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Linear Test Bed. Volume 2: Test Bed No. 2Test bed No. 2 consists of 10 combustors welded in banks of 5 to 2 symmetrical tubular nozzle assemblies, an upper stationary thrust frame, a lower thrust frame which can be hinged, a power package, a triaxial combustion wave ignition system, a pneumatic control system, pneumatically actuated propellant valves, a purge and drain system, and an electrical control system. The power package consists of the Mark 29-F fuel turbopump, the Mark 29-0 oxidizer turbopump, a gas generator assembly, and propellant ducting. The system, designated as a linear aerospike system, was designed to demonstrate the feasibility of the concept and to explore technology related to thrust vector control, thrust vector optimization, improved sequencing and control, and advanced ignition systems. The propellants are liquid oxygen/liquid hydrogen. The system was designed to operate at 1200-psia chamber pressure at an engine mixture ratio of 5.5. With 10 combustors, the sea level thrust is 95,000 pounds.
Document ID
19740011780
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Date Acquired
September 3, 2013
Publication Date
March 27, 1974
Subject Category
Facilities, Research, And Support
Report/Patent Number
NASA-CR-120183
R-9049-VOL-2
Accession Number
74N19893
Funding Number(s)
CONTRACT_GRANT: NAS8-25156
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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