建立带矢量喷管的涡扇发动机动态数学模型。
The mathematical model of turbofan engine transient process with thrust vectoring nozzle was established.
基于数值模拟方法，研究了逆流矢量喷管非定常内流性能。
Internal performance of unsteady flow of counterflow thrust vectoring nozzle has researched base on numerical simulation.
研究了矢量喷管偏转角和偏转角速度对涡扇发动机工作的影响。
The effects of thrust vectoring angle and angular velocity of vectoring on turbofan engine operation were investigated.
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.
研究结果表明，喷管内的分离激波是影响轴对称矢量喷管性能的重要因素。
The investigation shows that the separation shock wave gives an important effect on internal performance of axisymmetric vectoring nozzle.
研究表明，分离流动对矢量喷管的性能参数尤其是有效矢量角具有较大影响。
The results show that flow separation has much effect on the performance parameters, especially the efficient deficient angle of the nozzle.
最后，非定常流的结果进一步表明，逆流喷管是一种较高效率的射流式矢量喷管。
Lastly, the results of unsteady flow point out, counterflow thrust vectoring nozzle is a efficiency fluidic vectoring nozzle.
结果表明：偏转矢量喷管的壁温沿周向有明显变化，沿偏转方向的壁温较低，相反方向的壁温较高。
The results show that the temperature of deflected vectored nozzle varies apparently along the circumference, temperature along the deflecting direction is lower than that of the opposite direction.
提出了一种二元收扩矢量喷管的概念，用热射流实验台对二元矢量喷管进行了过膨胀状态下的喷管模型热态实验。
A new propulsion concept of 2 D C D vectoring nozzle was proposed, which had a convergent duct shaped by spheric surface and a divergent one with rectangular transverse section.
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.
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.
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.
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.
次流压比的增加将导致激波向扩张段上游移动，且喷管矢量角不断增加；
Along with the increase of the secondary flow pressure ratio, the shock move toward upstream divergent section and the thrust vector angle gradually increases;
减小喷管落压比可以提高矢量偏转角度。
The vectoring Angle increases with the decreasing of the nozzle pressure ratio.
减小喷管落压比可以提高矢量偏转角度。
The vectoring Angle increases with the decreasing of the nozzle pressure ratio.
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