Methods and systems for a discharge power supply for providing a stabilized discharge power to a Hall-effect thruster are provided. A method includes sensing, by a first sensor circuit and based on a discharge power, a voltage sense signal, sensing, by a second sensor circuit and based on the discharge power, a current sense signal, multiplying, by a multiplying circuit, the voltage sense signal and the current sense signal to generate a feedback signal, generating, by a control logic circuit and based on control signals, further control signals, generating, by an impulse generation circuit and based on the further control signals and the feedback signal, control impulses, producing, by a transistor bridge and using the control impulses and a power source, an electrical impulses, and modifying, by an output circuit, the electrical impulses to generate the stabilized discharge power.

A flying capacitor multilevel (FCML) converter including a gate driver circuit comprising a DC-DC flyback converter having a plurality of isolated outputs. In various examples, the FCML circuit further includes a first control circuit connected to the FCML circuit determining the load current associated with a desired power output from the load; and determining a desired output voltage associated with the load current; a second control circuit that drives an inductor current (I.sub.L) through the inductor so that the output applies an output voltage comprising the desired output voltage; and a third control circuit obtaining a comparison of an average of the inductor current (I.sub.L) through the inductor with a predetermined reference current (I.sub.LREF) and setting the duty cycle so that the average does not exceed the predetermined reference current. Also described is the converter driving a load comprising a plasma and a propulsion system comprising the converter.

A spacecraft includes a power train that includes a solar array, an electric propulsion subsystem, and a power conversion module. The power conversion module receives power from the solar array at a voltage, V.sub.i; and delivers power to the electric propulsion subsystem at a voltage, V.sub.o. The spacecraft is configured to operate at a varying distance, D, from the sun within the range of D.sub.min to D.sub.max, D.sub.max being at least 1.3D.sub.min. The solar array is configured to deliver power to the power conversion module at a voltage approximately equal to V.sub.o when the spacecraft is proximate to D.sub.max.

A vacuum arc thruster (VAT) for a propulsion system of a micro-satellite is provided. The VAT includes an anode, a cathode including a fuel, and an insulator between the anode and the cathode. The VAT is operable to create an arc between the anode and the cathode and discharge plasma through the diverging nozzle as thrust. The anode may define a diverging nozzle. The VAT may further include a Halbach array including a plurality of permanent magnets arranged in a ring, each of the permanent magnets of the ring having a radially inward positioned north pole and a radially outward positioned south pole.

A system for propelling a nanosatellite, including a pair of separated electrodes defining an ignition space therebetween a power source operationally connected to the pair of separated electrodes. Also included is a liquid propellant reservoir a pump reconnected in fluidic communication with reservoir and the ignition space and an electronic controller operationally corrected to the power source and to the pump.

A circuit (400, 700, 800) comprising: a first power source (402) supplying first current to a load (470) during a first Period of Time (PoT); a second power source (416) supplying a second current to the load during a second POT; a Unidirectional Current Valve (UCV) in series with the first power source; a current detector (420, 702, 802) in series with the UCV (422); and a switch (424) in parallel with a series combination of the current detector and UCV to bypass the UCV during the second PoT. The current detector determines whether the second period of time has commenced and whether the switch has closed.

According to certain aspects, an electric-propulsion thruster is used as part of a base or platform which also includes a power converter, having a plurality of inductors and other electrical components, and a printed circuit board (PCB). The PCB includes a layer at which the other electrical components and printed circuit inductor traces, for the plurality of inductors, are secured. The electric-propulsion thruster includes a housing (e.g., as part of the base or platform) providing a cavity and having at least one structurally-rigid side wall along the cavity, where the PCB is integrated with the electric-propulsion thruster for a compact arrangement which can be used to propel the apparatus. Such a compact design might be used as an important part of thruster spacecraft architecture such as micro-satellites (e.g., CubeSats).

Described herein is a thrust system for a vehicle that includes at least three electrical power controllers, at least four electrical switches each configured to receive electrical power from at least one of the at least three electrical power controllers, and at least three thrusters each configured to receive electrical power from at least one of the at least three electrical switches. The at least four electrical switches are operable to switch a supply of electrical power from any of the at least three electrical power controllers to any one of the at least three thrusters.

A control device includes an acquiring unit and a processing unit. The acquiring unit acquires a voltage course and a current course of a determinable number of periods of a frequency generator and transmits these to the processing unit. The processing unit determines a temporal offset t.sub.1 between a rising edge of the current course and a rising edge of the voltage course for each period of the determinable number of periods, and further determines if this temporal offset t.sub.1 is positive or negative. The processing unit determines a difference between the number of periods with positive temporal offset and the number of periods with negative temporal offset within the determinable number of periods, and generates and adapts a switching signal for a switch-on time of the voltage course if the number of periods with positive temporal offset differs from the number of periods with negative temporal offset.

A microwave electrothermal thruster (MET) and its control system is disclosed and claimed. The MET control system uses a dielectric resonator oscillator (DRO) in series with a GaN MMIC-based Solid State Power Amplifier (SSPA) to generate microwave energy, transfer it to a thrust chamber, and heat a propellant that exits a nozzle, providing thrust. The control system uses feedback to provide autonomous control of the MET. A wide variety of propellants may be used, including, for example, hydrazine, ammonia, and water.