NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Linear rocket engines for advanced space transportation systemsThe linear rocket engine is shown to be a viable candidate propulsion system for post-Space Shuttle single-stage-to-orbit systems. The linear engine system has been developed and fired demonstrating high performance and long life with firing durations exceeding 500 seconds. The application of the split or dual combustor to the linear engine permits the uses of two different propellant combinations in a single engine system. The split combustor possesses the advantages of the two position extendible bell nozzle in a fixed nozzle configuration. Engine power cycles and applications to typical vehicles are discussed.
Document ID
19750061586
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Sobin, A. J.
Martinez, A.
(Rockwell International Corp. Rocketdyne Div., Canoga Park, Calif., United States)
Date Acquired
August 8, 2013
Publication Date
September 1, 1975
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 75-1251
Accession Number
75A45658
Funding Number(s)
CONTRACT_GRANT: NAS8-25156
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available