基于反演法的导弹姿态控制律设计  

Design of Missile Attitude Controller Based on Backstepping Method

作　　者：吴鹏[1] 陈启超[2] 

机构地区：[1]东北林业大学机电工程学院,哈尔滨150040 [2]哈尔滨工业大学电气学院,哈尔滨150080

出　　处：《导弹与航天运载技术》2012年第4期31-34,共4页Missiles and Space Vehicles

基　　金：中央高校基金(Z02068)

摘　　要：提出一种应用反演法来设计导弹的姿态控制律,该控制律能够提高非线性系统的鲁棒性。在设计过程中,首先介绍了反演设计方法从第1步到第n步的设计步骤;然后,将导弹姿态角度作为提出的姿态控制律的控制对象,并根据给定的俯仰角、偏航角和滚转角作为参考信号,得到相应的舵偏输入,使导弹能够按照给定姿态角度确定的轨迹飞行;最后非线性仿真结果证明该控制律的设计可行。A new approach of missile attitude controller using backstepping design method is proposed to improve the robustness of nonlinear system. In this approach, the backstepping design method is introduced from step 1 to step n in the design procedure firstly. The missile attitudes are taken as the control objects of systems by the proposed attitude controller, and according to the given reference signals of pitch angle, yaw angle and roll angle, the relative rudder deviation inputs are derived from backstepping controller. So the missile can fly along the trace in decided attitudes angles. Finally the numerical simulation results demonstrate the feasibility of the proposed controller.

关 键 词：反演法 非线性系统 姿态控制 

分 类 号：TP183[自动化与计算机技术—控制理论与控制工程]