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High-Altitude Tests of Rocket Engines in Ground Test Facilities
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English
Abstract
An estimate of the major simulation requirements for high-altitude tests of rocket engines is presented. The design criteria for such facilities are examined in terms of the exhaust gas handling requirements, including both the pumping and cooling systems. Some requirements for the test cell and specialized installation and instrumentation equipment are discussed. Where appropriate, the characteristics of the test units in operation in the Rocket Test Facility at the Arnold Center are cited as examples. A forecast of future test requirements is also included.
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Authors
Citation
Smith, R. and Ferrell, J., "High-Altitude Tests of Rocket Engines in Ground Test Facilities," SAE Technical Paper 640811, 1964, https://doi.org/10.4271/640811.Also In
References
- U. S. Standard Atmosphere, 1962 U. S. Government Printing Office Washington, D. C. December 1962
- AGARD Flight Test Manual I Performance New York: Pergamon Press 1959
- Latvala E. K. Wang E. S. J. “Vacuum Pumping Methods for Space Chambers.” Paper presented at Second Symposium on Rocket Testing in Simulated Space and High Altitude Environments, Arnold Engineering Development Center June 1961
- Smith R. E. Jr. Taylor D. “Performance of Single-Stage and Two-Stage Exhaust Gas Ejector-Diffusers at Steady-State Conditions.” Paper presented at Second Symposium on Rocket Testing in Simulated Space and High Altitude Environments, Arnold Engineering Development Center June 1961
- German R. C. Bauer R. C. “Effects of Diffuser Length on the Performance of Ejectors without lnduced Flow.” AEDC-TN-61-89 August 1961
- Goethert B. H. “High Altitude and Space Simulation Testing.” ARS Journal 32 6 June 1962 872 882
- Test Facilities Handbook 5th Edition “Rocket Test Facility” 2 Arnold Engineering Development Center July 1963
- Marshall J. W. Mickola R. H. “Systems Design Consideration for Testing of Rocket Engines at Altitude.” ARS Preprint 1664-61 March 1961
- Goethert B. H. “Base Flow Characteristics of Missiles with Clustered Rocket Exhausts.” Aerospace Engineering 20 3 March 1961 28 29 108 117