某舰载扰流片式导弹主推力气动仿真

Aerodynamic Simulation on Spoiler Thrust for a Ship-Borne Missile

摘要:

为满足小型智能可控导弹的装舰需求，介绍了一型适用于小喷口固体火箭发动机的定轴转动式扰流片。数值仿真研究了扰流片安装位置和喷口压力对发动机主推力的影响。结果表明：扰流片旋转轴与发动机喷口距离改变对主推力调节特性影响小；增加旋转轴与发动机轴线的距离可增大主推力调节范围，但主推力起控角度同时增大。随着舵偏角的增大，发动机喷口的激波型面向发动机喷口靠近，且激波型面由斜激波逐渐变为正激波。

Abstract:

To meet the ship installation requirement of small intelligent controllable missile equipment，a fixed-axis rotating spoiler for small nozzle solid rocket motor is introduced in this paper. This paper has studied the influence of spoiler installation position and nozzle pressure on the thrust of the motor by numerical simulation. The results show that the change of the height between the spoiler rotation axis and the engine nozzle plane has little effect on the main thrust adjustment characteristic of the solid rocket motor. The increase of the distance between the spoiler rotation axis and the engine axis can increase the thrust adjustment range，but the initial control angle will also be increased. With the increase of the deflection angle，the shock wave gradually approaches the engine nozzle， and the shock wave profile changes from oblique shock wave to positive shock wave.