HYBRID PROPULSION SYSTEM FOR AN ADVANCED ROCKET-POWERED TARGET MISSILE.
Quarterly rept. no. 1, 1 Jun-30 Sep 66,
UNITED TECHNOLOGY CENTER SUNNYVALE CALIF
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The objectives of this program are 1 to demonstrate that low-cost hybrid propulsion units are capable of providing step thrust operation over an approximately 8 to 1 range, burning for durations of up to 7 min, and operating reliably under extreme environmental conditions of temperature and vibration and 2 to provide hybrid propulsion units to be used in a flight demonstration program to prove the feasibility of a hybrid-powered target missile. The program will be conducted in four phases phase I, design phase II, development phase III, system fabrication, assembly, and delivery and phase IV, technical liaison. During this report period, a total of seven heavyweight motor firings were conducted, of which four were nozzle evaluation tests at boost thrust conditions and three were fuel grain insulation tests at sustain thrust conditions. The results of the initial nozzle evaluation tests have shown that the nozzle material and configuration can produce nozzle material erosion rates of from 0 to 5 milssec. Initial fuel grain insulation tests results have shown that silicon materials ablate at a rate of 2 milssec when exposed to the combustion chamber gases. In addition, a pyrogen igniter system was successfully developed, and performance has been verified at ambient temperature conditions.
- Rocket Engines