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为获得最佳高性能火箭发动机,对两级脉冲(双脉冲)火箭发动机作了评定性试验。在这个评定试验中便用的双脉冲发动机由两个燃烧室、两个点火器和一个收敛-扩张型喷管组成。两个燃烧室由一个带多个排气喷口的保护盖(称为喷气盖)分开,彼此独立。尾部为助推级燃烧室,前面为主燃烧定。喷气盖用于保护主燃烧室内的推进剂,使其免受助推药柱燃烧时产生的高压和高温的影响。喷射杆嵌入在喷气盖上的喷孔内,当主燃烧室内推进剂燃烧产生一定压力时,它可以很容易地被喷射出去,点火试验结果表明喷气盖工作非常有效,象预想的那样产生了两级脉冲推力。
To obtain the best high-performance rocket engine, a two-stage pulsed (two-pulse) rocket engine was evaluated. The two-pulse engine used in this qualification test consisted of two combustion chambers, two igniters and a convergent-divergent nozzle. The two combustion chambers are separated by a protective cover with multiple exhaust vents, called the air cap, independent of each other. Tail for the boost-class combustion chamber, in front of the main combustion set. The air cap is used to protect the propellant in the main combustion chamber from the high pressures and temperatures that occur when the propellant charge is burned. The injection rod is embedded in the injection hole in the gas cap and can be easily ejected when the main combustion chamber propellant is burned to a certain extent. The ignition test results show that the gas cap works very effectively, resulting in two stages as expected Pulse thrust.