Accession Number : AD0377469
Title : HYBRID PROPULSION SYSTEM FOR AN ADVANCED ROCKET-POWERED TARGET MISSILE.
Descriptive Note : Quarterly rept. no. 1, 1 Jun-30 Sep 66,
Corporate Author : UNITED TECHNOLOGY CENTER SUNNYVALE CALIF
Personal Author(s) : Jones,R. A.
Report Date : NOV 1966
Pagination or Media Count : 166
Abstract : 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 mils/sec. Initial fuel grain insulation tests results have shown that silicon materials ablate at a rate of 2 mils/sec 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.
Descriptors : (*HYBRID ROCKET ENGINES, SURFACE TO AIR MISSILES), (*SURFACE TO AIR MISSILES, *GUIDED MISSILE TARGETS), ROCKET NOZZLES, COMBUSTION CHAMBERS, FUEL INJECTORS, IGNITION, DESIGN, CAPTIVE TESTS, SILICON, TEMPERATURE, TEST METHODS, THRUST, AIRFRAMES, FUEL TANKS, OXIDIZERS, STRESSES, PRESSURE
Subject Categories : Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE