32results about "Reactive propulsion thrust device" patented technology

ThermaSat™ propulsion system uses water as a safe and non-explosive propellant, and which is unpressurized at liftoff. Utilizing solar thermal propulsion, the compact and efficient capacitor heats water to steam to produce high thrust and total impulse. The advanced optical system allows for the thermal capacitor to charge through solar power alone with no protruding concentrators or power draw from the main bus. Additional solar panels, body mounted to the ThermaSat, provide auxiliary heating of the thermal capacitor when not directly incident to sunlight to promote non-sun pointing operations.

An automotive generator electric vehicle platform. The platform includes an on-board generator operable to be driven by hydraulic pressure and pneumatic pressure to provide power production on-demand against conditions causing deceleration or being affected by resistance. The hydraulic pressure is applied by a hydraulic impeller operably associated with the on-board generator. The pneumatic pressure is applied by a pneumatic impeller operably associated with a pulley drive system configured with a reverse skew bevel gear tilt ratio.

The present disclosure relates to systems, devices, and methods for spacecraft propulsion. In an embodiment, the present disclosure relates to an apparatus comprising a heat exchanger body defining a plurality of propellant channels configured to contain a propellant, a central cavity configured to contain a working fluid and fluidically connected to a plurality of working fluid channels that extend along a radial dimension of the apparatus, and a nozzle fluidically connected to the plurality of propellant channels and configured to expel the propellant.

A system can produce localized spacetime distortions, gravitational waves, sudden transitions in the index of refraction and optical path length changes via high-energy plasma formation. The system includes a high-energy spark-gap arrangement, where an electrical discharge between tungsten tips produces extremely high energy densities in a localized region. The system is tunable and can be driven by either constant or time-varying voltage sources, allowing for different distortion profiles and electromagnetic emission patterns. The system can operate in various environments, including air, inert gases such as helium, and even in vacuum conditions. Multiple spark-gap assemblies can be arranged to create customized distortion shapes and enhanced field effects.

To integrate a large number of propulsion force generating devices accompanied by an air current as reaction in a propulsion force direction while avoiding the air current.SOLUTION: In one embodiment of the present invention, a centrifugal force is applied to the air flow in a direction perpendicular to the direction of the propulsive force, and the path of the air flow is controlled so that the air flow does not hit other components of the stack. As a propulsive force generating device, there is a technique for obtaining a propulsive force by breaking the balance of atmospheric pressure in the device by diffraction of gas molecules derived from the wave nature of matter waves based on the quantum theory. Since this technology is in the field of fine technology including nano-technology, the device size is small, and it is necessary to integrate a large number of devices in order to obtain a practical driving force. A practical propulsion force can be obtained by the accumulation method of the present invention.SELECTED DRAWING: Figure 18

A method of generating energy, comprising the steps of providing core-shell type thermite particles and burning a dispersed group of the core-shell type thermite particles to generate heat. The combustion of the core-shell type thermite particles can proceed according to the combustion modes of various core-shell type thermites.

This invention discloses a pendulum swashplate engine, relating to the field of aerospace engine technology. The recoil principle of rockets is only one method of generating thrust, not the only one; any force that can move an object can be called "thrust." The idea of ​​this invention is to use a gyroscope rotor composed of a base (15) and a pendulum (3). By controlling the angle between the pendulum (3) and the rotation plane of the base (15), the gyroscope stability of the gyroscope rotor composed of the base (15) and the pendulum (3) can be controlled, thereby controlling the required torque. Because, under the premise of a fixed rotation speed, torque is proportional to excitation force, the magnitude of excitation force can be controlled by controlling the magnitude of torque. The direction of excitation force can be controlled by controlling the position of the angle between the pendulum (3) and the rotation plane of the base (15), ultimately generating an excitation force or thrust with constantly changing direction and magnitude to propel the satellite in space.

An automotive electrical generator electric vehicle platform. The platform includes an on-board electricity generator operative to be motivated by a hydraulic pressure and a pneumatic pressure to provide on-demand baug resistant electricity production. The hydraulic pressure is imparted by a hydraulic impeller operatively associated with the on-board electricity generator. The pneumatic pressure is imparted by a pneumatic impeller operatively associated with a pulley drive system configured with a counter tilt gear incline ratio.

Radioisotope power system and propulsion system technologies to increase the energy efficiency, mass efficiency, and duration capability of a vehicle during operation. A radioisotope power system includes a radioisotope power unit that emits a plurality of radiation particles and is configured to directly or indirectly provide power, propulsion, or both power and propulsion of a vehicle. The radioisotope power system can further include a thermoelectric generator coupled to the radioisotope power unit and configured for coupling to at least one thruster. The radioisotope power system can further include an optional radiation shield configured to block a first radiation particle of the plurality of radiation particles. The radioisotope power unit can include one or more radioisotopes. The one or more radioisotopes can include an alpha emitting isotope, a beta emitting isotope, a gamma emitting isotope, or a combination thereof.

The invention discloses a radioactive isotope micro-thruster based on directional radiation. The thruster comprises a radioactive isotope source, a particle orientation system, a radiation shielding shell and a power management system, the radioactive isotope source decays to generate charged particles, the particle orientation system restrains the particle emission direction in the dominant direction, the radiation shielding shell shields harmful radiation, and the power management system supplies power to the orientation system. During working, the power management system is activated and supplies power, the particle orientation system establishes a constraint field, particles generated by isotope source decay are directionally jetted under the action of the constraint field, and the thruster obtains reverse continuous micro-cattle magnitude thrust according to momentum conservation. The invention solves the problems of difficult thrust control, working medium demand, short service life and the like of the traditional propulsion technology, is suitable for tasks of deep space exploration, satellite drag-free control and the like, and has the advantages of stable thrust, long service life, no working medium and high reliability.

A device consisting of a large capacitor connected to an extremely high voltage alternating power supply. By properly adjusting the frequency of the power supply, a stationary radio wave can be produced in the space between the capacitor plates that creates a gravitational field and is capable of causing a gravitational force to act on any mass placed in the space between the capacitor plates. Thus, a mass placed in the space between the capacitor plates will be lifted gravitationally. Multiple such capacitors can be connected to form arrays in the three directions of space, which allows movement of masses in the three directions of space.

Device for generating thrust, comprising: a) Means of generating a variable electromagnetic field pulse density within a carrier system; b) a control unit configured to effect a temporally asymmetric modulation of the field pulse density in order to emit a directed pulse flux into a localized ambient field; c) wherein the control unit is configured such that the asymmetry of the modulation cycle generates a net reaction force on the device.

The invention discloses a spacecraft propulsion system utilizing magnetic repulsion forces for efficient thrust generation. The system comprises a rotating electromagnet configured to generate a repulsive magnetic field upon activation. A stationary solenoid positioned within the housing interacts with the rotating electromagnet, generating an opposing magnetic force. A tether mechanism connects the rotating electromagnet to a rotating member, with an adjustable angle relative to the stationary solenoid. A magnetic bearing supports the rotation of the member for minimal friction. The core functionality involves generating a non-uniform magnetic field through the rotating electromagnet. The electromagnet is activated as it approaches the stationary solenoid, creating a repulsive force. This force is deactivated before full engagement and channeled through the angled tether mechanism to produce a net forward thrust for the spacecraft. The control system manages the activation sequence, timing, and tether angle adjustments to optimize propulsion efficiency. This invention offers a novel approach to spacecraft propulsion using magnetic forces, potentially lower to more efficient and controllable spacecraft maneuvering compared to traditional methods.

An autonomous mobility sensing device (10) comprising: a solid substrate (11); a first layer (12) disposed on one surface (11a) of the solid substrate (11); and a second layer (14) that covers the one surface (11a) of the solid substrate (11) and the first layer (12) and is bonded to a region on the one surface (11a) of the solid substrate (11) via an adhesive layer (13), wherein the region excludes the first layer (12) and the peripheral edge thereof, the first layer (12) is a catalyst, the second layer (14) is a permeable film, a space (15) between the solid substrate (11) and the first layer (12), and the second layer (14) is a product storage layer, and the adhesive layer (13) has an adhesive interface (16) that bonds the solid substrate (11) and the second layer (14), and a non-adhesive interface (17) that does not bond the solid substrate (11) and the second layer 12(14).

To provide an anti-gravity propulsion device which gets operation by invalidating a part of centrifugal gravity force.SOLUTION: An anti-gravity propulsion device is made by applying such a principle that proximity magnets which face each other with the same magnetic poles repel each other and push back. Therein, in order to provide a stable biased centrifugal force from a magnetic centrifugal body (3) group which circulates while pushing against a wall surface of an inner circumference, the orbit circle is turned to such a shape of short elliptic shape (R1, D3) that a lower half circle thereof is shortened a little and, further, by obscuring biased centrifugal gravity force proceeding upward generated by offsetting each other with a force of repulsion magnetic force (5) installed on the surrounding in order to make the strong centrifugal gravity force quantity toward the lower side which is generated on the magnetic centrifugal body ineffective.SELECTED DRAWING: Figure 10

An electric propulsion simulator console (EPSC) (200) which electronically simulates an electric propulsion assembly of a spacecraft as well as propulsion fuel control components and positioning components of the spacecraft. The EPSC (200) simulates a spacecraft thruster electrical interface can test four thruster interfaces simultaneously and continuously. The simulator additionally facilitates the testing of spacecraft fault detection, isolation, and recovery by simulating failed magnet circuits, open anode paths, and flameout conditions. The EPSC includes an electrical propulsion unit load simulator (210) adapted to receive propulsion unit control signals from a spacecraft under test and a spacecraft propulsion unit positioner simulator (215) the simulator adapted to display a simulated state of three axes of movement for at least one propulsion unit positioner responsive to positioning signals received from the spacecraft under test. A propulsion unit fuel valve simulator (215) is also provided and can display a simulated state of propulsion unit fuel valves responsive to control signals received from the spacecraft under test.

An apparatus 100 for generating a propulsion force comprises: a laser arrangement 11; an optical device 120 comprising an optical region; and a coupling arrangement 140A comprising coils of optical fi

An aerospace electric motor using pulsed electromagnetic waves is a 100% electric motor that allows thrust to be generated even in the vacuum of space using high-voltage generators to charge low-inductance capacitors that are subsequently discharged onto field pulse emitters, whether these are electric, magnetic, or electromagnetic field pulse emitters, using electronic synchronisation and control circuits to generate high-power field pulses lasting fractions of a nanosecond, thereby achieving sustained thrust without the use of fuel or propellant. This technology is based on the concept that a force field can alter the dynamic state of a susceptible body without involving a momentum balance.

A space propulsion system can serve miniaturised satellites, but can be scaled easily, and includes: a combustion chamber implemented by a cylindrical container having cylindrical walls, a first end provided with at least an injection duct for a combustion agent, a fuel and / or a mixture thereof, for the injection according to a direction tangential to the cylindrical walls so as to induce a helical combustion path in the combustion chamber, a possible additional perpendicular injection duct for a fuel or a combustion agent, and an opposite end provided with a discharge duct arranged according to a direction tangential to the cylindrical walls so as to receive and direct the helical path, wherein the cylindrical walls in case have a deposition of catalytic material inside thereof, for accelerating the combustion reaction; and a supersonic nozzle, connected to the discharge duct for discharging the combustion products in the combustion chamber.

An electric heating system for heating a fluid stream, the system comprising: a housing having an inlet for a fluid stream to be heated by the electric heating system and an outlet for a fluid stream heated by the electric heating system; and a resistance heater mounted within the housing, the resistance heater comprising: a fluid input and a fluid output fluidly coupled to the inlet and outlet, respectively; a plurality of annular walls constructed from an electrically conductive material, the walls nested to define a plurality of annular flow channels arranged concentrically in series about a longitudinal axis, the walls extending between first and second opposite ends of the resistance heater spaced apart from one another along the longitudinal axis; and first and second electrical terminals for connecting to a source of electrical energy to heat the walls of the resistance heater, the first and second electrical terminals electrically connected to respective first and second walls comprising an outer pair of walls adjacent to one another and positioned radially outward of the resistance heater. The plurality of annular walls are mechanically connected to one another, whereby adjacent flow channels have opposite fluid flow directions and are connected at adjacent ends of each channel to define an alternating serpentine flow path, the serpentine flow path having an input end at a fluid input and an output end at a fluid output, the input end and output end being located at radially outer and inner positions, respectively, relative to the longitudinal axis. The plurality of annular walls are electrically connected to one another to define a continuous conductive path extending between first and second electrical terminals, the conductive path having a first portion extending from the first wall to a center of the resistive heater and a second portion extending from the center of the resistive heater to the second wall. A method of generating a high temperature fluid flow using an electrical heating system is also disclosed.

An electric thrust-generating device comprises a cathode (2) and an anode (3) which are substantially planar, arranged substantially parallel and spaced from each other, with an interposed material or a dielectric medium (4) therebetween, the device being configured for connection to a voltage generator (5), for applying a voltage between the cathode (2) and the anode (3), and thereby determine a passage of electrons (e-) from the cathode (2) to the anode (3). At least the cathode (2) is micro- or nano-structured at the surface thereof facing the anode (3), in particular for the formation of aggregates of electrons (e-).

The present disclosure relates to systems, devices, and methods for spacecraft propulsion. In an embodiment, the present disclosure relates to an apparatus comprising a heat exchanger body defining a plurality of propellant channels configured to contain a propellant, a central cavity configured to contain a working fluid and fluidically connected to a plurality of working fluid channels that extend along a radial dimension of the apparatus, and a nozzle fluidically connected to the plurality of propellant channels and configured to expel the propellant.

[Problem] To provide: a multimode propulsion device that ensures high safety and can be configured with a relatively simple structure; and a flying object. [Solution] A propellant tank 11 stores a propellant 11a containing at least one of nitrous oxide, hydrogen peroxide solution, and water. A thruster group 12 has a plurality of kinds of thrusters selected from a hybrid thruster 21, a catalyst thruster 22, a cold gas thruster 23, a resistojet thruster 24, and a plasma thruster 25. The thrusters of the thruster group 12 are connected to the propellant tank 11 so that the propellant 11a is supplied from the propellant tank 11, and are provided so as to be able to propel the flying object by using the propellant 11a supplied from the propellant tank 11.

The invention relates to a propulsion system comprising an engine having a pair of parallel longitudinal tubes (100), each longitudinal tube having a first end (10) and a second end (11), and delimiting an internal volume (12) filled with a fluid. Each longitudinal tube (100) comprises: a projectile (200), configured to move longitudinally within the internal volume, fixedly attached to a propeller (201); a mechanism for launching the projectile into the internal volume (12) from the first end, the propeller (201) being arranged to transform a translational motion of the projectile (200) into a rotational motion; a device for braking the rotation of the projectile (200) within the internal volume (12), located at the second end; a device for returning the projectile (200) to the first end; and a heat dissipation device, the propellers of the longitudinal tubes being counter-rotating.Figure for the abridged version: Fig. 1.

The invention relates to a piezoelectric thruster comprising:-a set of identical piezoelectric elements in the form of a stack (5) of piezoelectric disks (2) polarized in an alternating arrangement with respect to an electrically conductive electrode (1), the piezoelectric disks and the electrode (1) being joined together by means of an epoxy resin (3); -two parts, a smaller part (6) and a larger part (7), between which the stack (5) is arranged in a pressure-applied manner, and which exhibit a high quality factor Q and a high piezoelectric constant d33; -a power source (21) capable of providing an alternating current waveform, wherein the waveform exhibits two sinusoidal components of different frequencies. As a result, a piezoelectric thruster exhibiting extremely low energy loss due to the thermal effect is obtained in which the power transferred to the piezoelectric material is maximum and the piezoelectric material has a large mechanical offset.

According to various implementations of the invention, an electric propulsion engine includes: an engine housing forming an outer stator chamber and an inner rotor chamber, the outer stator chamber surrounding and concentric with the inner rotor chamber, the inner rotor chamber having an intake opening and an exhaust opening; an electromagnetic stator configured within the outer stator chamber; a plurality of rotors disposed within the inner rotor chamber along a central axis of the inner rotor chamber, each of the plurality of rotors having a plurality of rotor blades configured to rotate around the central axis of the inner rotor chamber thereby compressing a fluid as the fluid passes from the intake opening of the inner rotor chamber toward the exhaust opening of the inner rotor chamber, and each of the plurality of rotor blades having a magnetic rotor blade edge responsive to the electromagnetic stator.

A system can produce localized spacetime distortions, gravitational waves, sudden transitions in the index of refraction and optical path length changes via high-energy plasma formation. The system includes a high-energy spark-gap arrangement, where an electrical discharge between tungsten tips produces extremely high energy densities in a localized region. The system is tunable and can be driven by either constant or time-varying voltage sources, allowing for different distortion profiles and electromagnetic emission patterns. The system can operate in various environments, including air, inert gases such as helium, and even in vacuum conditions. Multiple spark-gap assemblies can be arranged to create customized distortion shapes and enhanced field effects.

Omnivorous solar thermal thrusters and adjustable cooling structures are disclosed. In one aspect, a solar thermal rocket engine includes a solar thermal thruster configured to receive solar energy and one or more propellants, and heat the one or more propellants using the solar energy to generate thrust. The solar thermal thruster is further configured to use a plurality of different propellant types, either singly or in combination simultaneously. The solar thermal thruster is further configured to use the one or more propellants in both liquid and gaseous states. Related structures can include valves and variable-geometry cooling channels in thermal contact with a thruster wall.

A shock-wave propulsion system for rectilinear motion moves space objects in zero gravity. The shock-wave propulsion system comprises: a liquid-propellant supply system (3) with control-operated valves connected to at least two hollow pipes (2) near their plugged ends; in-pipe heaters (4) that generate high-pressure gas, producing a transient uncompensated impulse; shock-wave dampers (5) mounted on the opposite open pipe (2) ends; a liquefaction system (6) coupled to the open ends to condense the gas; and a return -pumping circuit (7) that feeds the condensed liquid as a propellant back to the liquid-propellant supply system (3). In addition, the above valves controlled by the control system (8) are designed to start each subsequent pipe (2) so that its filling with liquid working fluid begins simultaneously with shutting off the previous pipe (2) after the wave reaches its shock-wave damper (5), creating repeated thrust cycles.