The force cell provides propellant-less propulsion for linear thrust applications and fuel-less torque for rotary applications. Linear thrust applications include propulsion for aircraft, spacecraft, flying cars, construction equipment for use in low and zero gravity environments, stabilization for ultra high buildings and realization of ultra long unsupported spans. Rotary torque applications include engines to drive electric generators of all sizesfrom mobile phone size to power station size. Force cells use radiation pressure originating from the zero-point fields in the vacuum of spacethe force in the Casimir effect, to produce a macroscopic external force through use of a multiplicity of microscopic Casimir cavities consisting of wedge shaped non-charged conducting plates attached to a matrix of non-conducting material. Force cells arranged in balanced pairs can produce modulated external thrust. Force cells arranged circularly can produce modulated torque.

An electric propulsion simulator console (EPSC) 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 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 adapted to receive propulsion unit control signals from a spacecraft under test and a spacecraft propulsion unit positioner simulator 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 is also provided and can display a simulated state of propulsion unit fuel valves responsive to control signals received from the spacecraft under test.

The present invention discloses an electric field propulsion system for spacecraft. The system includes a capacitor stack comprising an array of supercapacitors. Solid-state electronic circuits generate modulated currents and electric fields in pulse coils. The pulse coils direct the electric fields onto separated electric charges stored in the capacitor stack. The resulting unidirectional Lorentz Forces thereby generate thrust without reaction mass. Reaction momentum is carried away by Poynting Vector fields in conformity with the currently understood principles of electrodynamics. The design is scalable down to micro-chip sized thrusters.

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.

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.

A nuclear thermal propulsion rocket engine. A source of fissionable material such as plutonium is provided utilizing a carrier fluid having neutron moderating constituents, such as hydrogen and/or carbon, therein. A carrier fluid may be methane, or ethane, or a combination thereof. A neutron source is provided, such as from a neutron beam generator. Reactor design geometry provides containment of fissionable material in the reactor during acceleration. Collisions occur between neutrons and fissionable material injected by way of the carrier fluid. Impact of neutrons on fissionable material results in a nuclear fission in sub-critical mass reaction conditions in the reactor, resulting in release of heat energy to fluids provided to the reactor. The reactor is sized and shaped to receive the reactants and expandable fluids such as hydrogen, and to confine heated and pressurized gases for discharge out through a throat, into a rocket engine expansion nozzle for propulsive discharge, The design provides a rocket engine with a specific impulse in the range of from about eight hundred (800) seconds to about twenty five hundred (2500) seconds.

A nuclear thermal propulsion rocket engine. A source of fissionable material is provided in a bed of fuel pebbles located in a reactor. A fluid having neutron moderating constituents, such as hydrogen and/or carbon, therein, is provided, which may be in the form of methane, or ethane, or a combination thereof, or may further include various isotopes of hydrogen. An external neutron source is provided using a neutron beam generator. Reactor design geometry provides containment of fissionable material, and for any byproducts of fission reactions, in the reactor during acceleration of the rocket. Impact of neutrons on fissionable material results in a nuclear fission reaction conditions in the reactor, resulting in release of heat energy to fluids provided to the reactor. The reactor is sized and shaped to contain fuel pebbles containing fissionable material, and to confine expandable fluids as they remove heat from fuel pebbles. the heated fluids are discharged out through a throat, into a rocket engine expansion nozzle for propulsive discharge, The design provides a rocket engine with a specific impulse in the range of from about eight hundred (800) seconds to about twenty five hundred (2500) seconds.

There is disclosed a vehicle (100) and a method for propelling the vehicle comprising a propulsion arrangement (102). The propulsion arrangement (102) includes a chamber arrangement (104) that is configured to store antimatter therein by using magnetic and/or electrostatic fields. The chamber arrangement (104) and a centre of gravity (106) of the vehicle are positioned at a relative distance from each other to form a matter-antimatter dipole when in operation. The matter-antimatter dipole provides a propulsion force to the vehicle (100). Optionally, the vehicle (100) is a space vehicle (namely a spacecraft, a satellite or similar).

There is disclosed a vehicle (100) and a method for propelling the vehicle comprising a propulsion arrangement (102). The propulsion arrangement (102) includes a chamber arrangement (104) that is configured to store antimatter therein by using magnetic and/or electrostatic fields. The chamber arrangement (104) and a centre of gravity (106) of the vehicle are positioned at a relative distance from each other to form a matter-antimatter dipole when in operation. The matter-antimatter dipole provides a propulsion force to the vehicle (100). Optionally, the vehicle (100) is a space vehicle (namely a spacecraft, a satellite or similar).

A filtering apparatus formed by a plurality of channel systems. Each of the channel systems include an inlet port formed on an inlet side of the plate; no more than one outlet port formed on an outlet side of the plate; and a channel formed in the plate, the channel coupled to the inlet port and to the outlet port, wherein the ratio of the product of the capture area of the inlet ports of a channel system with the first transmissivity associated with the inlet ports to the product of the capture area of the outlet ports of a channel system with the second transmissivity associated with the outlet ports is greater than one. The channel system is configured to interact with objects of interest on a scale which is smaller than a value several orders of magnitude larger than the mean free path of an object of interest. Some plate embodiments are configured to interact with particles, such as air molecules, water molecules, or aerosols. Other plate embodiments are configured to interact with waves or wavelike particles, such as electrons, photons, phonons or acoustic waves.