一种滑翔增程火箭弹姿态控制器设计

A Design of Attitude Controller for Glide Range-Extended Rocket Projectile

为了克服火箭弹滑翔飞行过程中各种扰动因素的影响,提高弹道控制效果,研究了一种非线性随机系统最优控制方法。基于火箭弹飞行过程的一般控制原理,建立了微分方程形式的姿态动力学模型;以攻角和侧滑角作为观测量,以舵偏角作为控制量,推导出姿态控制系统的状态方程、目标函数与控制律;给出了伴随函数的详细表达式,并基于里卡蒂方程设计了最优滤波器。以滑翔段启控点散布作为特征点进行姿态控制器控制参数设计与仿真分析。仿真结果表明,该控制器系统响应快,具有良好的控制品质。

In order to overcome the influence of various disturbance factors and to improve the control effect in the process of glide and flight,an optimal control method for nonlinear stochastic systems is studied.Based on the general control principle of rocket projectiles flight process,a differential form of attitude dynamics model is established.Taking attack angle and yaw angle as observation variables,and rudder reflection angles as control variables,the state equations,the objective function and the control law are deduced.The detailed expression of the adjoint function is put forward.The optimal filter is designed based on the Riccati equation.Control parameter is designed and simulation analysis is carried out with spread glide control point as the feature point.The simulation results show that this controller system responds quickly and has a good control quality.