National Altitude Rocket Test Facilities
Abstract
The necessity for experimental verification of rocket-engine performance at altitude or near-space conditions has long been recognized in the aerospace industry. Recent spacecraft rocket-engine research and development trends toward higher area ratios, advanced nozzle concepts, and nonequilibrium flow conside ations have made altitude simulation a requirement of development pro- grams. Recause the need for information regarding the capabilities and char- acteristics of altitude test facilities that are suitable for l%id-rocket%- engine operation was recognized, this survey was compiled with the help of representatives of industry and government agencies;% % INTROPUCTION The advent of upper-stage and spacecraft engine-vehicle development pro- grams along with the need for more rigorous performance and reliability data justified the construction of a number of altitude test facilities. The test capabilities of these facilities range from small attitude-control engines to large upper-stage engines. The altitude-simulating systems include simple diffusers coupled to the engine nozzle exit (fig. 1), steam ejector coupled to the engine-driven diffuser (fig. 2), and pumped environmental chambers coupled to a diffuser or ejector system for use during engine firing (fig. 3). Several techniques for vacuum generation exist. In addition to the conventional sys- tems of mechanical pumps and steam boilers for stem% ejectors, there are semi- portable liquid-propellant-driven steam generators.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1964
- Accession Number
- ADA396960
Entities
People
- Jack A. Suddreth
Organizations
- National Aeronautics and Space Administration