弹体自旋条件下姿控发动机控制律设计

针对大气层内带有横向喷流姿控发动机和尾部气动舵的导弹，研究了弹体自旋条件下的姿态控制问题。以导弹的横向加速度为输出，建立了姿态系统数学模型，并对模型进行了分析和简化。考虑了双通道控制和单通道矢量控制两种控制方式，针对姿控发动机的离散工作特点，分别研究了控制律设计问题，实现了横向加速度的快速跟踪。针对喷流干扰效应，给出了喷流放大因子的在线估计算法。最后，进行了数值仿真，仿真结果说明了所提方法的有效性。

Control Law Design of Lateral Attitude Jets for Spinning Missile

For an endo-atmospheric missile with lateral attitude jet engines and aerodynamic fins,attitude control is investigated under the condition of body spinning.Choosing the lateral accelerations of the missile as the output,the mathematical models of the attitude control system are constructed,analyzed and simplified.Both dual path control and single path vectored control are considered.Based on the discrete characteristics of the attitude thrusters,respective controllers are designed to realize the fast tracking of the lateral accelerations.In the design,the lateral jet magnification factors are also estimated on-line to cope with the jet interaction effect.Finally,numerical simulation is conducted,and the simulation results show the effectiveness of the proposed method.