卫星姿控发动机喷管羽流撞击效应试验  

Experimental study on plume impingement effects of satellite attitude control thruster nozzle

作　　者：张建华[1] 贺碧蛟[1] 蔡国飙[1] 陈爱国[2] 杨彦广[2] 李震乾[2] 

机构地区：[1]北京航空航天大学,北京100083 [2]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》2007年第2期250-255,共6页Acta Aerodynamica Sinica

基　　金：民用航天预先研究项目(WB1.19);国防预研项目(41320060102)

摘　　要：在高超声速低密度风洞中试验研究了卫星姿控发动机喷管羽流对平板模型的撞击效应,包括气动力和气动热效应。试验气体为加热的氮气。对两个卫星姿态控制发动机喷管的十种实验状态进行了测量。测出了平行于喷管轴线的平板模型上的压力分布和温度变化及处于喷管上方后流区的挡板的温度变化,给出了平板模型上的气动力和气动热分布规律,并判断是否形成后流区。测量结果表明,试验结果可靠,具有工程应用价值,能为姿控发动机在卫星上的布局提供参考。Experimental study has been performed for the plume impingement effects of the satellite attitude control thruster plume to a fiat plate. The impingement effects include plate surface force and heat payload. The whole experimentation is performed in the supersonic low density wind tunnel and the test gas is heated nitrogen. Ten experimental cases are measured for two different geometry satellite thrusters and different plate＇ s locations. The parameters such as plate＇ s surface pressure and heat flux distribution are obtained. The heat flux distribution of plate in the plume backflow is also measured. The laws of distribution of surface pressure and heat flux are obtained by comparing the experimental results, by which it can be judged to form the backflow. The results analysis demonstrates that the experimental results are effective and reasonable. The study provides the experimental foundation for the layout of attitude control thrusters on satellites.

关 键 词：姿控发动机 高空羽流 撞击效应 气动力 气动热 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]