The development of a hybrid propulsion system for an advanced rocket-powered target missile has progressed through the tenth program month. During the past 3 months, the last increment of heavyweight motor components and a flightweight feed system assembly were delivered to AFRPL. The second set of flightweight feed system hardware was received, assembled, and successfully underwent a series of cold flow tests at UTC. The first flightweight propulsion system proof test was conducted with a motor firing which operated for 95 sec at the boost thrust level followed by 257 sec of sustain, which demonstrated a stepped thrust ratio in excess of 6:1. The total firing time was 6 min. Delivered total impulse exceeded the requirement by 8.6%. The remaining tests will be conducted during the next reporting period. The current status of the program indicates that the hybrid propulsion units to be used in the flight demonstration program will be delivered according to the original schedule. (Author)
Hybrid Propulsion System for an Advanced Rocket-Powered Target Missile
1967
40 pages
Report
No indication
English
NTIS | 1993
|Engineering Index Backfile | 1961
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