A reconfigurable power processing unit for a spacecraft including a plurality of power modules. Each of the power modules includes a first power source and a second power source. The first power source and the second power source are configured to be in series in a first state and in parallel in a second state. A plurality of contactors connect each power module to at least one of another power module in the plurality of power modules and a power processing output and are configured to control the state of the power modules.

Plasma cathodes for Hall and ion thrusters of high power efficiency, high current, low cost, compactness, are provided. The cathodes employ an orifice cup for containing plasma or discharge outside of the cathode insert.

Aspects disclosed herein include graphite and hexagonal boron nitride bimaterials, methods of making these bimaterials, and electric propulsion devices or thrusters with these bimaterials. Aspects disclosed herein include electric propulsion devices comprising: at least one portion comprising or formed of a monolithic bimaterial; wherein the monolithic bimaterial comprises a graphite material and a hexagonal boron nitride material; and wherein the graphite material and hexagonal boron nitride material are monolithically integrated in the bimaterial.

There is disclosed a method of vectoring a rocket propulsion system producing a partly ionized exhaust jet along a longitudinal jet axis and through a nozzle. One or more pairs of electrodes may straddle the exhaust jet inside the nozzle or at a nozzle exit. A high-voltage DC supply may energize one or more of the electrode pairs with a strong electric field. A field intensity of the electric field may be scaled by the DC supply to proportionately deflect the exhaust jet away the longitudinal axis by a desired vectoring angle. The particular pair voltages sent to each pair of electrodes by the DC supply may be weighted for establishing a desired azimuth for the deflection. The strong electric field may laterally accelerate positively charged particles in the exhaust jet toward a negatively charged side of the one or more electrode pairs, thereby achieving the desired deflection and azimuth.

An integrated ion thruster unit for a spacecraft can include a unit housing including a thrust face, and a plurality of tiles arranged in an array on the thrust face. Each of the tiles can include an emitter and an extractor configured to provide a reference voltage with respect to the emitter. The emitter can include a plurality of tips configured to emit ions in a thrust direction from an ionic liquid propellant in response to an applied voltage.

A plasma engine includes a plasma source that generates ions from molecular gas species received at a gas input where at least some of the ions generated are atomic species ions. An ion extractor is configured to extract ions from the plasma source with an electric field. A housing comprising a recombination region receives ions extracted from the ion extractor. At least some of the atomic species ions recombine into molecular species in the housing, thereby releasing energy for thrust.

An exemplary air-breathing plasma engine and methods of operation are disclosed employing an arc plasma chamber that generates plasma, e.g., electrode-coupled, direct current plasma, via electrodes continuously fed by an electrode-feeding assembly. The plasma chamber can be implemented in any one of the stages following the compression stage and having high-pressure and high-velocity air flow, e.g., for a jet engine, turbojet engine, or rocket engine.