The development of a hybrid propulsion system for an advanced rocket-powered target missile has advanced through the seventh program month. During the past 3 months, the heavyweight motor test series was completed successfully, and designs have been finalized for the flightweight thrust chamber assembly components. The results of the final nozzle evaluation tests have shown that the nozzle configuration selected has a nozzle material erosion rate of 0.45 mils/sec. Motor ignition has been demonstrated at -65 F at sea-level conditions and at a simulated altitude of 50,000 ft. The required thrust ratings have been demonstrated at boost and sustain thrust levels for the durations specified, and step thrust operation has been verified over an 8 to 1 range. The flightweight feed system component buildup has been initiated and cold-flow checkout 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 in accordance with the original schedule. (Author)
Hybrid Propulsion System for an Advanced Rocket-Powered Target Missile
1967
252 pages
Report
No indication
English
NTIS | 1993
|Engineering Index Backfile | 1961
|