Accession Number : AD0881744
Title : Air Force Reusable Rocket Engine Program XLR129-P-1. Volume 1
Descriptive Note : Final rept. 6 Nov 1967-15 Aug 1970
Corporate Author : PRATT AND WHITNEY AIRCRAFT WEST PALM BEACH FL FLORIDA RESEARCH AND DEVELOPMENT CENTER
Personal Author(s) : Atherton, Robert R.
PDF Url : AD0881744
Report Date : JAN 1971
Pagination or Media Count : 419
Abstract : The objective of this program was to demonstrate the performance and mechanical integrity of a 250,000 lb thrust reusable rocket engine designated the XLR129-P-1. The program, sponsored by the Air Force Rocket Propulsion Laboratory, was accomplished by Pratt and Whitney Aircraft at the Florida Research and Development Center and consisted of design and analysis of all engine components and the demonstrator engine. Fabrication and testing of the critical major components was also accomplished. The engine was designed to operate with liquid oxygen and liquid hydrogen propellants, uses the staged combustion cycle, includes a variable thrust, and a variable mixture ratio capability. During the third year, fabrication and testing of certain components such as the preburner injector, transition case, and fuel turbopump was accomplished. Critical control system components such as the preburner oxidizer valve, the preburner fuel valve and static seals were also tested and evaluated. These tests demonstrated the feasibility of these components. (Author)
Descriptors : *LIQUID PROPELLANT ROCKET ENGINES, *RENDEZVOUS SPACECRAFT, MANUFACTURING, COMBUSTION CHAMBERS, INJECTORS, THRUST VECTOR CONTROL SYSTEMS, CAPTIVE TESTS, ROCKET NOZZLES, SPACE PROPULSION, CRYOGENIC PROPELLANTS, TURBOPUMPS, BUTTERFLY VALVES.
Subject Categories : Liquid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE