高室压脉冲推力器设计与实验研究  

Design and experiment of a pulse thruster with high combustion chamber pressure

作　　者：梁树强[1] 覃粒子[1] 林震[1] 刘宇[1] 刘亚冰[1] 谢侃[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《火箭推进》2009年第4期8-13,共6页Journal of Rocket Propulsion

基　　金：国家自然科学基金(50706003)

摘　　要：为了检验高室压脉冲推力器的设计并掌握液体N2O/酒精推进剂的点火燃烧规律,进行了实验研究。可移动喷注器的动密封采用O型圈结构,推进剂的流动通道既能保证充填时推进剂的流通,又能保证挤压时不会有回流。冷试结果表明密封效果良好。测定了系统的热试时序,实现了稳态条件下的点火燃烧,燃烧室压力为2.58MPa。由于液体N2O的饱和蒸汽压较高,容易蒸发,积存在燃烧室内的蒸气造成点火压力峰比较高。In order to verify the design of a pulse thruster with high combustion chamber pressure and grasp the combustion characteristic of liquid NRO/alcohol, the experiments were carried out. Using O-ring as dynamic sealing of the moving injector. The propellant flow paths ensure propellants flowing from manifold cavities to extrusion cavities without propellants count-flow. According to the test results, the sealing of O-rings works well. The time sequence was measured, and the ignition was achieved. The combustion chamber pressure was 2.58MPa. The ignition pressure peak was high because of N2O having high saturation vapor pressure.

关 键 词：脉冲推力器 设计 动密封 实验 

分 类 号：V433.9[航空宇航科学与技术—航空宇航推进理论与工程]