An apparatus comprises multiple electrically conductive loops, an elongated tubular ferromagnetic shield, and an elongated tubular superconductive inner shield. The superconductive inner shield is positioned within the ferromagnetic shield. Each conductive loop includes (i) a thrust segment extending from a first end of the superconductive inner shield outside the ferromagnetic shield to a second end of the superconductive inner shield and (ii) a return segment passing through an interior passage of the superconductive inner shield from the second end of the superconductive inner shield to the first end of the superconductive inner shield. The conductive loops can be spatially arranged relative to a uniform external magnetic field so that interaction between the external magnetic field and electrical current flowing in the conductive loops results in asymmetric magnetic flux density around, and non-zero net force exerted on, the conductive loops.

A fuel less pneumatic and hydraulic lift system flight system provides the following systemic components. A chassis supporting an electric battery and a pressurized base hydraulic cylinder, a hydraulic fluid pumping assembly fluidly coupled to the pressurized base hydraulic cylinder; a lift mechanism assembly providing an attractive levitation plate mounted to the chassis; and a repulsive levitation plate mounted to a carriage, wherein the repulsive levitation plate is disposed in a magnetic pole repulsive alignment relative to the attractive levitation plate causing a magnetic lift effect to the chassis; and a plurality of propulsions jets mounted to the chassis, wherein the plurality of propulsion jets enabling motive functionality using hydraulic fluid propulsion and pneumatic pressure via the hydraulic fluid pumping assembly in conjunction with the magnetic lift effect.

A fuel less pneumatic and hydraulic lift system flight system provides the following systemic components. A chassis supporting an electric battery and a pressurized base hydraulic cylinder, a hydraulic fluid pumping assembly fluidly coupled to the pressurized base hydraulic cylinder; a lift mechanism assembly providing an attractive levitation plate mounted to the chassis; and a repulsive levitation plate mounted to a carriage, wherein the repulsive levitation plate is disposed in a magnetic pole repulsive alignment relative to the attractive levitation plate causing a magnetic lift effect to the chassis; and a plurality of propulsions jets mounted to the chassis, wherein the plurality of propulsion jets enabling motive functionality using hydraulic fluid propulsion and pneumatic pressure via the hydraulic fluid pumping assembly in conjunction with the magnetic lift effect.

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.

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.

A thruster assembly, including a switch connected to a power source, a thruster, a propellant tank for storing and pressurising a propellant, and a propellant channel for guiding the propellant to the thruster. The thruster includes a space for receiving the propellant from the propellant channel, an electrically controlled heating element, a thruster body having a first thermal expansion coefficient, a valve component having a second thermal expansion coefficient, which is different than the first thermal expansion coefficient, inside the thruster body, and a nozzle, wherein the valve component includes a sealing surface closing the nozzle in a first temperature, and the electrically controlled heating element in response to actuation of the switch heats said thruster to a second temperature where the thermal expansion of the thruster opens the nozzle.

A thruster assembly, including a switch connected to a power source, a thruster, a propellant tank for storing and pressurising a propellant, and a propellant channel for guiding the propellant to the thruster. The thruster includes a space for receiving the propellant from the propellant channel, an electrically controlled heating element, a thruster body having a first thermal expansion coefficient, a valve component having a second thermal expansion coefficient, which is different than the first thermal expansion coefficient, inside the thruster body, and a nozzle, wherein the valve component includes a sealing surface closing the nozzle in a first temperature, and the electrically controlled heating element in response to actuation of the switch heats said thruster to a second temperature where the thermal expansion of the thruster opens the nozzle.

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.

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 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.