Computational investigation of secondary flow thrust vector control technology used in a convergent-divergent nozzle;
采用六分力试验技术对某推力矢量发动机燃气舵的气动特性进行了试验研究。
Along with the deep development of study, the microjet technology will be possibly applied to control the aerodynamic flow of the high speed aircraft surface and the thrust vector of rocket engine.
并指出，随着研究工作的深入，该项技术还可望用于高马赫数飞行体表面气体流动控制、火箭发动机推力方向控制等。
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