介绍了差分流量调节的计算方法和内喷管与塞锥推力矢量变化的分析过程，计算产生的俯仰力矩。
The computing method of differential throttling and the analytical process of thrust vector of inner nozzle and plug were introduced. The generated moments of pitch were given.
矢量喷管是先进战斗机的特征，本文讨论了实现推力矢量存在的技术难点。
As thrust vectoring nozzle is the feature of advanced fighters, the difficulties in implementing thrust vectoring are summarized.
围绕组合喷管及其流量分配调节和推力矢量技术，本文开展了系统性研究。
Systematic researches on combined nozzle and its flow regulation, as well as thrust vector technologies are carried out in this dissertation.
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