tubes (plural)). ) can be made to match the details that depend greatly on the design and operating conditions of the moving body and the engine (tubes (plural)).

[0184] Similar to the use of a discharge along a closed path, which is induced and initiated by an ionization laser pulse (e.g., a laser filament), energy can also be deposited further in front of the moving body using more remote deposition techniques, such as for example, the deposition of microwave energy. This deposition is also potentially seeded / facilitated in this case by forming an ionization region in front of the moving body using a laser plasma. This microwave energy can also be preferentially induced upstream using a laser plasma, e.g., a laser filament. The high microwave energy resulting from a sufficiently short microwave pulse can be used with or without seeding to increase the coupling of the microwave energy into the air. Three advantages of depositing energy further upstream are, in particular: (i) there is no need for a return path, simplifying and reducing the energy input to any induction / seeding path or region; (ii) the volume into which the energy is supplied takes longer to expand and is advantageous when flying at very high Mach numbers (e.g., Mach 9 - 25), although laser-induced discharges also present very significant advantages at these speeds; (iii) in cases where the shock wave is ionized typically above Mach 12 or 13, the more remotely focused microwave and / or laser energy can enter the ionized shock wave and address any problems that can arise from a discharge interacting with the ionized shock wave. This microwave energy can also be preferentially induced upstream using a laser plasma, e.g., a laser filament. The high microwave energy resulting from a sufficiently short microwave pulse can be used with or without seeding to increase the coupling of the microwave energy into the air. Three advantages of depositing energy further upstream are, in particular: (i) there is no need for a return path, simplifying and reducing the energy input to any induction / seeding path or region; (ii) the volume into which the energy is supplied takes longer to expand and is advantageous when flying at very high Mach numbers (e.g., Mach 9 - 25), although laser-induced discharges also present very significant advantages at these speeds; (iii) in cases where the shock wave is ionized typically above Mach 12 or 13, the more remotely focused microwave and / or laser energy can enter the ionized shock wave and address any problems that can arise from a discharge interacting with the ionized shock wave. advantages at these speeds; (iii) in cases where the shock wave is ionized typically above Mach 12 or 13, the more remotely focused microwave and / or laser energy can enter the ionized shock wave and address any problems that can arise from a discharge interacting with the ionized shock wave. advantages of depositing energy further upstream are, in particular: (i) there is no need for a return path, simplifying and reducing the energy input to any induction / seeding path or region; (ii) the volume into which the energy is supplied takes longer to expand and is advantageous when flying at very high Mach numbers (e.g., Mach 9 - 25), although laser-induced discharges also present very significant advantages at these speeds; (iii) in cases where the shock wave is ionized typically above Mach 12 or 13, the more remotely focused microwave and / or laser energy can enter the ionized shock wave and address any problems that can arise from a discharge interacting with the ionized shock wave. advantages at these speeds; (iii) in cases where the shock wave is ionized typically above Mach 12 or 13, the more remotely focused microwave and / or laser energy can enter the ionized shock wave and address any problems that can arise from a discharge interacting with the ionized shock wave. advantages at these speeds; (iii) in cases where the shock wave is ionized typically above Mach 12 or 13, the more remotely focused microwave and / or laser energy can enter the ionized shock wave and address any problems that can arise from a discharge interacting with the ionized shock wave. advantages at these speeds; (iii) in cases where the shock wave is ionized typically above Mach 12 or 13, the more remotely focused microwave and / or laser energy can enter the ionized shock wave and address any problems that can arise from a discharge interacting with the ionized shock wave. advantages at these speeds; (iii) in cases where the shock wave is ionized typically above Mach 12 or 13, the more remotely focused microwave and / or laser energy can enter the ionized shock wave and address any problems that can arise from a discharge interacting with the ionized shock wave. advantages at these speeds; (iii) in cases where the shock wave is ionized typically above Mach 12 or 13, the more remotely focused microwave and / or laser energy can enter the ionized shock wave and address any problems that can arise from a discharge interacting with the ionized shock wave. is to mitigate. In the explanation of this consideration when using discharge, it is necessary that the laser path is more advantageous than other potential paths that include various levels of ionization at the ionization Mach number. In addition to depositing energy in the air in front of the moving body, in order to condition the air that the moving body encounters (which is taken in at the inlet(s) in the case of air bleeding applications), it is also possible to utilize surface discharges for in-phase / synchronous control of energy deposition both internally and externally to control the internal and external flows and promote the propulsion effectiveness, performance, control, and / or overall efficiency of the moving body.

[0185] In addition to depositing energy in the air in front of the moving body, in order to condition the air that the moving body encounters (which is taken in at the inlet(s) in the case of air bleeding applications), it is also possible to utilize surface discharges for in-phase / synchronous control of energy deposition both internally and externally to control the internal and external flows and promote the propulsion effectiveness, performance, control, and / or overall efficiency of the moving body. In addition to depositing energy in the air in front of the moving body, in order to condition the air that the moving body encounters (which is taken in at the inlet(s) in the case of air bleeding applications), it is also possible to utilize surface discharges for in-phase / synchronous control of energy deposition both internally and externally to control the internal and external flows and promote the propulsion effectiveness, performance, control, and / or overall efficiency of the moving body. In addition to depositing energy in the air in front of the moving body, in order to condition the air that the moving body encounters (which is taken in at the inlet(s) in the case of air bleeding applications),

[0186] Similar to the application examples of the above high-speed flying bodies / projectiles, in order to optimize certain advantages, energy can be deposited in front of the high-speed ground vehicle and phased / synchronized / time coordinated with various other operating processes. In the case of high-speed trains, most of the infrastructure for depositing energy already exists. Electrical pulses are already induced in the tracks to levitate, propel, monitor, and / or control the ground vehicle. This existing infrastructure significantly facilitates the use of grid power that provides the energy that must be deposited to form a low-density region in front of the ground vehicle that dramatically reduces resistance and enables much higher speed operation. In certain embodiments, since there are already tracks that define the path of the ground vehicle and guide the ground vehicle, no laser pulses are required. High-energy discharges can be used to deposit energy in front of the ground vehicle along the path of the ground vehicle to open a low-density region or tube that follows the tracks precisely. Similar to the application examples of the above high-speed flying bodies / projectiles, in order to optimize certain advantages, energy can be deposited in front of the high-speed ground vehicle and phased / synchronized / time coordinated with various other operating processes. In the case of high-speed trains, most of the infrastructure for depositing energy already exists. Electrical pulses are already induced in the tracks to levitate, propel, monitor, and / or control the ground vehicle. This existing infrastructure significantly facilitates the use of grid power that provides the energy that must be deposited to form a low-density region in front of the ground vehicle that dramatically reduces resistance and enables much higher speed operation. In certain embodiments, since there are already tracks that define the path of the ground vehicle and guide the ground vehicle, no laser pulses are required. High-energy discharges can be used to deposit energy in front of the ground vehicle along the path of the ground vehicle to open a low-density region or tube that follows the tracks precisely. Similar to the application examples of the above high-speed flying bodies / projectiles, in order to optimize certain advantages, energy can be deposited in front of the high-speed ground vehicle and phased / synchronized / time coordinated with various other operating processes. In the case of high-speed trains, most of the infrastructure for depositing energy already exists. Electrical pulses are already induced in the tracks to levitate, propel, monitor, and / or control the ground vehicle. This existing infrastructure significantly facilitates the use of grid power that provides the energy that must be deposited to form a low-density region in front of the ground vehicle that dramatically reduces resistance and enables much higher speed operation. In certain embodiments, since there are already tracks that define the path of the ground vehicle and guide the ground vehicle, no laser pulses are required. High-energy discharges can be used to deposit energy in front of the ground vehicle along the path of the ground vehicle to open a low-density region or tube that follows the tracks precisely. Similar to the application examples of the above high-speed flying bodies / projectiles, in order to optimize certain advantages, energy can be deposited in front of the high-speed ground vehicle and phased / synchronized / time coordinated with various other operating processes. In the case of high-speed trains, most of the infrastructure for depositing energy already exists. Electrical pulses are already induced in the tracks to levitate, propel, monitor, and / or control the ground vehicle. This existing infrastructure significantly facilitates the use of grid power that provides the energy that must be deposited to form a low-density region in front of the ground vehicle that dramatically reduces resistance and enables much higher speed operation. In certain embodiments, since there are already tracks that define the path of the ground vehicle and guide the ground vehicle, no laser pulses are required. High-energy discharges can be used to deposit energy in front of the ground vehicle along the path of the ground vehicle to open a low-density region or tube that follows the tracks precisely. Similar to the application examples of the above high-speed flying bodies / projectiles, in order to optimize certain advantages, energy can be deposited in front of the high-speed ground vehicle and phased / synchronized / time coordinated with various other operating processes. In the case of high-speed trains, most of the infrastructure for depositing energy already exists. Electrical pulses are already induced in the tracks to levitate, propel, monitor, and / or control the ground vehicle. This existing infrastructure significantly facilitates the use of grid power that provides the energy that must be deposited to form a low-density region in front of the ground vehicle that dramatically reduces resistance and enables much higher speed operation. In certain embodiments, since there are already tracks that define the path of the ground vehicle and guide the ground vehicle, no laser pulses are required. High-energy discharges can be used to deposit energy in front of the ground vehicle along the path of the ground vehicle to open a low-density region or tube that follows the tracks precisely. Similar to the application examples of the above high-speed flying bodies / projectiles, in order to optimize certain advantages, energy can be deposited in front of the high-speed ground vehicle and phased / synchronized / time coordinated with various other operating processes. In the case of high-speed trains, most of the infrastructure for depositing energy already exists. Electrical pulses are already induced in the tracks to levitate, propel, monitor, and / or control the ground vehicle. This existing infrastructure significantly facilitates the use of grid power that provides the energy that must be deposited to form a low-density region in front of the ground vehicle that dramatically reduces resistance and enables much higher speed operation. In certain embodiments, since there are already tracks that define the path of the ground vehicle and guide the ground vehicle, no laser pulses are required. High-energy discharges can be used to deposit energy in front of the ground vehicle along the path of the ground vehicle to open a low-density region or tube that follows the tracks precisely. Similar to the application examples of the above high-speed flying bodies / projectiles, in order to optimize certain advantages, energy can be deposited in front of the high-speed ground vehicle and phased / synchronized / time coordinated with various other operating processes. In the case of high-speed trains, most of the infrastructure for depositing energy already exists. Electrical pulses are already induced in the tracks to levitate, propel, monitor, and / or control the ground vehicle. This existing infrastructure significantly facilitates the use of grid power that provides the energy that must be deposited to form a low-density region in front of the ground vehicle that dramatically reduces resistance and enables much higher speed operation. In certain embodiments, since there are already tracks that define the path of the ground vehicle and guide the ground vehicle, no laser pulses are required. High-energy discharges can be used to deposit energy in front of the ground vehicle along the path of the ground vehicle to open a low-density region or tube that follows the tracks precisely. Similar to the application examples of the above high-speed flying bodies / projectiles, in order to optimize certain advantages, energy can be deposited in front of the high-speed ground vehicle and phased / synchronized / time coordinated with various other operating processes. In the case of high-speed trains, most of the infrastructure for depositing energy already exists. Electrical pulses are already induced in the tracks to levitate, propel, monitor, and / or control the ground vehicle. This existing infrastructure significantly facilitates the use of grid power that provides the energy that must be deposited to form a low-density region in front of the ground vehicle that dramatically reduces resistance and enables much higher speed operation. In certain embodiments, since there are already tracks that define the path of the ground vehicle and guide the ground vehicle, no laser pulses are required. High-energy discharges can be used to deposit energy in front of the ground vehicle along the path of the ground vehicle to open a low-density region or tube that follows the tracks precisely. Similar to the application examples of the above high-speed flying bodies / projectiles, in order to optimize certain advantages, energy can be deposited in front of the high-speed ground vehicle and phased / synchronized / time coordinated with various other operating processes. In the case of high-speed trains, most of the infrastructure for depositing energy already exists. Electrical pulses are already induced in the tracks to levitate, propel, monitor, and / or control the ground vehicle. This existing infrastructure significantly facilitates the use of grid power that provides the energy that must be deposited to form a low-density region in front of the ground vehicle that dramatically reduces resistance and enables much higher speed operation. In certain embodiments, since there are already tracks that define the path of the ground vehicle and guide the ground vehicle, no laser pulses are required. High-energy discharges can be used to deposit energy in front of the ground vehicle along the path of the ground vehicle to open a low-density region or tube that follows the tracks precisely. Similar to the application examples of the above high-speed flying bodies / projectiles, in order to optimize certain advantages, energy can be deposited in front of the high-speed ground vehicle and phased / synchronized / time coordinated with various other operating processes. In the case of high-speed trains, most of the infrastructure for depositing energy already exists. Electrical pulses are already induced in the tracks to levitate, propel, monitor, and / or control the ground vehicle. This existing infrastructure significantly facilitates the use of grid power that provides the energy that must be deposited to form a low-density region in front of the ground vehicle that dramatically reduces resistance and enables much higher speed operation. In certain embodiments, since there are already tracks that define the path of the ground vehicle and guide the ground vehicle, no laser pulses are required. High-energy discharges can be used to deposit energy in front of the ground vehicle along the path of the ground vehicle to open a low-density region or tube that follows the tracks precisely. The size of the low-density tube promotes the aerodynamic stability of the ground vehicle while achieving the desired level of resistance reduction. It can be controlled to cause a decrease. As long as energy is deposited in front of the flying object the diameter of the tube is determined by the energy deposited per unit length and by the ambient atmospheric pressure When depositing energy along the ground or along a line, (as long as the energy is deposited along the line in the outside air) the ideal shape of the low-density tube is not a circular cylinder centered on the line of the deposited energy, but a semi-cylindrical shape of the tube when depositing energy along an ideal line on an ideal plane. If we assume that the semi-cylinder is replicated like a reflection with respect to an ideal plane, the semi-cylinder would appear to be a complete cylinder, exactly the same as in the case of deposition in the outside air. Since only half of the cylinder is rarefied, only half of the energy required to achieve a complete cylinder in the outside air is needed to open a semi-cylinder along the ground (along the line) of the same diameter. In practice, due to the deviation of the geometry of the line from being perfectly flat, and the interaction between the shock wave generated by the deposited energy and the ground and the actual geometry of the line, it deviates from the ideal. However, the low-density volume opened in front of a ground vehicle is approximately the same as the volume of an ideal semi-cylinder on an ideal plane, and its actual shape can be adjusted / controlled by shaping the line. In fact, at a level that does not react to the details of the deposition, a number of beneficial features can be incorporated into the process. One of these features is the ability to deposit energy (to form the low-density tube) in the form of a plurality of sub-pulses rather than a single large pulse during discharge. This allows the size / capacity of a number of circuit elements and conductors to be

[0187] If we assume that the semi-cylinder is replicated like a reflection with respect to an ideal plane, the semi-cylinder would appear to be a complete cylinder, exactly the same as in the case of deposition in the outside air. Since only half of the cylinder is rarefied, only half of the energy required to achieve a complete cylinder in the outside air is needed to open a semi-cylinder along the ground (along the line) of the same diameter. In practice, due to the deviation of the geometry of the line from being perfectly flat, and the interaction between the shock wave generated by the deposited energy and the ground and the actual geometry of the line, it deviates from the ideal. However, the low-density volume opened in front of a ground vehicle is approximately the same as the volume of an ideal semi-cylinder on an ideal plane, and its actual shape can be adjusted / controlled by shaping the line. In fact, at a level that does not react to the details of the deposition, a number of beneficial features can be incorporated into the process. One of these features is the ability to deposit energy (to form the low-density tube) in the form of a plurality of sub-pulses rather than a single large pulse during discharge. This allows the size / capacity of a number of circuit elements and conductors to be However, the low-density volume opened in front of a ground vehicle is approximately the same as the volume of an ideal semi-cylinder on an ideal plane, and its actual shape can be adjusted / controlled by shaping the line. In fact, at a level that does not react to the details of the deposition, a number of beneficial features can be incorporated into the process. One of these features is the ability to deposit energy (to form the low-density tube) in the form of a plurality of sub-pulses rather than a single large pulse during discharge. This allows the size / capacity of a number of circuit elements and conductors to be However, the low-density volume opened in front of a ground vehicle is approximately the same as the volume of an ideal semi-cylinder on an ideal plane, and its actual shape can be adjusted / controlled by shaping the line. In fact, at a level that does not react to the details of the deposition, a number of beneficial features can be incorporated into the process. One of these features is the ability to deposit energy (to form the low-density tube) in the form of a plurality of sub-pulses rather than a single large pulse during discharge. This allows the size / capacity of a number of circuit elements and conductors to be However, the low-density volume opened in front of a ground vehicle is approximately the same as the volume of an ideal semi-cylinder on an ideal plane, and its actual shape can be adjusted / controlled by shaping the line. In fact, at a level that does not react to the details of the deposition, a number of beneficial features can be incorporated into the process. One of these features is the ability to deposit energy (to form the low-density tube) in the form of a plurality of sub-pulses rather than a single large pulse during discharge. This allows the size / capacity of a number of circuit elements and conductors to be However, the low-density volume opened in front of a ground vehicle is approximately the same as the volume of an ideal semi-cylinder on an ideal plane, and its actual shape can be adjusted / controlled by shaping the line. In fact, at a level that does not react to the details of the deposition, a number of beneficial features can be incorporated into the process. One of these features is the ability to deposit energy (to form the low-density tube) in the form of a plurality of sub-pulses rather than a single large pulse during discharge. This allows the size / capacity of a number of circuit elements and conductors to be However, the low-density volume opened in front of a ground vehicle is approximately the same as the volume of an ideal semi-cylinder on an ideal plane, and its actual shape can be adjusted / controlled by shaping the line. In fact, at a level that does not react to the details of the deposition, a number of beneficial features can be incorporated into the process. One of these features is the ability to deposit energy (to form the low-density tube) in the form of a plurality of sub-pulses rather than a single large pulse during discharge. This allows the size / capacity of a number of circuit elements and conductors to be However, the low-density volume opened in front of a ground vehicle is approximately the same as the volume of an ideal semi-cylinder on an ideal plane, and its actual shape can be adjusted / controlled by shaping the line. In fact, at a level that does not react to the details of the deposition, a number of beneficial features can be incorporated into the process. One of these features is the ability to deposit energy (to form the low-density tube) in the form of a plurality of sub-pulses rather than a single large pulse during discharge. This allows the size / capacity of a number of circuit elements and conductors to be However, the low-density volume opened in front of a ground vehicle is approximately the same as the volume of an ideal semi-cylinder on an ideal plane, and its actual shape can be adjusted / controlled by shaping the line. In fact, at a level that does not react to the details of the deposition, a number of beneficial features can be incorporated into the process. One of these features is the ability to deposit energy (to form the low-density tube) in the form of a plurality of sub-pulses rather than a single large pulse during discharge. This allows the size / capacity of a number of circuit elements and conductors to be However, the low-density volume opened in front of a ground vehicle is approximately the same as the volume of an ideal semi-cylinder on an ideal plane, and its actual shape can be adjusted / controlled by shaping the line. In fact, at a level that does not react to the details of the deposition, a number of beneficial features can be incorporated into the process. One of these features is the ability to deposit energy (to form the low-density tube) in the form of a plurality of sub-pulses rather than a single large pulse during discharge. This allows the size / capacity of a number of circuit elements and conductors to be However, the low-density volume opened in front of a ground vehicle is approximately the same as the volume of an ideal semi-cylinder on an ideal plane, and its actual shape can be adjusted / controlled by shaping the line. In fact, at a level that does not react to the details of the deposition, a number of beneficial features can be incorporated into the process. One of these features is the ability to deposit energy (to form the low-density tube) in the form of a plurality of sub-pulses rather than a single large pulse during discharge. This allows the size / capacity of a number of circuit elements and conductors to be It can be reduced and the existing circuits can be utilized more effectively. For example, at a given point in time or when there are multiple propulsion and levitation magnets that interact at a given point along a line the energy from these individual circuits is reoriented / reused individually and fed forward so that a discharge can be driven along a segment of the line. Thereby, all the energy is collected from propulsion and levitation circuits that interact in close temporal proximity or overlap, and the same benefits are achieved as would have been achieved in an integrated case. Each of the drive circuits for these propulsion and levitation circuits can, in this case as well, be configured to drive the discharge circuit independently instead of being integrated first. As disclosed in and incorporated by reference in the prior patent a conductive path along the line (along which a discharge is generated to deposit energy and move air) can be configured from a path that is slightly more conductive than the low-conductivity medium (e.g., concrete, or other potential low-conductivity line materials) in which the conductive path is incorporated The slightly preferentially conductive path can also be composed of "dotted lines" of conductive material, e.g., pieces of electrode material embedded in a low-conductivity line material. Similar to the flexibility provided by decomposing the emissions over time into a plurality of temporally distinct emissions that will be integrated into a single low-density tube, the discharge can further be composed of spatially distinct discharges This discharge can be integrated into one arcuate low-density tube. This spatial separation can be done, for example, between different pieces of electrode material, and different segments of this "dotted line" are energized independently. The spatial separation can also be done in the form of discharges that travel approximately the same length, but follow separate paths (this one variant is spatial The slightly preferentially conductive path can also be composed of "dotted lines" of conductive material, e.g., pieces of electrode material embedded in a low-conductivity line material. Similar to the flexibility provided by decomposing the emissions over time into a plurality of temporally distinct emissions that will be integrated into a single low-density tube, the discharge can further be composed of spatially distinct discharges This discharge can be integrated into one arcuate low-density tube. This spatial separation can be done, for example, between different pieces of electrode material, and different segments of this "dotted line" are energized independently. The spatial separation can also be done in the form of discharges that travel approximately the same length, but follow separate paths (this one variant is spatial This discharge can be integrated into one arcuate low-density tube. This spatial separation can be done, for example, between different pieces of electrode material, and different segments of this "dotted line" are energized independently. The spatial separation can also be done in the form of discharges that travel approximately the same length, but follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). The discharges can follow separate paths (this one variant is spatial separation). 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More realistically such separate paths are likely not ideal and do not necessarily have to be perfectly parallel to each other, and each path is slightly deflected to the side. If different paths are close enough in time and space to merge into an arch-shaped low-density tube, this flexibility in spatial and temporal frequencies can be further combined by depositing energy along the different paths at different times. In addition to accommodating significant natural variations, this flexibility reduces tolerances and allows existing circuits to be more fully utilized without adding unnecessary circuitry to combine energy from multiple feedlines (e.g., feedlines feeding multiple propulsion and / or levitation coils) or without recycling / harvesting energy from multiple propulsion and / or levitation coils. Another feature is that a small canopy can be placed on one or more preferred conductive paths of a low-conductivity line material to provide protection, especially from debris, weather, and environmental obstacles, e.g., paths (s) and discharges (s) especially from bird droppings. A non-harmful drainage channel can also be provided when opening the tube to prevent water from pooling due to rain, and the canopy can be mounted over the entire length of the line as further protection from the environment, the canopy having multiple layers perforated to minimize reflection in some cases, and a net or mesh can also be mounted around the line if wildlife exclusion is desired. Further operational features are, for example, those of a ground vehicle ​​​​​​​​​​​By dragging a light brush at the end, the track can be cleaned by the passing of the ground vehicle. The discharge itself also helps to eliminate any potential contamination.

[0188] For propulsion, the design of an electrically propelled high-speed ground vehicle (e.g., a maglev vehicle) can use a linear motor in which power is supplied to the windings of a guideway (i.e., an "active guideway"). When energy is supplied to the electromagnets for both propulsion and levitation purposes, the inductive energy stored in the loop / circuit must be dissipated. Typically, a great deal of effort is expended to minimize the arcing resulting from the dissipation of this energy due to the generation of high voltages after the train has passed. By nature, at this high voltage, a strong arc that has traditionally been difficult to mitigate is generated. In contrast, rather than dissipating this energy with circuit elements that dissipate the energy on a longer time scale, it can be productively utilized by depositing it in front of the ground vehicle and removing the air in front of the ground vehicle. Further, at high speeds, the propulsion energy required to propel the ground vehicle is equal to or greater than the energy required to push the gas out of the path of the ground vehicle. Therefore, the power and energy delivered to the inductive propulsion elements are already appropriately sized to deliver the pulsed electrical energy required to reduce the resistance of the ground vehicle (this available power, energy, and circuitry from the propulsion elements are augmented by that from any levitation elements). To convert the inductively stored electrical energy into a discharge suitable for reducing resistance and enhancing stability, it is inherent in the overall design of the ground vehicle and power delivery / conversion. a linear motor in which power is supplied to the windings of a guideway (i.e., an "active guideway") When energy is supplied to the electromagnets for both propulsion and levitation purposes, the inductive energy stored in the loop / circuit must be dissipated. Typically, a great deal of effort is expended to minimize the arcing resulting from the dissipation of this energy due to the generation of high voltages after the train has passed. By nature, at this high voltage, a strong arc that has traditionally been difficult to mitigate is generated. In contrast, rather than dissipating this energy with circuit elements that dissipate the energy on a longer time scale, it can be productively utilized by depositing it in front of the ground vehicle and removing the air in front of the ground vehicle. Further, at high speeds, the propulsion energy required to propel the ground vehicle is equal to or greater than the energy required to push the gas out of the path of the ground vehicle. Therefore, the power and energy delivered to the inductive propulsion elements are already appropriately sized to deliver the pulsed electrical energy required to reduce the resistance of the ground vehicle (this available power, energy, and circuitry from the propulsion elements are augmented by that from any levitation elements). To convert the inductively stored electrical energy into a discharge suitable for reducing resistance and enhancing stability, it is inherent in the overall design of the ground vehicle and power delivery / conversion. In contrast, rather than dissipating this energy with circuit elements that dissipate the energy on a longer time scale, it can be productively utilized by depositing it in front of the ground vehicle and removing the air in front of the ground vehicle. Further, at high speeds, the propulsion energy required to propel the ground vehicle is equal to or greater than the energy required to push the gas out of the path of the ground vehicle. Therefore, the power and energy delivered to the inductive propulsion elements are already appropriately sized to deliver the pulsed electrical energy required to reduce the resistance of the ground vehicle (this available power, energy, and circuitry from the propulsion elements are augmented by that from any levitation elements). To convert the inductively stored electrical energy into a discharge suitable for reducing resistance and enhancing stability, it is inherent in the overall design of the ground vehicle and power delivery / conversion. This available power, energy, and circuitry from the propulsion elements are augmented by that from any levitation elements. To convert the inductively stored electrical energy into a discharge suitable for reducing resistance and enhancing stability, it is inherent in the overall design of the ground vehicle and power delivery / conversion. To convert the inductively stored electrical energy into a discharge suitable for reducing resistance and enhancing stability, it is inherent in the overall design of the ground vehicle and power delivery / conversion. A specific circuit is required, and this circuit can be mounted on each induction magnet along the line, or can be included in the actual ground vehicle, thereby reducing costs. A hybrid approach can also be utilized, in which part of this discharge circuit is distributed along the line, and part of the discharge circuit is included in the ground vehicle. During normal operation, discharge occurs only in front of the ground vehicle. This can serve as an advantageous and natural safety mechanism. Regarding energy, at lower speeds, for example, from 100 m / s to 280 m / s, energy pulses are deposited in front of the ground vehicle in the form of discharges to provide a higher speed and stability about 50% to 300% of the magnitude of the propulsion pulses used to move the ground vehicle forward against friction and resistance. At higher speeds, for example, from 250 m / s to 600 m / s, energy pulses are deposited in front of the ground vehicle in the form of discharges to provide a higher speed and stability about 20% to 200% of the magnitude of the propulsion pulses used to move the ground vehicle forward against friction and resistance. At even higher speeds, for example, from 450 m / s to 1200 m / s, energy pulses are deposited in front of the ground vehicle in the form of discharges to provide a higher speed and stability about 15% to 150% of the magnitude of the propulsion pulses used to move the ground vehicle forward against friction and resistance. In one embodiment, the hardware along the line is expected to be standardized and can generate the same maximum energy propulsion (and levitation if necessary) pulses and discharge energy in front of the ground vehicle between the propulsion magnets. Considering this sufficient availability of power, a ground vehicle that provides higher speed and stability is expected to be standardized, and can generate the same maximum energy propulsion (and levitation if necessary) pulses and discharge energy in front of the ground vehicle between the propulsion magnets. Considering this sufficient availability of power, a ground vehicle that provides higher speed and stability is expected to be standardized, and can generate the same maximum energy propulsion (and levitation if necessary) pulses and discharge energy in front of the ground vehicle between the propulsion magnets. There will always be sufficient power present to deposit energy in the form of a discharge in front. Using this flexibility, the energy of these discharge pulses can be adjusted to optimize the efficiency of a ground vehicle and / or facilitate speeds that are normally impossible, and / or enhance the stability of a ground vehicle. These energies and energy ratios are adjusted based on the configuration of the ground vehicle and circuit, as well as its operating conditions.

[0189] A high-speed train benefits from the deposition of energy in front of it to reduce resistance and enhance its stability and inductivity, and does not need to be electrically propelled or magnetically levitated. Any high-speed ground vehicle can benefit from these dynamics. Electrically propelled vehicles, including magnetically levitated vehicles, are particularly suitable for adopting this technology. Regardless of the propulsion or buffering approach, aerodynamic forces serve to place the ground vehicle at the center of a low-density tube formed along the track, which helps to enhance the stability, controllability, and simplicity of the ground vehicle, as well as the speed at which the ground vehicle can move when the track deviates from a straight path.

[0190] When weaving a fabric on a loom, the weft thread (or filling or yarn) must be propelled by a certain method of passing it through the warp threads to manufacture the fabric. Although not limited, numerous methods including shuttle, rapier (single rigid, double rigid, double flexible, and double telescoping), projectile, air jet, and water jet are used to propel / insert the weft thread. In addition to more traditional single weft insertion (or single pick insertion), multi-phase weft insertion (or pick insertion) is also possible. is utilized. In all of these applications, one limiting factor of loom performance is the speed at which the weft can cross the warp. This speed, while not limited, tends to be restricted by a number o...

Claims

1. 1. A method for reducing resistance to a projectile in a barrel of a gun, comprising: and forcing air out of the barrel of the gun in front of the projectile, The product energy is electromagnetic and / or chemical energy disposed in front of the projectile. The method according to any one of claims 1 to 4,

2. When a round having 50% to 90% less driving charge than a conventional round is fired in the gun, Conventional bullets fired in the gun without depositing energy in front of the projectile.

10. The method of claim 1, achieving comparable projectile muzzle velocities.

3. The method of claim 1 , wherein the chemical energy comes from an ignited barrel-sweeping propellant.

4. The barrel sweep propellant deposits the motive energy that propels the projectile from the gun.

4. The method of claim 3, wherein the driving charge is in addition to the driving charge.

5. 4. The barrel sweeping propellant is an integral part of a round which contains the projectile and the driving charge. The method described.

6. The method of claim 5, wherein the round further comprises a piezoelectric element that ignites the barrel-sweeping propellant. 。

7. A round having an integral barrel-clearing charge and less driving charge than a conventional round is fired. When fired, the projectile is fired in the gun without depositing energy in front of the projectile.

6. The method of claim 5, wherein the projectile achieves a muzzle velocity comparable to that of a conventional bullet.

8. The method of claim 1 , wherein the electromagnetic energy results from an electrical discharge inside the gun.

9. The discharge takes the form of an electric arc between two insulated electrodes located adjacent the breech of the gun.

9. The method of claim 8, wherein

10. 10. The method of claim 8, wherein the discharge is in the form of a closed circuit entirely contained within the projectile.

11. The guns include small caliber guns, medium caliber guns, large caliber guns, breaching guns, machine guns, mortars, radar guns, etc.

2. The method of claim 1, wherein the weapon is a firearm, a handgun, or a small firearm.

12. the deposited energy is sufficient to expel the volume of air in the barrel, or is a multiple of the energy sufficient to expel the volume of air in the barrel. How to.

13. The method of claim 1 , further comprising mitigating acoustic detection.

14. The method of claim 1 , further comprising increasing the muzzle velocity of the projectile.

15. 10. The method of claim 1, further increasing the impact velocity or impact energy of the projectile. How to.

16. The method reduces acoustic signatures to minimize adverse effects on the hearing of nearby people. The method of claim 1 .

17. The method reduces acoustic signatures to minimize adverse effects on the hearing of nearby people. The method of claim 7,

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