NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Solid propellant rocket motorThe characteristics of a solid propellant rocket engine with a controlled rate of thrust buildup to a desired thrust level are discussed. The engine uses a regressive burning controlled flow solid propellant igniter and a progressive burning main solid propellant charge. The igniter is capable of operating in a vacuum and sustains the burning of the propellant below its normal combustion limit until the burning propellant surface and combustion chamber pressure have increased sufficiently to provide a stable chamber pressure.
Document ID
19730016057
Acquisition Source
Legacy CDMS
Document Type
Other - Patent
Authors
Dowler, W. L.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Shafer, J. I.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Behm, J. W.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Strand, L. D.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Date Acquired
September 2, 2013
Publication Date
May 1, 1973
Subject Category
Propulsion Systems
Accession Number
73N24784
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-PATENT-3,729,935|NASA-CASE-NPO-11559
Patent Application
US-PATENT-APPL-SN-147996
No Preview Available