47results about "Reactive propulsion thrust device" patented technology

An electron propulsion engine utilizes the acceleration of electrons to propel a spacecraft through space. The acceleration of the electrons in space emits electromagnetic radiation which can be used to propel the spacecraft. The radiation emission also decelerates the electrons, which allows the decelerated electrons to be recycled for reuse by the electron propulsion engine. The electron propulsion engine includes a first engine module, a second engine module, and an engine control system. The first engine module and the second engine module correspond to two mirror structures that form the electron propulsion engine. The engine control system facilitates the automatic control of the operation of the electron propulsion engine. The first engine module and the second engine module each includes a vacuum housing. The vacuum housing of each engine module is a D-shaped structure that facilitates the acceleration of the electrons and the resulting radiation emission to propel the spacecraft.

A magnetic field propulsion unit generates a drive force when being arranged in an external magnetic field. The magnetic field propulsion unit includes a support structure, a magnetic field generating device attached to the support structure and configured to generate a first magnetic field, an energy supply unit, and a control unit. The energy supply unit provides the magnetic field generating device with electrical energy. The control unit controls the energy supply unit so that the energy supply unit supplies energy to the magnetic field generating device. The control unit supplies varying current to the magnetic field generating device. The magnetic field generating device has a central axis and is arranged in the external magnetic field such that the central axis is inclined with respect to magnetic field lines of the external magnetic field at an angle different from 0°, 90°, 180°, and 270°.

The present disclosure relates to a system and method that produces thrust without a propellant or any physically moving parts. The disclosed method produces thrust by accelerating electrons between a multilayer capacitive stack and taking advantage of a conductive dampener that makes up a single thrust unit. For example, as power is applied to a first conductive layer separated by a second conductive layer by at least one dielectric layer, the electrons accelerating from the first layer produce a thrust whose direction is determined by the presence of a cover layer. Multiple middle conductive layers with corresponding dielectric layers can provide thrust scalability. Stacked thrust units with a minimum of a calculated distance between said units can also scale the thrust observed. Specialty materials with built in dielectrics such as anodized aluminum can further improve the thrust unit.

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

[Problem] Due to the law of action and reaction, it is not possible to achieve thrust in a closed space. [Solution] Shifting one of a pair of action and reaction objects that are on a straight line.

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 optical mining apparatus comprising: a light weight solar reflector; optics for controlling the delivery of concentrated sun light onto the surface of a target; and a temperature controlled gas enclosure that contains the target; wherein said solar reflector is oriented to reflect sun light onto said optics.

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.

A magnetic field propulsion unit (1) for generating a drive force when being arranged in an external magnetic field (100) is described. The magnetic field propulsion unit (1) includes a support structure (5), a magnetic field generating device (10) attached to the support structure (5) and configured to generate a first magnetic field (12), an energy supply unit (30), and a control unit (40). The energy supply unit (30) provides the magnetic field generating device (10) with electrical energy. The control unit (40) controls the energy supply unit (30) so that the energy supply unit (30) supplies energy to the magnetic field generating device (10). The control unit (40) supplies varying current to the magnetic field generating device (10). The magnetic field generating device (10) has a central axis (11) and is arranged in the external magnetic field (100) such that the central axis (11) is inclined with respect to magnetic field lines (101) of the external magnetic field (100) at an angle different from 0°, 90°, 180°, and 270°.

A vehicle for obtains linear momentum without throwing the mass from the vehicle in the space, comprising of a power source 13; a rigid base 1; a motor 3A and a motor 3B fitted in the rigid basel; a shaft 4A for the motor 3A, and a shaft 4B for the motor 3B; an adjuster 6A fixed with the shaft 4A, and an adjuster 6B fixed with the shaft 4B, the adjuster 6A is the first part of a rotor blade 5A, and the adjuster 6B is the first part of a rotor blade 5B, the second part of the rotor blade 5A is a blade 7A, and the second part of the rotor blade 5B is a blade 7B; a rigid body 10 fixed to the end of the rigid base 1; a thrust structure 8A, a thrust structure 8B, a thrust structure 8C, and a thrust structure 8D fixed in the rigid body 10, at the start the thrust structures 8A and 8D give linear motion to the blades 7A and 7B, respectively, after getting the linear motion, the blades 7A and 7B are travelling; an electromagnet 6AE and an electromagnet 6BE present on the outer surface of the adjusters 6A and 6B, respectively, after travelling, the blades 7A and 7B stick with the electromagnets 6AE and 6BE, respectively, now the blade 7A and the adjuster 6A joined via the electromagnet 6AE, and the blade 7B and the adjuster 6B joined via the electromagnet 6BE, after joining, the blades 7A and 7B start the circular motion, wherein the circular motion of the blades 7A and 7B generates centripetal reaction force.

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

A thruster operable for use in a satellite may include a rotating detonation combustion chamber; a fuel source operably connected to the rotating detonation combustion chamber, the fuel source comprising two chemical propellants, wherein each of the two chemical propellants comprises a liquid with a vapor pressure sufficient to self-pressurize each of the two chemical propellants; and a valve system configured to control a feed of each of the two chemical propellants to the rotating detonation combustion chamber.

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.