SSME engine system integration of the alternate turbopump program
Abstract
The effect of the engine level integration of the alternate High Pressure Oxidizer Turbopump (HPOTP) on the performance of the Space Shuttle Main Engine (SSME) is examined with reference to the results of the current engine system ground test data analysis. In particular, attention is given to the observed steady state and transient mainstage engine system effects with respect to various engine hardware combinations. It is concluded that none of the engine system concerns eliminate the turbomump from consideration as a permanent addition to the flight program pending certification.
- Publication:
-
Joint Propulsion Conference and Exhibit
- Pub Date:
- June 1993
- Bibcode:
- 1993jpmc.confQU...S
- Keywords:
-
- Ground Tests;
- Manned Space Flight;
- Space Shuttle Main Engine;
- Systems Integration;
- Turbine Pumps;
- Flight Characteristics;
- Fuel Pumps;
- High Energy Oxidizers;
- Propulsion System Performance;
- Spacecraft Propulsion and Power