摘要
质量矩控制是一种全新的飞行控制方法,与广泛应用的空气动力控制相比,可以避免飞行器在超高马赫数飞行时舵面的气动加热问题,而且,可以提高飞行器的机动性、敏捷性和制导控制精度。以所建立的质量矩拦截弹数学模型为基础,通过对模型合理的简化,得到一个耦合的非线性动力学系统,利用滑模控制设计了拦截弹飞行时的姿态控制系统,提出采用模糊逻辑算法抑制系统抖振的同时,把控制系统的多个设计目标转化为不等式约束,采用遗传算法优化控制参数,控制系统性能满足设计要求。仿真结果验证了这种方法的有效性。
As a novel method, mass moment control offers significant advantages over conventional aerodynamic control systems in applications such as the control of flight vehicles at extreme Mach numbers, where the aerodynamic heating can make it impractical to deploy control surfaces. Furthermore, it can meet the demands of the maneuverability, agility and the precision of guidance and control of flight vehicles. Based on the constructed model of mass moment interception missile, a coupled nonlinear system was proposed by rational simplification. In order to eliminate system chattering, attitude control system was developed via utilizing fuzzy sliding mode control approach, which satisfied the given performance indexes, and could be found by using genetic algorithm （GA） to optimize the controller parameters by converting design objectives into the inequality constraints. The simulation results justify the effectiveness of the method.
出处
《系统仿真学报》
EI
CAS
CSCD
北大核心
2008年第5期1274-1278,共5页
Journal of System Simulation
基金
国家自然科学基金项目(60434010)
关键词
质量矩拦截弹
姿态控制
滑模控制
模糊逻辑算法
遗传算法
mass moment interception missile
attitude control
sliding mode control
fuzzy algorithm
genetic algorithm
