A Fiber-fed Pulsed Plasma Thruster (FPPT) has an anode, a coaxial insulator, and a fiber propellant feed system. At least two cathodes insulated from each other are configured about the coaxial insulator to define an interior profile shaped into a nozzle region. At least one igniter fitted through each cathode. Wherein when the igniters are triggered, the igniters expel electrons toward the anode to ignite a primary high energy discharge between the anode and the cathodes thereby creating a plasma that vaporizes the fiber propellant. The dissociated fiber propellant combines with the primary high energy discharge to create a partially or fully ionized plasma, that is electromagnetically and electrothermally accelerated to produce predominantly {right arrow over (j)}×{right arrow over (B)}{right arrow over (j)}×{right arrow over (B)} thrust.

A system can include a reservoir configured to hold working material, a decontamination module configured to remove contaminants from the working material, a flow control mechanism configured to regulate working material flow between the reservoir and the decontamination module, and a manifold fluidly connecting the reservoir to the decontamination module.

Electrospray devices and methods of fabricating electrospray devices are described

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 propulsion system for a spacecraft includes at least one chemical propulsion engine, at least one electrical propulsion engine, and a propellant feed system that includes a propellant supply system including at least one tank to store a common propellant. The propellant supply system is configured to deliver a controlled flow of the common propellant to both the chemical propulsion engine and the electrical propulsion engine. Also disclosed is the use of a common propellant in a spacecraft and a method of providing a common propellant to an electrical and a chemical propulsion engine.

A propulsion system for a spacecraft includes at least one electrical propulsion engine comprising at least one neutraliser; and a pressurant gas system comprising a pressurant gas which is fed directly into the at least one neutraliser.

An electric thruster comprises a propellant delivery system, wherein the propellant delivery system comprises: a pipe for carrying propellant; a valve which is adapted to adjust a volume or mass flow of the propellant in the pipe; and an expansion actuator which is adapted to actuate the valve for adjusting the volume or mass flow of the propellant. The electric thruster further comprises at least one tank which is adapted to receive propellant for the electric thruster; and a discharge chamber. The at least one tank thereby at least partially encloses an end of the discharge chamber and/or an element thermally coupled with the discharge chamber, and the valve of the propellant delivery system is arranged between the tank and the end of the discharge chamber.

The invention relates to an ion thruster, comprising: a chamber, a reservoir, comprising a solid propellant (PS), housed in the chamber and comprising a conductive jacket provided with an orifice; means for forming an ion-electron plasma in the chamber, which means are able to sublime the solid propellant in the reservoir, then to generate said plasma in the chamber from the sublimed propellant coming from the reservoir through the orifice; a means for extracting and accelerating the ions and electrons of the plasma out of the chamber, which means comprises at least two grids at one end (E) of the chamber; a radiofrequency AC voltage source for generating a radiofrequency signal comprised between the plasma frequencies of the ions and of the electrons, arranged in series with a capacitor and connected, by one of its outputs and via this capacitor, to one of the grids, with the other grid being connected to the other output of said voltage source;
said means for extracting and accelerating and said voltage source making it possible to form, at the output of the chamber, an ion-electron beam.

A thruster for a micro-satellite is disclosed. The thruster includes a cathode composed of a propellant material and an anode composed of ablative material. The thruster includes a housing having a proximate end and an opposite distal end having a thrust channel. The housing holds the anode and the cathode. A pulsed voltage source is coupled between the cathode and the anode causing current sufficient to create ablation of the anode and a plasma jet including ablated particles from the anode to be emitted from the thrust channel.

The present disclosure is related to propulsion systems (e.g., electrospray devices such as electrospray emitters and/or electrospray thrusters) having a sublimable barrier that may act as a passive valve for a propellant (e.g., a source of ions). The sublimable barrier may be located and arranged such that it physically separates a propellant, such as a source of ions, from an ambient environment exterior to the propulsion system. After the sublimable barrier has sublimated due to exposure to vacuum, and where appropriate diffused out of the propulsion system, the propulsion system may be operated normally. In some embodiments, the sublimable barrier may be a solid sublimable organic compound.