The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Feb. 16, 2021

Filed:

Mar. 14, 2014
Applicant:

Exquadrum, Inc., Adelanto, CA (US);

Inventors:

Kevin E. Mahaffy, Oak Hills, CA (US);

Byron Henning, Lancaster, CA (US);

Korey Robert Kline, Miami, FL (US);

Philip Pelfrey, Jupiter, FL (US);

Eric Schmidt, Hesperia, CA (US);

Elias Wilson, Palmdale, CA (US);

Assignee:

EXQUADRUM, INC., Adelanto, CA (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02K 9/52 (2006.01); F02K 9/34 (2006.01); F02K 9/97 (2006.01); F02K 9/72 (2006.01);
U.S. Cl.
CPC ...
F02K 9/52 (2013.01); F02K 9/34 (2013.01); F02K 9/72 (2013.01); F02K 9/97 (2013.01);
Abstract

A hybrid rocket engine is described that achieves stable, highly efficient hybrid combustion by having a core flow of fuel-rich gas generator gases, with the flow being surrounded with an annular injection of oxidizer. The fuel-rich gas serves to vaporize and decompose the oxidizer, such as nitrous oxide, and prepare it for effective, stable combustion. In one embodiment, this is done at the head-end of a combustion chamber. The combustion products can then be expanded through a nozzle to create thrust. The engine can be an upper stage engine that can include modular thrust chambers and an integrated aerospike nozzle. The thrust chambers can be arranged in an array that rings the top of the aerospike nozzle.


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