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.

An impedance measurement circuit includes a signal injector having a voltage input and a voltage output, a controllable switch, and a voltage drop device connected in parallel with the controllable switch between the voltage input and the voltage output. The voltage output is connected to a load. A voltage sensor is configured to measure a voltage across the load. A current sensor is configured to measure a current draw of the load. A computing device is configured to determine an impedance of the load at a frequency based on the measured voltage and the measured current. The computing device controls the switch based on the frequency.

Electroaerodynamic devices and their methods of operation are disclosed. In one embodiment, ions are formed by dielectric barrier discharge using a time varying voltage differential applied between a first electrode and a second electrode. The ions are then accelerated in a downstream direction using a second voltage differential applied between a third electrode and the first and/or second electrodes, where the third electrode is located down stream from the first and second electrodes. The ions may then collide with naturally charged molecules and/or atoms within a fluid to accelerate the fluid in the downstream to create an ionic wind and an associated thrust.

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).

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.

Disclosed herein is a propulsion system comprising: a solid conductive or semiconductive cathode (130); an anode (110) having a potential difference relative to said cathode (130), said potential difference creating an electric field between said anode (110) and said cathode (130); and an insulated trigger (150) adapted to trigger an arc discharge from a point on a upper surface of said cathode (130) in pulses, when said trigger (150) and cathode (130) are substantially in a vacuum, said trigger being bounded within the cathode so that the point at which the arc is triggered is located on the upper surface of said cathode.

Plasma cathodes for micro Hall and ion thrusters of unprecedented power efficiency, low cost, compactness, are provided. The cathodes employ, for example, a very small planar scandate cathode as electron source, delivering over 350 ma of discharge from an emitter area as small as only 0.012 cm2.

Systems and methods establish plasma in a rotating magnetic field. An exemplary embodiment is a plasma thruster that establishes a first transverse magnetic field with respect to a system axis of a plasma propulsion system; establishes a second transverse magnetic field oriented orthogonally to the first transverse magnetic field, wherein the second transverse magnetic field is out of phase with the first transverse magnetic field; and establishes a magnetic field aligned with the system axis using a plurality of magnet elements oriented along the system axis. A plasma containment portion defines an interior region, wherein an interior region of a plasma containment portion accommodates a plasma that is established by a rotating magnetic field component that is cooperatively established by the first transverse magnetic field and the second transverse magnetic field, and wherein the plasma is accelerated out of the plasma containment portion by magnetic forces to generate a propulsion force.

An atmosphere-breathing pulsed plasma thruster includes an inlet, a discharge section with an anode in fluid communication with the inlet, and a nozzle in fluid communication with the discharge section. Electrode assemblies extend radially through the discharge section and include a second electrode in the discharge section and an elongate portion extending outwardly. An electrode control mechanism moves the plurality of electrode assemblies between an inner position nearer to the anode and an outer position farther from the anode. At least one igniter extends between the anode and a cathode. An ignition circuit connects the anode and the cathodes to a first source of electric energy, and connects the igniter to a second source of electric energy through a controllable switch. A processor controls the position of the second electrodes, for example, in response to changes in atmospheric pressure.

A satellite thruster increases satellite efficiency. The Linear Actuated CAT has a stepper motor to move the ablative electrode forward. A LabVIEW program and Arduino microcontroller are used to analyze the Linear Actuated CAT to determine how many steps are required for re-ignition, arc current, and the validity of the feed system. Results from testing show that micro-stepping the stepper motor is an effective way to replenish the cannibalized electrode for propellant.