Systems and methods for rotating detonation combustion satellite thrusters
AssigneeJuno Propulsion Inc.
InventorsAriana MARTINEZ, Alexis HARROUN
Life of this patent
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Abstract
A thruster operable for use in a satellite may include a rotating detonation combustion chamber; a fuel source operably connected to the rotating detonation combustion chamber, the fuel source comprising two chemical propellants, wherein each of the two chemical propellants comprises a liquid with a vapor pressure sufficient to self-pressurize each of the two chemical propellants; and a valve system configured to control a feed of each of the two chemical propellants to the rotating detonation combustion chamber.
Claims34
A thruster, the thruster comprising:
- a rotating detonation combustion chamber;
- and
- a fuel source fluidically connected to the rotating detonation combustion chamber, the fuel source comprising a plurality of chemical propellants, wherein a first and a second chemical propellant of the plurality of chemical propellants comprises a liquid with a vapor pressure higher than an operating pressure of the first and the second chemical propellant of the plurality of chemical propellants.
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Dependencies are inferred from the claim text.