Development, flight performance, and test results for two single-stage Malemute rocket vehicles launched at Tonopah Test Range. [Analysis of rocket engine failures]
Two recent Malemute rocket motor failures had been attributed to a change in the internal ballistics of the rocket motor induced by vehicle spin. After the second failure a correlation between the outcome of all previous tests and the time history of the orientation of the total acceleration vector angle was observed. In an effort to obtain additional data to substantiate the acceleration vector angle correlation and to learn more about the Malemute spin problem in general, two single-stage Malemute rocket vehicles were launched from the Tonopah Test Range in July 1976. The results of the aeroballistic and flight performance analyses conducted in preparation for these tests, along with pertinent thrust, mass property, and aerodynamic coefficient data and the results of the tests, which were completed successfully with all objectives satisfied are presented. The first rocket vehicle flight had a vector angle history within the allowable limits established by the vector angle hypothesis. The test was successful, and examination of the recovered motor showed adequate design of the motor insulation system, igniter, and nozzle. The second flight test had a vector angle history that fell outside of the established limits; it exploded 0.6 second before burnout. From the examination of the recovered motor pieces, it was determined that this flight failure and previous flight failures were caused by motor case insulation erosion resulting from flowing alumina.
- Research Organization:
- Sandia Labs., Albuquerque, NM (USA)
- DOE Contract Number:
- EY-76-C-04-0789
- OSTI ID:
- 7214828
- Report Number(s):
- SAND-77-0061
- Country of Publication:
- United States
- Language:
- English
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