高室压脉冲推力器冷流实验  

Cold test of pulse thruster with high combustion chamber pressure

作　　者：梁树强[1] 刘宇[1] 覃粒子[1] 林震[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《航空动力学报》2009年第7期1661-1665,共5页Journal of Aerospace Power

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了解其工作特性,进行了冷流实验.可移动喷注器的动态密封采用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.实验表明密封效果良好,摩擦力大小符合设计要求,冷流下推力器仍可脉冲工作,可移动喷注器能够实现增压的目的.In order to verify the design and analyze the characteristics of pulse thruster with high combustion chamber pressure,the cold test was carried out.Using O-ring as a dynamic seal of the moving injector,the channels enabled the propellants to flow from manifold cavities to extrusion cavities,and few propellants were recirculated.The sealing result of O-rings was tested,and the friction force was measured.According to test results,the sealing result is good,and the friction force accords with the design requi...

关 键 词：脉冲推力器 可移动喷注器 冷流实验 动密封 脉冲工作 

分 类 号：V433.91[航空宇航科学与技术—航空宇航推进理论与工程]