高室压脉冲液体火箭发动机特性试验

Characteristics tests of pulse liquid rocket engine with high chamber pressure

为了研究高室压脉冲液体火箭发动机工作原理,增压规律以及脉冲特性,通过一系列冷热流试验对试验发动机进行了研究。冷流试验中使用水和氮气作为工质,试验发动机实现自主脉冲工作,验证了差动式可移动活塞应用在推力室中具有增压效果。热流试验中使用气氧/酒精为推进剂,使用传统挤压式推进剂供给系统。在可移动喷注器行程0.8mm条件下,获得9次连续脉冲,燃烧室峰值压强5.511MPa,高于推进剂供给压强(氧气路3.761MPa,酒精路4.424MPa),表明在相同的推进剂供给压强下,高室压脉冲液体火箭发动机能提高燃烧室压强。

Numerous tests using cold flow and hot gas were employed in order to investigate the operating theory, pressurizing principles and pulse characteristics of a Pulse Liquid Rocket Engine （PLRE） with high chamber pressure. A test PLRE with a pressure-fed propellant system was de- signed and fabricated based on calculations and theoretical analysis. In cold flow tests, water and ni- trogen were employed as working substances. The automatic pulse cycles of the test PLRE show that the differential piston increases chamber pressure when it is applied to the thrust chamber. In hot gas tests, ethanol and oxygen were used as propellants. A sequence of nine automatic pulse circles was obtained with a 0.8 mm displacement range of the movable injector. The peak chamber pressure was 5.511MPa, which was higher than propellants feeding pressures （3.761MPa for ethanol and 4.424MPa for oxygen）. The test results show that the PLRE can obviously increase the chamber pressure while the propellants feeding pressures stays the same as the conventional pressure-fed liquid rocket engine.