高超声速飞行器俯冲段制导与姿控系统设计

针对高超声速飞行器俯冲飞行段制导与姿态控制问题，建立基于飞行器加速度分量的三通道角速率解算模型，提出一种新颖的制导控制系统设计方法。建立高超声速飞行器俯冲段六自由度(6DOF)质心和绕质心动力学与运动模型，以目标-飞行器三维(3D)空间相对运动模型为基础，利用终端滑模控制方法和零化视线(LOS)角速率原理得到飞行器期望过载进而解算对应的俯仰、偏航和滚转角速率指令；姿控系统基于滑模控制理论完成该三通道角速率指令的跟踪并生成飞行器舵偏指令；该方法以解析模型替代传统姿控系统设计中欧拉角指令的跟踪回路，可有效降低制导与姿控系统阶数并减少控制系统设计参数，同时省略了根据气动系数反求欧拉角指令的过程；仿真结果显示，该方法能保证高超声速飞行器(GHV)精确命中地面固定目标，且俯冲飞行过程中各项状态变量均稳定可控。

Guidance and Attitude Control System Design for Hypersonic Vehicle in Dive Phase

For the guidance and control system design of the hypersonic vehicle in the dive phase, an analytical model between components of acceleration of the vehicle in the ballistic frame and the three-channel body rates is established, and a novel guidance and control system design approach is proposed. The six-degree-of- freedom (6DoF) dynamic and kinematical equations of translational and rotational loops of the hypersonic vehicle are denoted. The desired acceleration and three-channel body rates are derived based on the three-dimensional (3D) relative dynamics and the analytical model by making the line-of-sight (LOS) angle rates to converge to zero. The commanded control surface fin deflections are obtained by tracking these body rates commands. The novel analytical model is applied to substitute for the compensated dynamics for the traditional tracking processes of the roll, yaw, and pitch angles. The order and tuning parameters of the 6DoF guidance and control system are reduced, and the process of calculating the angle commands is omitted. Finally, the effectiveness and robustness of the proposed scheme are investigated and verified using an air-breathing generic hypersonic vehicle (GHV).