this paper is focused on how to establish mathematical model of vectoring nozzle on the basis of flow field calculation 本文的研究就是针对矢量喷管数学模型的建立开展的。
the thrust-vectoring nozzle control and integrated control of the engine and thrust-vectoring nozzle are researched in this paper 这样,不仅使模型完全达到实时性要求,而且使得计算过程思路更加清晰,易于理解。
the thrust-vectoring nozzle control and integrated control of the engine and thrust-vectoring nozzle are researched in this paper 这样,不仅使模型完全达到实时性要求,而且使得计算过程思路更加清晰,易于理解。
the unsteady flow as thrust vectoring nozzle deflecting dynamically is investigated . the method of calculating the unsteady flow in the nozzle is given and the flow of the nozzle in the maximum power setting and maximum a / b power setting of the engine is calculated 研究了矢量喷管动态偏转过程中气流的非定常流动和矢量喷管非定常流动计算方法,计算了矢量喷管在发动机某中间状态和加力状态下的非定常流场。
more than 200 different condition 3d viscosity steady flow fields in the thrust vectoring nozzle at different nozzle pressure ratio and different nozzle area ratio and different geometric defected angle is calculated by the program developed . and the related performance parameters are acquired by numerical simulation 利用该程序计算了某矢量喷管在不同的压比、面积比和几何偏转角下的200多种三维有粘流场,获得了矢量喷管的性能数据。