85results about "Reactive propulsion thrust device" patented technology

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 spacecraft-borne propulsion device includes a propellant storage mechanism including a propellant storage container that stores a propellant in a vapor-liquid equilibrium state or a liquid phase, the propellant being ethanol or an aqueous ethanol solution; a propellant transport mechanism configured to supply, with an electric pump, the propellant under pressurization to a pressure exceeding 1 atm at room temperature; a gas heating mechanism including a heater including a separate heater for heating up connected via a check valve; a thruster head mechanism having a nozzle that generates a thrust with a heated gas; and a power supply mechanism including a storage battery for driving the electric pump and the heater for heating up. The propellant storage mechanism, the propellant transport mechanism, the gas heating mechanism, and the thruster head mechanism are connected in series.

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.

The present invention relates to a new form of air, land, underwater, or space propulsion, achieved by the use of suitable electromagnetic interactions. When using coils (1), with internal core (2) and support piece (3), subjected to current pulses with asymmetric current derivative and magnetic field, we obtain directional propulsion forces. This is possible due to a new electromagnetic propulsion mechanism that uses the conservation of total momentum where the sum of the mechanical moment with the moment of the magnetic field must always be conserved, resulting in a constant and null total sum of the two components, where the variation of the magnetic field moment will generate a corresponding change in the mechanical moment of the coil, thus generating propulsion forces. When magnetic fields with asymmetric derivative are produced in an external volume, they may also generate force fields.

Radiation shielding technologies for radioisotope battery-powered vehicles to protect computer systems and humans and increase the energy efficiency, mass efficiency, and duration capability of the vehicle during operation. A radioisotope power system includes a radioisotope power unit that emits a plurality of radiation particles. The radioisotope power system further includes a radiation shield configured to block a first radiation particle of the plurality of radiation particles. The radioisotope power system further includes a decoupling device configured to decouple the radiation shield from a vehicle. The radioisotope power unit can include one or more radioisotopes for power, propulsion, or both power and propulsion of the vehicle. The one or more radioisotopes can include an alpha emitting isotope, a beta emitting isotope, a gamma emitting isotope, or a combination thereof. The one or more radioisotopes can be for heat generation. The vehicle can be a spacecraft or an aircraft.

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°.

An apparatus comprised of positionally directable masses attached to a binding component that includes a coupling device for payload to reduce gravitational deviation of the apparatus' trajectory by alternatingly accelerating and retracting physically bound component masses in equal and opposite directions to the extents of their bindings, initially and optimally perpendicular to the gravitational field and perpendicular to the apparatus trajectory by using in built transduction componentry located within the masses or the binding componentry or both that utilises electromagnetic forces, forces generated by chemical reactions, or other applied or responsive motive force to positionally direct the bound directable masses.

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.

The present invention relates to a piezoelectric thruster comprising: - a set of identical piezoelectric elements by way of a battery (5) of polarised piezoelectric discs (2) alternately arranged relative to conductive electrodes (1), the piezoelectric discs and the electrodes (1) being bonded by an epoxy resin (3); - two parts, a smaller part (6) and a larger part (7) between which the batteries (5) are arranged by applying pressure, and the piezoelectric discs exhibiting a high quality factor Q and a high piezoelectric constant d33; - a power supply source (21) capable of providing an alternating current wave form, wherein the wave form exhibits two sinusoidal components with different frequencies. A piezoelectric thruster is thus obtained, exhibiting very low energy loss due to thermal effects, wherein maximum power is delivered to the piezoelectric material, the piezoelectric materials having a high mechanical excursion.

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.

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.

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 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.

An elliptical orbit thruster, which relates to the technical field of aerospace engines. The elliptical orbit thruster effectively solves the problem of the prior art not being suitable for manufacturing engines of unidentified flying objects, and also provides another method and line of thought that differ from those regarding rocket engines. The magnitude differences of momentum and acting force in opposite directions are produced by means of the conversion of acceleration, deceleration, momentum and angular momentum inside an object, such that a spacecraft can be pushed to continuously fly in the universe without the need to discharge substances.

The invention discloses a technical scheme and an implementation method of a space navigation propeller, namely a phased array quantum propeller, using a space-time field superconducting curve velocity principle, and belongs to the technical field of frontier space navigation. According to the invention, a brand-new microwave device technology, namely a phased array unidirectional oscillation microwave device technology, is adopted, so that a steady-state quantum magnetic field which is completely separated from a wave source (namely completely separated from a propulsion system) and independently exists in space and time can be synthesized in a far-field region; a steady-state quantum magnetic field which does not belong to any object (entity) and independently exists in space and time is manufactured around a moving superconductor to push the system to advance, and the superconductive curved speed refers to the speed of the superconductor in the steady-state quantum magnetic field which does not belong to any object.

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.

The present invention discloses an electromagnetic drive device for generating a unidirectional force and a method for doing so. The electromagnetic drive device comprises one or more cabin units, a power source, and a control unit. Each cabin unit comprises a housing, one or more magnetic flux control cores, one or more pairs of magnetic materials, and one or more electrically conductive elements. The one or more cabin units operationally form a vehicle structure in a predefined shape and are configured to generate the unidirectional force. The predefined shape is configured to provide distributed drive and control redundancy based on an arrangement of the one or more cabin units in defined geometries to form the vehicle structure.The control unit is configured to activate and deactivate one or more cabin units, regulate thrust levels, and change the vehicle's driving direction.

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.

A microwave generator is connected with a waveguide, a coil is installed in the waveguide, and the microwave generator is connected with the coil in the waveguide in series through a wire. During working, the microwave generator transmits microwaves into the waveguide tube through the antenna, when the microwaves reach the first coil, the wire transmits microwave electric signals to the first coil and generates a magnetic field, and due to the fact that the phases of the microwaves and the first coil are always the same, attraction force is generated. And when the magnetic field of the first coil is transmitted to the antenna of the microwave generator in the opposite direction, the phase difference between the waveform emitted by the microwave and the waveform returned by the first coil is pi / 2, and the interaction force generated between the antenna and the first coil has the same direction, so that unidirectional power is provided for the system. The method has the beneficial effects that the direction of the counter-acting force is changed by utilizing the time difference of microwave propagation, the defect that an aerospace engine depends on spraying substances is overcome, and a new scheme is provided for aerospace development.