一种考虑交叉耦合效应的飞翼布局飞机控制分配方法  

A Control Allocation Method for Flying Wing Aircraft with Control Effector Interactions Considered

作　　者：徐明兴[1] 祝小平[2] 周洲[1] 王怿[1] 张波[1] 

机构地区：[1]西北工业大学无人机特种技术重点实验室,陕西西安710072 [2]西北工业大学无人机所,陕西西安710072

出　　处：《西北工业大学学报》2014年第1期69-74,共6页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(11302178);西北工业大学基础研究基金(JCT20130110)资助

摘　　要：大展弦比飞翼布局飞机采用开裂式方向舵进行航向与阻力控制,开裂式方向舵大张角情况下与临近舵面间存在舵效的交叉耦合。交叉耦合力矩非线性特性突出,采用基于线性模型的控制分配方法会产生一定的分配误差。序列线性规划法可以解决考虑交叉耦合效应的分配问题,但对耦合力矩数学形式要求严格且求解需进行多次线性规划,实时性较差。给出了一种基于补偿的线性规划法,该方法的用舵量要大于序列线性规划法,但实时性要明显好于序列线性规划法且对交叉耦合力矩的数学形式没有固定要求。For flying wing aircraft with large ratio, split-rudder is used for pitch and drag control; this leads to the occurrence of control effector interactions between the split-rudder and adjacent control surface. As the nonlinear characteristics of interaction moment is prominent, control allocation methods based on linear model produce a cer- tain error. Sequential linear programming can solve the problem of considering the control interactions, but its per- formance highly relies on the mathematical form of interaction moment and the solving process requiring multiple linear programming may lead to a poor real-time performance. In this paper, a method based on compensation and linear programming is given. This method needs a greater control input, but real-time performance is significantly better than Sequential linear programming, and the mathematical form of interaction moment is relaxed.

关 键 词：飞翼布局飞机 开裂式方向舵 交叉耦合 控制分配 序列线性规划 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]