A magnetic field propulsion unit includes a magnetic field generating device with multiple conductive lines conduct a current to generate a magnetic field; a contact breaker arrangement individually transitions each of the multiple conductive lines from a conductive state to a non-conductive state; an energy supply unit provides the magnetic field generating device with electrical energy; and a control unit controls the energy supply unit so that energy supply to each individual conductive line is controlled and control the contact breaker arrangement. The multiple conductive lines are arranged along a longitudinal axis. The control unit supplies a first conductive line with electrical energy so that a first magnetic field surrounding the first conductive line is generated, transitions the first conductive line to a non-conductive state, and supplies a second conductive line with electrical energy so that a second magnetic field is generated.

A reverse directional thrust device by a bidirectional translative movement is provided. The reverse directional thrust device is a thruster, formed by a drive motor, a magnetic reversing mechanism, and a system within a hermetic frame. The system allows a thrust to forward a sense of direction and to reverse the thrust towards an opposite sense of direction, and starting from an expulsion of compressed air, from an interaction with a magnetic field allowing the bidirectional translative movements of components rotary, wherein two translating impulse discs perforated with curved holes and fixed to a threaded axis of rotation, and a toothed disc interposed between the two translating impulse discs. The drive motor and the magnetic reversing mechanism do not fall within a scope of the reverse directional thrust device.

A reverse directional thrust device by a bidirectional translative movement is provided. The reverse directional thrust device is a thruster, formed by a drive motor, a magnetic reversing mechanism, and a system within a hermetic frame. The system allows a thrust to forward a sense of direction and to reverse the thrust towards an opposite sense of direction, and starting from an expulsion of compressed air, from an interaction with a magnetic field allowing the bidirectional translative movements of components rotary, wherein two translating impulse discs perforated with curved holes and fixed to a threaded axis of rotation, and a toothed disc interposed between the two translating impulse discs. The drive motor and the magnetic reversing mechanism do not fall within a scope of the reverse directional thrust device.

A transportation network for providing propellant in space can include optical mining vehicles that concentrate solar energy to spall captured asteroids, capture released volatiles, and store them in reservoirs as propellants. The network can also have orbital transfer vehicles that use solar thermal rocket modules that focus solar energy on heat exchangers to force propellant through nozzles, as well as separable aeromaneuvering tanker modules with reusable heatshields and storage tanks. The network can have propellant depots positioned between Earth and a transport destination. The depots can mechanically couple to accept propellant delivery and to supply it to visiting space vehicles.

A vehicle including a sealed container, a propulsion system with an intake and an exhaust affixed to an interior of the sealed container, an exhaust stream emitted from the exhaust, a thrust corridor within the sealed configured to channel the exhaust stream, and a return corridor configured to channel an intake stream into the intake of the propulsion system wherein the exhaust stream transforms into the intake stream after traveling a sufficient distance within the sealed container and the exhaust stream and intake stream generate a pressure differential within the sealed container wherein the pressure differential is sufficient to result in a movement of the vehicle relative to the vehicle's surroundings.

An apparatus that is capable of propelling a gas includes a first layer and a second layer arranged in a stack, mechanism for heating and/or cooling the first layer and the second layer to form a hot layer and a cold layer, and a through hole in the stack. A surface of both the hot layer and the cold layer is exposed in an interior of the through hole. The mechanism for heating and/or cooling the first and second layers controls the hot layer to be hotter than an ambient temperature of the gas, and the cold layer to be colder than the ambient temperature of the gas.

A propulsion apparatus using sound radiation force according to an exemplary embodiment of the present invention includes: an ultrasound generation unit which is installed at one side of an object to be operated, generates ultrasound, and provides propulsive force to the object to be operated by using sound radiation force of the ultrasound; and an ultrasound control unit which is coupled to one side of the ultrasound generation unit, and increases propulsive force to be provided to the object to be operated by controlling intensity of the ultrasound generated by the ultrasound generation unit.

A propulsion apparatus using sound radiation force according to an exemplary embodiment of the present invention includes: an ultrasound generation unit which is installed at one side of an object to be operated, generates ultrasound, and provides propulsive force to the object to be operated by using sound radiation force of the ultrasound; and an ultrasound control unit which is coupled to one side of the ultrasound generation unit, and increases propulsive force to be provided to the object to be operated by controlling intensity of the ultrasound generated by the ultrasound generation unit.

A thermal control system may transfer energy (directly or after a delay) to a thrusting device that can be used to slow a reentry vehicle entering a gaseous atmosphere from orbit. The thermal control system may mitigate the heating of the vehicle by transferring heat generated by the viscous interaction between the vehicle and high-altitude portions of a planetary atmosphere to a working fluid. This working fluid may then be routed through and/or ejected through one or more nozzles aligned to produce thrust in a direction that opposes the forward motion of this vehicle. This counter thrust may help to slow the reentry vehicle and reduce the amount of kinetic energy that can be converted into thermal energy. The working fluid may also be stored to use for propulsion after the reentry vehicle slows below hypersonic velocities.

A control system for controlling the operation of a plurality of micro thrusters arranged in a plurality of parallel horizontal rows and a plurality of parallel vertical columns, the control system requires a power source, a first plurality of power lines connected to the power source and coupled to at least one micro thruster of the plurality of micro thrusters in a horizontal row of the plurality of parallel horizontal rows, a second plurality of power lines connected to the power source and coupled to at least one micro thruster of the plurality of micro thrusters in a vertical column of the plurality of parallel vertical columns, and a control unit coupled to the power source to control activation of the first plurality of power lines and activation of the second plurality of power lines.