在不增加激励器输入功率的情况下，带倾角激励器可以极大地增加主流偏转角度，推力向量控制效果很好。
The actuator at an angle can change greatly the primary jet direction and has a good effect on thrust vectoring without increasing input power.
结果表明：地面和空中最小操纵速度的大小主要取决于工作发动机推力形成的偏转力矩。
The calculating results show the different mainly depends on non symmetric thrust moment formed by the operative engine.
对于轴对称喷管模型主要进行了喷管的推力特性测量，对于实施矢量偏转后的喷管模型除了给出了喷管推力特性外，还给出了喷管的偏转效率。
The thrust characteristics of axis symmetry nozzle were mainly measured in test. For the nozzle having a vectoring angle, the deflection efficiency was measured too.
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