Phase Four, Inc.

Mohammed Umair Siddiqui

Derek William Thompson

Jason Jackson Wallace

David Tsai

Joshua Robert Synowiec

Simon Rubin Halpern

Jesse Sidhu

Systems and methods for a multimode propulsion system (MMPS) are presented. The MMPS includes a chemical thruster, an electric thruster, and a shared propellant tank. The MMPS further includes a propellant decomposition chamber that transforms, via a catalytic and/or electrolytic process, the propellant from the tank into vapor form for use as gas propellant by the electric thruster. The electric thruster can be configured for targeted ionization of one or more constituent species present in the vapor form of the propellant. Flow activation/control from the tank to the chemical and electric thrusters is provided by a fluidic feed system. The branches include a check valve and a pressure regulator in series connection. A normally closed squib valve prevents propellant flows/leaks from the tank to either the chemical or the electric thrusters when the MMPS is not in operation.

Multimode propulsion system

An electrothermal plasma production device is presented. The plasma production device includes: a plasma production chamber; an RF antenna external to the plasma production chamber; a propellant tank and flow regulator external to the plasma production chamber and in communication with the plasma production chamber; and a plenum disposed between the propellant tank and the plasma production chamber. The RF antenna, in combination with an AC power source, is configured to provide an RF energy to an interior region of the plasma production chamber and to an interior region of the plenum with sufficient power to ionize at least some of the propellant in the plenum. The plasma production chamber is configured to include a propellant injector for receiving propellant at a first closed end of the plasma production chamber.

Propellant injector system for plasma production devices and thrusters

The invention provides an electrothermal RF plasma production system and thruster design, and associated components, that may be used in terrestrial applications and/or miniaturized to the mass, volume, and power budget of Cube Satellites (CubeSats) to meet the propulsion needs of the small satellite (&#x2dc;5 to &#x2dc;500 kg) constellations and larger satellite buses.

Electrothermal radio frequency thruster and components

The invention provides a plasma production and control device that may be used in propulsion (e.g., satellite propulsion) and/or industrial applications. The plasma production system comprises a unidirectional magnetic field.

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El Segundo, CA, United States of America

Mohammed Umair Siddiqui