O2/H2 Advanced Maneuvering Propulsion Technology Program Engine System Studies. Volume II. 25,000 Pound Thrust Bell Engine Configuration Design and Analysis.
Final rept. 1 Feb-1 Oct 71.
ROCKETDYNE CANOGA PARK CA
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The report describes the results of the O2H2 Advanced Maneuvering Propulsion Technology Program Bell Engine study. The objective of the study was the definition of main rocket engine systems applicable to advanced cryogenic oxygenhydrogen space vehicles. The study described in this volume was directed toward non-aerospike nozzle configurations to provide designs for comparison to the aerospike configuration described in Volume 1. Preliminary engine designs were prepared for thrust levels from 8,000 to 50,000 pounds for several nozzle and engine system configurations. A detailed design and analysis was carried out for a selected 25,000-pound-thrust engine configuration. The analysis included the effects of variations in certain engine system design conditions, development programs and costs, failure mode, effects, operational characteristics, and maintenance plans. Author
- Liquid Propellant Rocket Engines
- Unmanned Spacecraft