Abstract: Various embodiments of a vortex thruster system is described herein that is configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system is configured to decompose a monopropellant and deliver the decomposed monopropellant into a vortex combustion chamber for generating various thrust levels. In some embodiments, the vortex thruster system includes a secondary propellant valve configured to deliver a secondary propellant into the vortex combustion chamber containing decomposed monopropellant to create a high thrust level. Related systems, methods, and articles of manufacture are also described.

Abstract: Various embodiments of a vortex thruster system is described herein that is configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system is configured to decompose a monopropellant and deliver the decomposed monopropellant into a vortex combustion chamber for generating various thrust levels. In some embodiments, the vortex thruster system includes a secondary propellant valve configured to deliver a secondary propellant into the vortex combustion chamber containing decomposed monopropellant to create a high thrust level. Related systems, methods, and articles of manufacture are also described.

Abstract: Various embodiments of a vortex thruster system is described herein that is configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system is configured to decompose a monopropellant and deliver the decomposed monopropellant into a vortex combustion chamber for generating various thrust levels. In some embodiments, the vortex thruster system includes a secondary propellant valve configured to deliver a secondary propellant into the vortex combustion chamber containing decomposed monopropellant to create a high thrust level. Related systems, methods, and articles of manufacture are also described.

Abstract: Various embodiments of a vortex thruster system is described herein that is configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system is configured to decompose a monopropellant and deliver the decomposed monopropellant into a vortex combustion chamber for generating various thrust levels. In some embodiments, the vortex thruster system includes a secondary propellant valve configured to deliver a secondary propellant into the vortex combustion chamber containing decomposed monopropellant to create a high thrust level. Related systems, methods, and articles of manufacture are also described.

Abstract: An acoustic resonance igniter uses high-pressure helium to heat a resonance cavity so a hot surface of the resonance cavity forms a source of ignition to a combustion chamber. The resonance cavity may be round or may extend linearly to increase the size of the hot surface. The combustion chamber is cooled by arranging a feed of hydrogen and oxygen which is oxygen rich and which becomes more so when ignition occurs. A second combustion chamber receives the combustion chamber output and adds additional hydrogen through ports tangential to the wall of the second combustion chamber to enrich the fuel ratio and cool the second combustion chamber. The acoustic resonance igniter is used to ignite a large rocket engine or to form a rocket thruster.

Abstract: An acoustic resonance igniter uses gas expanding through a nozzle to form a sonic, or under-expanded supersonic, jet directed against the opening of a blind resonance cavity in a central body, setting up a high-frequency sonic resonance which heats the gas within the cavity. A pintle extends coaxially with the nozzle and injects liquid propellant into the jet. The liquid propellant ignites with the heated gas within the resonance cavity forming combustion gases. The combustion gases flow through openings in a flange which supports the resonance cavity into a combustion chamber in the same direction as the gas jet flows. The liquid propellant is injected from within the support flange in the direction of combustion gas flow to film cool the combustion chamber wall and the flange and the central body supported by the flange. The acoustic resonance igniter may form a rocket engine ignition torch or a RCS thruster.