PRELIMINARY PERFORMANCE ANALYSIS OF THE PULSE-DETONATION-JET ENGINE SYSTEM

An engine capable of propelling a guided missile from zero flight speed to a cruising Mach number of 2.80 was assumed. The detonation tubes are arranged in 6 concentric rows of 32 tubes each, which gives an engine diameter of 34 in. The length of the tubes is 15 in., and the over-all length of the engine is 55 in. The engine dry weight is about 900 lb. The shock wave produced during the pulse compression phase will be used to ignite or detonate the fuel- air mixture. The most suitable structure which would permit operation at the maximum cycle temperature of 3500 deg F was determined to be an uncooled tube assembly consisting of zirconium boride or graphite. Preliminary experiments were begun on an experimental apparatus for initiating a detonation wave by means of a shock wave. An engine of this type can deliver as much thrust as the ramjet at the higher Mach numbers and at a lower specific fuel consumption. It will also provide static thrust and power to accelerate from take-off to a high supersonic cruising speed.