机械式轴对称矢量喷管动态偏转的矢量特性研究  

Performance of Mechanical Axisymmetric Vectoring Nozzle During Dynamic Deflection

作　　者：张群锋[1] 吕志咏[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《航空动力学报》2004年第3期294-299,共6页Journal of Aerospace Power

摘　　要：采用限体积法在同位网格中对满足几何守恒定律的控制方程进行离散化,对某一轴对称矢量喷管在几何偏角速度大小为40°/s下从0°偏转到14.2°过程中的内外流场采用压力隐式分离算法(PISO)进行了数值模拟,分析了该喷管在不同的落压比、不同的外流速度下偏转时,喷管内外流场的动态变化特性,几何偏角和气动矢量角的关系,当喷管偏转后在内壁面产生分离时,喷管的气动矢量角振荡。研究结果为矢量喷管的设计和发动机控制技术的研究提供了参考。To study the internal flow characteristics of an axisymmetric vectoring nozzle with external flow at the geometrical deflective angle varying from 0° to 14.2° with deflective angle rate of 40°/s, the numerical simulation is conducted with collocated finite volume scheme and pressure implicit split-operator method. The influence of nozzle pressure ratio and the external flow on the performance of the axisymmetric vectoring nozzle and the relation between the geometrical deflective angle and thrust vectoring angle are analyzed. The thrust vectoring angle oscillates after the separation flow occurs on internal wall. The results can be used for designing these nozzles and their control method.

关 键 词：轴对称矢量喷管 动态偏转 矢量角 分离流 数值模拟 飞机 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]