含攻击角度约束的三维制导控制一体化鲁棒设计方法
Robust design approach of three-dimensional integrated guidance and control containing impact angle constraints

针对具有攻击角度约束的STT飞行器对象, 提出了一种三维制导控制一体化鲁棒设计方法. 首先, 基于某 些可行性简化原则, 推导出面向三维制导控制一体化设计的非线性数学模型. 然后, 针对一类多变量非线性系统, 通过引入控制补偿项, 提出了一种鲁棒动态逆设计方法. 结合鲁棒动态逆和动态面控制方法, 完成了制导控制一体 化鲁棒算法的设计. 仿真结果表明, 所提出的三维制导控制一体化算法可保证飞行器的稳定飞行和精确制导, 并且 满足攻击角度的约束要求. 此外, 该方案具备针对参数不确定性和等效干扰的强鲁棒性能.
With regard to the slide-to-turn (STT) aircraft constrained by impact angles, a novel robust design approach for three-dimensional integrated guidance and control (3D-IGC) is put forward. Based on some feasible simplification principles, one nonlinear mathematical model facing to 3D-IGC design is first deduced. For a class of multi-variable nonlinear system, a robust dynamic inversion control (RDIC) method is proposed by introducing a type of control compensation term. Combined RDIC theory with dynamic surface control (DSC) method, the robust design of 3D-IGC law is finished. Simulation results present that, the proposed 3D-IGC law can guarantee the stable flight and accurate guidance of researched aircraft, and also satisfy the constrained condition of impact angles. Furthermore, it possesses strong robust property against system uncertainties and equivalent disturbances.