基于动态逆的质量矩拦截弹模糊滑模控制

Fuzzy sliding mode control approach to mass moment interception missile based on dynamic inversion

质量矩控制可以避免飞行器在超高马赫数飞行时的舵面气动加热问题,本文建立了质量矩拦截弹数学模型,将其简化为一个耦合的非线性动力学系统.应用双时标分解的方法,提出将拦截弹动力学分离为快变状态动力学和慢变状态动力学,在快变和慢变子系统中应用滑模控制理论设计拦截弹飞行控制系统,采用模糊逻辑算法抑制系统的抖振现象,同时也可以抑制气动参数摄动而引起的控制系统性能的下降.仿真结果表明系统性能指标满足设计要求,只需微调滑块位置,即可实现拦截弹的飞行控制,提高了拦截弹的机动性和敏捷性.

Mass moment control can avoid the aerodynamic heating of flight vehicles flying at extreme Mach numbers. Based on the constructed model of the mass moment interception missile （MMIM） , a coupled nonlinear system is presented by rational simplification in this paper. Dynamics of the MMIM are separated into two parts on basis of the two time-scale separation theory ： the dynamics of fast state and the dynamics of slow state. In order to restrain the chattering of the system and keep the tracking performance of the system by considering the aerodynamic parameter perturbation, the flight control system is developed for the two subsystems respectively via utilizing the fuzzy sliding mode control approach. It can not only control the flight overload of the interception missile but also meet a given set of performance indexes by moving the three masses in missiles slightly. Furthermore, it can meet the demands of the maneuverability and agility of missiles.