战术导弹大扇面机动发射研究

Study on Large Sector Maneuvering Launch for Tactical Missile

传统自动驾驶仪或简易平台式惯导系统采用装定扇面角的方法控制导弹机动转弯 ,受框架式陀螺仪测量范围的限制 ,发射扇面角不能过大 ,否则会引起框架系统的锁定 ,导致导弹失稳 ;另外该方法还不能控制导弹的法向过载 ,转弯太急将导致法向过载超过设计指标要求。为此本文提出了一种可直接对导弹法向过载和过载速率进行控制的方案 ,利用能量最优控制方法设计了过载控制指令 ,并采用由角加速度计和线加速度计构成的新型捷联惯导系统对导弹进行稳定和控制。应用该方案对某型超音速导弹进行弹道仿真时 ,较好地控制导弹实现了从± 90°直至± 180°的几种大扇面角发射 。

Traditional autopilot or simple platform INS applies the scheme of setting sector angular to control missile’s maneuvering turn. Be restricted by measurement range of framework gyroscope, sector angular was limited, or framework system would be locked. Moreover, that scheme couldn’t control missile’s normal overload. If missile turned too sharp, overload would exceed the design index. Therefore this paper brings forward a scheme to control missile’s overload and its velocity directly. Applying the method of optimal control for energy to design overload instructions. Further,utilizing a new kind of strapdown inertial navigation system composed of angular accelerometers and linear accelerometers to stabilize and control missile. When applying the scheme to simulate the trajectory for supersonic missile, achieves some large sector launch from ±90° to ±180°. The result shows that this scheme has perfect application value.