基于自适应高阶滑模的直气复合控制律设计

对直接力/气动力复合控制导弹控制律设计问题做出了研究.建立了俯仰平面内姿态控制系统的数学模型，应用非线性理论分析模型，基于分析简化模型，建立了用于控制律设计的简化模型.利用自适应高阶滑模进行了虚拟控制量设计，考虑气动舵舵偏以及舵偏角速度的约束以及脉冲发动机的特点，建立二次规划最优化问题.利用有效集法实时分配虚拟控制量，获得气动舵以及脉冲发动机控制量.进行数字仿真验证控制律有效性，所设计控制律适应气动舵以及脉冲发动机特点，能对过载指令进行快速跟踪.

Adaptive Continuous Higher Order Sliding Mode Control for#br# Dual Aero/Propulsive Missile#br#

A controller design for missiles with blended lateral jets and aerodynamic is presented,The mathematical model of attitude control system in the pitch plane is constructed,and the nonlinear system theory is applied to analyze the mode. A virtual controller is designed using adaptive higher order sliding mode based on simplified mode.A constrained quadratic programming formulation is constructed considering the rate and position limits of rudder and characristic of reaction jets. Using active set methods, control allocation problem is solved.Simulation results show the effectiveness of the proposed design,which can suit the blend actuator and track the command of overload.