A matrix thruster that may be used to reposition and/or stabilize a CubeSAT satellite. The matrix thruster includes a conductive plate with an opening, a plurality of wires within the opening, a power supply electrically connected to the conductive plate or each of the plurality of wires via an inductor, and an electrical switch. The electrical switch creates a current change that creates an electric potential spike across the inductor. The electric potential spike across the inductor initiates an arc discharge between one of the wires and the conductive plate, which forms plasma that ejects cathode particles from the matrix thruster. Using multiple wires (e.g., four titanium wires) extends the lifetime of the thruster, as each wire restores an inter-electrode film needed for the other wires to continue generating plasma.

A trussed collapsible tubular mast includes a deformable beam having an extended state, a flattened state, and a rolled state, where a stiffness and strength of the deformable beam in the extended state is greater than a different stiffness and a different strength of the deformable beam in the flattened state. At least one collapsible tubular mast wall has a plurality of truss members of a first material having a first material thickness. At least one truss member is disposed substantially perpendicular to a longitudinal axis of the trussed collapsible tubular mast. Disposed between the truss members is a wall area of a second material thickness less thick than the first material thickness.

The present invention presents an adjustable speed reusable rocket with attachable wings system which is optimized for multiple purpose, such as space travel, high-speed long-distance travel between different addresses on earth, etc. The rocket system comprises an adjustable speed rocket propulsion system (rocket booster), an attachable wings system, a payload or space shuttle and may include slider wings system, etc. Firstly, the rocket system flies at a lift force caused by the attachable wings system at a low speed (e.g., Mach 0.5˜3). While the rocket system reaches relatively high altitude (e.g., 25,000 meters), at this altitude, the air density is extremely low comparing with the surface of earth at zero sea level, and then the attachable wings system may detach from the rocket system and fly to a designated location as a glider or by its engine on a runway, and the rocket system begins to fully initiate propulsion system and exert the payload to forward at a super high speed. Comparing with rocket fully initiate propulsion system from earth surface, the aerodynamic friction and the aerodynamic heat caused by air is extremely small and low.

ThermaSat™ propulsion system uses water as a safe and non-explosive propellant, and which is unpressurized at liftoff. Utilizing solar thermal propulsion, the compact and efficient capacitor heats water to steam to produce high thrust and total impulse. The advanced optical system allows for the thermal capacitor to charge through solar power alone with no protruding concentrators or power draw from the main bus. Additional solar panels, body mounted to the ThermaSat, provide auxiliary heating of the thermal capacitor when not directly incident to sunlight to promote non-sun pointing operations.

An electrodynamic assembly for propelling a spacecraft in orbit around a celestial body having a magnetic field is disclosed. The assembly includes a plurality of coaxial cables for an electrodynamic assembly for propelling a spacecraft in orbit around a celestial body having a magnetic field. Each coaxial cable includes an electrically conductive core surrounded by a first electrically insulating sheath, and an electrically conductive current return circuit mounted outside the first electrically insulating sheath. The current return circuit includes a first end electrically connected to a first end of the core of the coaxial cable.

Disclosed are systems for converting rotational momentum into linear propulsion. A propulsion system includes one or more thrust units with masses controllably driven by actuators to generate inertia that thrusts a vehicle with the propulsion system in a desired direction. The propulsion system can be configured to have multiple units, each configured to generate thrust in a desired direction and counteract or neutralize thrust in other directions. The propulsion system can generate thrust via two operational cycles and/or through continuous operation. The propulsion system may comprise two mirroring units, each configured to operate in mirrored synchrony to generate a net thrust in a desired direction and counteract or neutralize thrust in other or undesired directions.

A multi-mode thruster system for use in a spacecraft includes a microwave source; a cavity coupled to the microwave source and including a first inlet to receive a first fluid and a second inlet to receive a second fluid; and a nozzle provided at one end of the cavity. The thruster operates in a microwave electrothermal thruster (MET) mode to (i) generate a standing wave in the cavity using the microwave source and (ii) raise a temperature of the first fluid to generate a first hot gas that exits the cavity via the nozzle to generate thrust. The thruster operates in a chemical propulsion mode to (i) produce a reduction-oxidation reaction between the first fluid and the second fluid and (ii) generate a second hot gas that exits the cavity via the nozzle to generate thrust.

Exemplary embodiments provided herein include an attachment and deployment system and method. Exemplary embodiments may use features together or separately as desired. The attachment feature may be used to periodically couple a solar sail.

A booster system for a launch vehicle includes a plurality of core boosters and a plurality of patchy boosters. The plurality of core boosters and the plurality of patchy boosters are arranged in an inner space of a rocket casing of the launch vehicle, and the plurality of patchy boosters is separatable from the launch vehicle.

A booster system for a launch vehicle includes a plurality of core boosters and a plurality of patchy boosters. The plurality of core boosters and the plurality of patchy boosters are arranged in an inner space of a rocket casing of the launch vehicle, and the plurality of patchy boosters is separatable from the launch vehicle.