Investigation of Scavenging Systems for Removal of Rocket Exhaust Gases from Space Simulation Chambers

摘要

Tests were conducted on a rocket exhaust scavenging system as part of a program to develop new techniques for testing at simulated space conditions. Detailed plume characteristics were computed, and a model scavenging system was tested for both cold and hot gas rockets. Results indicate that for the firing of a typical small control rocket it will be possible to maintain 0.0001 torr pressure in a space chamber. (Author)