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Advanced space engine preliminary designAnalysis and design of an optimum LO2/LH2, combustion topping cycle, 88,964 Newtons (20,000-pound) thrust, liquid rocket engine was conducted. The design selected is well suited to high-energy, upper-stage engine applications such as the Space Tug and embodies features directed toward optimization of vehicle performance. A configuration selection was conducted based on prior Air Force Contracts, and additional criteria for optimum stage performance. Following configuration selection, analyses and design of the major components and engine systems were conducted to sufficient depth to provide layout drawings suitable for subsequent detailing. In addition, engine packaging to a common interface and a retractable nozzle concept were defined. Alternative development plans and related costs were also established. The design embodies high-performance, low-weight, low NPSH requirements (saturated propellant inlet conditions at start), idle-mode operation, and autogenous pressurization. The design is the result of the significant past and current LO2/LH2 technology efforts of the NASA centers and the Air Force, as well as company-funded programs.
Document ID
19740008376
Document Type
Contractor Report (CR)
Authors
Zachary, A. T. (Rockwell International Corp. Canoga Park, CA, United States)
Date Acquired
September 3, 2013
Publication Date
October 1, 1973
Subject Category
PROPULSION SYSTEMS
Report/Patent Number
NASA-CR-121236
R-9269
Funding Number(s)
CONTRACT_GRANT: NAS3-16751
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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