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本文先建立了高性能BTT导弹控制系统和两个横向加速度指令数学模型。由于高性能BTT导弹滚转速率较大,俯仰、偏航通道间存在强动力学耦合,但滚动通道可以近似解耦。然后,用本文给出的模型跟随理论设计俯仰一偏航通道自动驾驶仪,用线性二次型理论设计滚动通道自动驾驶仪。为了满足远程全空域BTT导弹作战要求,自动驾驶仪中的增益是滚转速率和动压头的函数。最后,利用某典型地空导弹动力学模型进行了六自由度数字仿真,计算结果表明设计出的自动驾驶仪对导弹结构参数、气动参数、高度等变化具有良好的鲁棒性,导弹侧滑角、脱靶量很小。
This paper first established a high performance BTT missile control system and two lateral acceleration command mathematical model. Due to the high roll rate of high performance BTT missiles and strong dynamic coupling between pitch and yaw channels, the rolling channels can be approximately decoupled. Then, the pitch-yaw channel autopilot is designed using the model following theory presented in this paper, and the linear quadratic theory is used to design the rolling-channel autopilot. To meet the operational requirements of long-range, all-aisle BTT missiles, the gain in the autopilot is a function of roll rate and dynamic head. Finally, a typical six-DOF numerical simulation is conducted using a typical SAM dynamic model. The results show that the designed autopilot has good robustness to missile structural parameters, aerodynamic parameters, altitude and other changes. The missile side slip angle , Off-target is very small.