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 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.

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 system for propelling craft which is applicable in any environment. It employs an alternating magnetic field supplied by a coil. A parallel plate capacitor is situated so that the flux of the magnetic field flows between the plates of the capacitor. The capacitor is charged and discharged in synchronization with the alternating magnetic field. The changing magnetic field creates an electric field that applies a force to the charge in the plates which is then transferred to the body of the device. Any induced reactive electric force on the coil affects equally the protons and electrons in the wires of the coil creating the magnetic field, thus the force is non-reactive. At the same time, the changing electric field in the capacitor creates a magnetic field. The current in the coils and/or the surface current in the ferromagnetic material (if present) experiences a force from the magnetic field. The magnetic field created by these currents, however, has no free charge between the plates of the capacitor with which to react, thus this force is also non-reactive. The two forces are in opposite directions, but are not the same magnitude, thus the device is propelled in a single direction.

A system for propelling craft which is applicable in any environment. It employs an alternating magnetic field supplied by a coil. A parallel plate capacitor is situated so that the flux of the magnetic field flows between the plates of the capacitor. The capacitor is charged and discharged in synchronization with the alternating magnetic field. The changing magnetic field creates an electric field that applies a force to the charge in the plates which is then transferred to the body of the device. Any induced reactive electric force on the coil affects equally the protons and electrons in the wires of the coil creating the magnetic field, thus the force is non-reactive. At the same time, the changing electric field in the capacitor creates a magnetic field. The current in the coils and/or the surface current in the ferromagnetic material (if present) experiences a force from the magnetic field. The magnetic field created by these currents, however, has no free charge between the plates of the capacitor with which to react, thus this force is also non-reactive. The two forces are in opposite directions, but are not the same magnitude, thus the device is propelled in a single direction.

Thrusting systems and vehicles are disclosed. One thrusting system includes a signal generator and a waveguide. The signal generator is configured to generate an electromagnetic wave. The waveguide is coupled to the signal generator to receive the electromagnetic wave such that at least a portion of electric and magnetic components of the electromagnetic wave extend in a direction transverse to a wave axis of the electromagnetic wave. The waveguide includes a dielectric material positioned to extend in a direction of the wave axis along a portion of the waveguide. An interaction between the electromagnetic wave and the waveguide induces a net force on the waveguide. One vehicle includes a thrusting system substantially as described above.

Thrusting systems and vehicles are disclosed. One thrusting system includes a signal generator and a waveguide. The signal generator is configured to generate an electromagnetic wave. The waveguide is coupled to the signal generator to receive the electromagnetic wave such that at least a portion of electric and magnetic components of the electromagnetic wave extend in a direction transverse to a wave axis of the electromagnetic wave. The waveguide includes a dielectric material positioned to extend in a direction of the wave axis along a portion of the waveguide. An interaction between the electromagnetic wave and the waveguide induces a net force on the waveguide. One vehicle includes a thrusting system substantially as described above.

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.

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.

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.