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High performance n2o4/amine elements. [propellant tests of hypergolic rocket propellants used in space shuttle orbiters
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Falk, A. Y. |
| Copyright Year | 1976 |
| Description | An analytical and experimental investigation was conducted to develop an understanding of the mechanisms that cause reactive stream separation, commonly called blowapart, for hypergolic propellants. The investigation was limited to a N2O4/MMH propellant combination and to a range of engine-operating conditions applicable to the space tug and space shuttle attitude control and orbital maneuvering engines. Primary test variables were: chamber pressure (1 to 20 atm), fuel injection temperature (283 to 400 K)m and propellant injection velocity (9 to 50 m/s). The injector configuration studied was the unlike doublet. The reactive stream separation experiments were conducted using special combustors designed to permit photography of the near-injector spray combustion flow field. Analysis of color motion pictures provided the means of determining the occurrence of reactive stream separation. |
| File Size | 18615565 |
| Page Count | 98 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19760015308 |
| Archival Resource Key | ark:/13960/t83j87w7d |
| Language | English |
| Publisher Date | 1976-03-01 |
| Access Restriction | Open |
| Subject Keyword | Propellants And Fuels Propellant Tests Injectors Test Stands Orbit Maneuvering Engine Space Shuttle Motion Pictures Space Tugs Hypergolic Rocket Propellants Fuel Injection Combustion Chambers Space Shuttle Orbiters Propellant Combustion Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
