The present invention discloses a pulsed electric field propulsion system for spacecraft. The system includes a capacitor stack comprising an array of supercapacitors. Solid-state electronic circuits generate high time-rate-of-change currents and pulsed 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 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.

A device is for giving a continuous, smooth thrust at a chosen direction of movement by exploiting a difference of initial impulses and final impulses given to rotational sources of magnetic field. Interactions between the magnetic field of the rotational sources and electromagnetic fields generated by stationary sources cause the impulses of various magnitudes and directions. The device is for creating a thrust at any chosen direction. The device does not require any motor. The device is only powered by electricity which may be supplied from solar panels, nuclear reactor, alkaline battery, and other sources.

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.

As is scientifically well know magnetic flux is a physical force (i.e. the Lorentz force and Ampere's force). The invention utilizes a plurality of electromagnetic and or plasma coils to create high pressure, high velocity magnetic flux directed through variable exhaust nozzles or a cone shaped electrical coil to create thrust for spacecraft.

A vapor jet system to continuously jet vapors while suppressing cavitation. One vapor jet system includes a liquid storage part for separately storing two or more kinds of mutually insoluble liquids; a jet orifice; and a jet control part. Jetting the vapors is from a state where pressure in the space storing the vapors in the liquid storage part is higher than the saturated vapor pressure in any of the two or more kinds of liquids. Alternatively, a vapor jet system can include a fluid storage part storing one kind of liquid and at least one kind of inactive gas having a composition different from the liquid; a similar jet orifice; and a similar jet control part. Jetting the vapors and inactive gas(es) is (are) from a state where pressure in a vapor storing space in the fluid storage part is higher than the saturated vapor pressure in the liquid.

A vapor jet system to continuously jet vapors while suppressing cavitation. One vapor jet system includes a liquid storage part for separately storing two or more kinds of mutually insoluble liquids; a jet orifice; and a jet control part. Jetting the vapors is from a state where pressure in the space storing the vapors in the liquid storage part is higher than the saturated vapor pressure in any of the two or more kinds of liquids. Alternatively, a vapor jet system can include a fluid storage part storing one kind of liquid and at least one kind of inactive gas having a composition different from the liquid; a similar jet orifice; and a similar jet control part. Jetting the vapors and inactive gas(es) is (are) from a state where pressure in a vapor storing space in the fluid storage part is higher than the saturated vapor pressure in the liquid.

A magnetic field propulsion unit (1) comprises a magnetic field generating device (10) with multiple conductive lines (100) which are configured to conduct a current so as to generate a magnetic field, a contact breaker arrangement (20) that is configured to individually transition each of the multiple conductive lines from a conductive state to a non-conductive state, an energy supply unit (30) configured to provide the magnetic field generating device (10) with electrical energy, and a control unit (40) configured to control the energy supply unit so that energy supply to each individual conductive line is controlled and to control the contact breaker arrangement. The multiple conductive lines (100) are arranged along a longitudinal axis (110). The control unit (40) is configured to supply a first conductive line (L1) with electrical energy so that a first magnetic field surrounding the first conductive line is generated, transition the first conductive line (L1) to a non-conductive state, supply a second conductive line (L2) with electrical energy so that a second magnetic field is generated.

Methods, structures, devices and systems are disclosed for fabrication of microtube engines using membrane template electrodeposition. Such nanomotors operate based on bubble-induced propulsion in biological fluids and salt-rich environments. In one aspect, fabricating microengines includes depositing a polymer layer on a membrane template, depositing a conductive metal layer on the polymer layer, and dissolving the membrane template to release the multilayer microtubes.

The present disclosure provides a thruster device. The device includes a force-generating element mounted to a housing. The element is configured to generate a thrust force for propelling the housing. The element including a first electrode connected to a first input terminal of a power source. A second electrode is spaced apart by a predetermined distance from the first electrode and connected to a second input terminal of the power source. The second electrode includes a second longitudinal axis oriented parallelly to a first longitudinal axis. A dielectric medium is disposed between the electrodes. Upon receiving field emission condition, charged particles available at the first electrode accelerate towards the second electrode for generating a thrust force along a direction of movement of the charged particles. The thrust force is generated when the predetermined distance between the electrodes is shorter than a Rindler horizon defined by the charged particles during acceleration.