Air-Augmented Hybrid Target Missile.
Technical rept. 1 Nov 68-1 Jun 69 on Phase 1 and 2,
UNITED TECHNOLOGY CENTER SUNNYVALE CA
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The feasibility of using an air-augmented hybrid rocket for a target missile propulsion system is currently being investigated. The results of the phase I mission study and preliminary system design efforts have shown that an air-augmented hybrid propulsion system is capable of providing a minimum of 5-min range time on station from sea level to 50,000 ft at Mach numbers up to 3.1. Parametric study results have defined an optimum propulsion system capable of supresonic cruise in excess of 25 min at 50,000-ft altitude. The results of various tradeoff studies have shown the effects of air-to-propellant ratio, fuel generator OF ratio, fuel generator pressure, ramburner base pressure, combustion efficiency, ramburner Mach numbers, and air inlet effects. A baseline design configuration has been selected, and off-design performance characteristics have been determined. The phase II fuel formulation development effort has resulted in the successful characterization of a low-cost, high heating value solid fuel that may be used with MON-25 or IRFNA liquid oxidizers. Fuel formulation selection was based on the results obtained by a series of fuel generator screening tests using fuel formulation candidates selected from a fuel performance summary which was prepared specifically for this application. Activities during phase III will include full-scale gas generator and direct-connect tests and a final preliminary design effort. Author
- Air Breathing Engines (Unconventional)
- Rocket Propellants