基于推力矢量控制的气体二次喷射混合流场实验研究  

Experimental research of secondary injection based on thrust vector control

作　　者：郭建中[1] 陈步学[2] 

机构地区：[1]西北工业大学飞机系,陕西西安710072 [2]西北工业大学航天工程学院,陕西西安710072

出　　处：《流体力学实验与测量》2003年第4期34-37,共4页Experiments and Measurements in Fluid Mechanics

摘　　要：介绍用于固体火箭发动机推力矢量控制的气体二次喷射实验装置及实验方法;研究了气体二次喷射中喷射位置、喷射角度、喷射孔形状、喷射马赫数、喷射流量等诸多参数对混合流场弓形激波的影响;并对实测的弓形激波半径与激波理论分析方法求得的激波半径进行了比较,二者激波斜率基本一致。This paper introduces the experimental equipment and the method of secondary injection based on thrust vector control of SRM.Effect on bow shock wave due to secondary gas injection was investigated with different Mach numbers,gas mass,jet nozzle shape,jet positions and angles.The experimental data obtained from schlieren photograph were compared with the results from the blast wave theory. It proved that the shock slope from the blast wave agreed well with the experimental ones.This experiment provides a good foundation for theoretical calculation research of side thrust on thrust vector control.

关 键 词：推力矢量控制 气体喷射 流场 飞行器 喷管 实验研究 固体火箭发动机 

分 类 号：V435.23[航空宇航科学与技术—航空宇航推进理论与工程] V435.6