Much works has been distributed to the development of a vacuum system to simulate the outer space and a measurement system to test the arcjet performance . ignition experiments in various operational modes have been done with argon as propellant . macroscopical working parameters including thrust , mass flow rate , voltage , current , inlet pressure and vacuity are obtained by the test measurement system and actual performance parameters including specific impulse , thrust efficiency , ratio of thrust and power and ratio of power and mass flow are calculated 以氩气作为推进剂,在不同工况下进行点火实验,测量获得了其工作推力、电弧电压和电流、推进剂流率和弧室压力等宏观参数,得到了不同实验条件下其工作的实际比冲、推力效率、推力/功率比以及比功率等性能参数,分析了推进剂质量流率、电弧功率、电弧加热发动机电弧室结构尺寸等因素对其性能的影响,为数值模拟研究和实际的低功率电弧加热发动机优化设计及研制提供了实验基础。
The solid - propullant ducted rocket , which combines the advantages of solid propullant rocket and ramjet propulsion , is a new kind of combined propulsion system . it offers considerable advantages for missile propulsion , such as high specific impulse , high speed , light weight , long range , high maneuver and simple structure . as the major direction of the propulsion system for supersonic missile , the ducted rocket has good prospects 它将固体火箭技术和冲压技术有机结合在一起，具有比冲高、速度快、重量轻、射程远、机动性能好和结构简单等诸多优点，最大限度地满足了新一代导弹对其动力装置提出的要求，是超声速导弹动力装置的一个主要发展方向，有着广阔的研究前景。
