冲压式舵机腔内工作压力随飞行速度变化规律的数值仿真

为了简化舵机工作时所需的高压气源,现在一些反坦克导弹采用了冲压式舵机,其最大特点是利用导弹的飞行速度,使得来流的空气由舵机进气口进入舵机气源腔内受阻,从而产生舵机工作时所需的高压气体.由于导弹在飞行过程中其速度是变化的,因此,舵机内的高压气体压力也随速度变化,如何计算舵机内高压气体压力,对舵机和反坦克导弹的设计很重要.本文采用了求解三维、雷诺平均的Navier-Stokes方程的方法,对反坦克导弹的可能飞行速度范围进行了数值仿真.

DIGITAL SIMULATION OF PRESSURE ON A RUDDER ALONG WITH THE VELOCITY OF A MISSILE

In order to secure a highpressure source for the operation of the rudder, a punching rudder is generally used in anti-tank missiles. Its key characteristics lies that the flow velocity is made use of to produce a high pressure for rudder operation when an anti-tank missile is flight. Because the velocity varies in the flight of an anti-tank missile, the pressure in the pump of the rudder is also changing. It is of significance to calculate the pressure in the design of rudders or anti-tank missiles. A method of calculating three-dimensional Navier-Stokes equations was presented. The appropriate range of velocity of anti-tank missile flight was discussed.