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US 12,540,590 B2Granted
Ignition and operation of liquid fuel powered rocket engine
AssigneeVenus Aerospace Corp.
InventorsAli Moradi, William Thomas Ross, Vishal Doshi, Eric Wernimont, Andrew Duggleby
Life of this patent
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Abstract
A rocket engine configured to run on a liquid fuel and liquid hydrogen peroxide is started by impinging high pressure streams of a fuel and liquid H2O2 into a combustion chamber under pressure and temperature conditions sufficient to decompose the liquid H2O2 into hot water stream and oxidizer and achieve ignition.
Claims7
A rocket system comprising a rocket engine configured to run on liquid fuel and liquid H2O2, said rocket engine comprising:
- a detonation chamber including a mixing section wherein liquid fuel and liquid H2O2 originating from an injection plate are impinged on one another;
- and a detonation section wherein the liquid fuel and liquid H2O2 achieve ignition and detonation, wherein the detonation section includes an annulus extending to a nozzle section of the rocket, and wherein the rocket system comprises one or more ignition torches which join the detonation chamber at a position equal to about 4 times a width of the annulus downstream of the injection plate.
Dependencies are inferred from the claim text.