质量矩拦截弹滑模反演控制律设计

摘要

与传统的舵面控制相比，采用质量矩控制的飞行器在高速飞行下的气动阻力和气动加热都将大大降低，极大地增强了飞行器的机动性和敏捷性，为飞行器的控制效率和控制精度的提高提供了条件。以末段飞行中的质量矩拦截弹为控制对象，在建立其非线性耦合动力学系统数学模型的基础上，针对气动参数和结构总体参数的不确定因素的影响和执行机构在控制过程中存在的抖振现象，采用反演控制和参数提取时自适应律的积分处理算法，设计了快速终端滑模控制律。通过对控制器的稳定性分析和质量块移动指令执行情况的仿真，验证了此方法的有效性和可行性。%Compared with the conventional aerodynamic control,the aerodynamic resistance and heating can be reduced if a flight vehicle is controlled by adopting mass moving control under condition of flying at a high speed.By so doing the maneuverability and agility of vehcles can be enhanced greatly to provide quali-fications for the improvement of the control efficiency and precision of the vehicles.In this paper,taking an interception missile flying at the last stage as a control target,based on the coupled nonlinear system of the missile constructed math model,in view of the influefnce of the aerodynamic parameters and that of the in-determinate factors of the collectivity parameters,and the chattering of the system in the control process , a quick terminal sliding mode control system is developed via backstepping and integral.Through the sta-bility analysis and the simulation of the masses locomotion,the results show that the method is effective and feasible.