Abstract: Aiming at a cold gas micro-propulsion thruster,a high altitude simulation experiment system was studied, and the experiment system was set up. The thrust and specific impulse of the thruster were measured using the thrust test system. The steady characteristic of the thruster was determined. When the propellants are propane and nitrogen, respectively, the average specific impulse of the thruster are 83.5s and 75.6s, respectively. In order to acquire the dynamic performance of the thruster, the test system should be calibrated with the positive and negative step force, and then the delay time of the test system was 90ms based on the calibration data. Under the specific test condition, the rise time calculation method of thruster and thrust test system was proposed. When mass flux of propane is 40mg/s, the engine rise time is 27.1ms. 

Key words: Cold gas micro-propulsion thruster;Steady calibration;Dynamic calibration;Negative step force;Positive step force;Response time

摘要： 针对所设计的微小推力冷气发动机进行高空模拟试验,搭建了试验系统,并应用推力测试装置测量了发动机不同推进剂下的推力和比冲,得到了发动机的稳态特征参数,当分别以丙烷和氮气为推进剂时,平均比冲分别为83.5s和75.6s。为了获得发动机的动态特征参数,对推力测量装置进行了负阶跃力和正阶跃力动态标定,通过标定数据的对比验证得到推力测量系统的延迟时间为90ms；进而在特定试验工况下,给出了发动机和推力测量装置实际上升时间的计算方法,得到丙烷质量流量为40mg/s时,发动机的上升时间为27.1ms。 

关键词: 微小推力冷气发动机;静态标定;动态标定;负阶跃力;正阶跃力;响应时间 