Loading...
Please wait, while we are loading the content...
Space simulation experiments on reaction control system thruster plumes
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Cassidy, J. F. |
| Copyright Year | 1972 |
| Description | A space simulation procedure was developed for studying rocket plume contamination effects using a 5-pound bipropellant reaction control system thruster. Vacuum chamber pressures of 3 x 10 to the minus 5 torr (70 miles altitude) were achieved with the thruster firing in pulse trains consisting of eight pulses (50 msec on, 100 msec off, and seven minutes between pulse trains). The final vacuum was achieved by cooling all vacuum chamber surfaces to liquid helium temperature and by introducing a continuous argon leak of 48 std. cc/sec into the test chamber. An effort was made to simulate propellant system flow dynamics corresponding to actual spacecraft mission use. Fast time response liquid flow rate measurements showed that large variations occurred in the ratio of oxidizer to fuel flow for pulse-on times up to 120 msec. These variations could lead to poor combustion efficiency and the production of contamination. |
| File Size | 2255772 |
| Page Count | 10 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730002016 |
| Archival Resource Key | ark:/13960/t96736z6m |
| Language | English |
| Publisher Date | 1972-01-01 |
| Access Restriction | Open |
| Subject Keyword | Propulsion Systems Simulation Liquid Rocket Propellants Rocket Engines Rocket Exhaust Thrust Control Combustion Efficiency Plumes Contamination Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
