An investigation was conducted to determine the feasibility of a small, low-cost, caseless, hybrid-booster/solid-fuel ramjet (H/SFRJ) that utilizes a common fuel grain and has no ejectables. Performance of an air-to-ground missile with a solid propellant booster and SFRJ sustainer, capable of being fired from an unmanned aerial vehicle or helicopter was obtained using an Air Force computer code. A H/SFRJ motor was then designed analytically and compared to the generated computer output. The results showed that a H/SFRJ that has performance equal to a solid-booster SFRJ is feasible. The final missile design had a range of 20 nm, a flight Mach number of 2.0, a diameter and length of 5 and 99 inches respectively, and weighed 82 lb. Caseless hybrid rockets with erodible nozzles were tested to validate assumptions made in the design analysis. In addition, transition from hybrid-rocket booster to solid-fuel ramjet sustainer was demonstrated. (MM).
Integral Hybrid-Boost/Solid Fuel Ramjet Propulsion for Lightweight Tactical Missiles
1995
64 pages
Report
No indication
English
Air & Space-Launched Missiles , Jet & Gas Turbine Engines , Rocket Engines & Motors , Ramjet engines , Air to surface missiles , Solid propellant rocket engines , Computer programs , Guided missiles , Theses , Grain size , Helicopters , Unmanned , Lightweight , Mach number , Remotely piloted vehicles , Booster rocket engines , Rocket nozzles , Solid propellants , Propellant grains , Sustainer engines , Solid fuels , Ramjet engine nozzles , Hybrid rocket engines
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