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filingDate 1970-05-08-04:00^^<http://www.w3.org/2001/XMLSchema#date>
grantDate 1972-10-03-04:00^^<http://www.w3.org/2001/XMLSchema#date>
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publicationDate 1972-10-03-04:00^^<http://www.w3.org/2001/XMLSchema#date>
publicationNumber US-3695041-A
titleOfInvention Two-stage hydrazine rocket motor
abstract Hydrazine is catalytically decomposed in a primary reaction chamber. During low thrust operation all of the decomposition products flow directly to the nozzle. During high thrust operation an oxidizer is reacted with a major portion of the decomposed hydrazine in the central portion of the secondary reaction chamber downstream of the primary reaction chamber. The remaining decomposed hydrazine is directed as a buffer layer along the inner surface of the secondary reaction chamber''s outer wall, to serve as a coolant.
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