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.
通过测量固体火箭发动机水下工作过程中的推力和侧向力，研究了扰流片和摆喷管两种推力矢量方式的水下推力矢量特性。
By measuring the thrust and lateral forces of solid rocket motor during firing conditions, the thrust vector control performances of jet TAB TVC and movable nozzle TVC were studied.
对摆喷管推力矢量方式，获得了推力、侧向力、推力矢量角随发动机喷管偏角以及水深的变化规律。
For the movable TVC, the thrust and lateral forces with respect to nozzle deflection angles and the depth of water were obtained.
对飞机采用推力矢量技术，即应用二元喷管后飞机的气动特性及飞机性能和操纵性加以初步研究，给出了一些结论。
This paper primarily discussed the aerodynamic characteristics and performance, flying quality of aircraft which is using thrust-vector technology, some results are given.
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.
利用数值模拟的方法，通过对逆流方案中喷管气动性能的研究验证了逆流推力矢量方案的可行性。
The feasibility of counterflow scheme is validated by research on the internal aerodynamic characteristics of nozzle using numerical simulation.
利用数值模拟的方法，通过对逆流方案中喷管气动性能的研究验证了逆流推力矢量方案的可行性。
The feasibility of counterflow scheme is validated by research on the internal aerodynamic characteristics of nozzle using numerical simulation.
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