一种考虑交叉耦合效应的飞翼布局飞机控制分配方法 -- 西北工业大学,2014,32(1):69-74
论文:2014,Vol:32,Issue(1):69-74
引用本文:
徐明兴, 祝小平, 周洲, 王怿, 张波. 一种考虑交叉耦合效应的飞翼布局飞机控制分配方法[J]. 西北工业大学
Xu Mingxing, Zhu Xiaoping, Zhou Zhou, Wang Yi, Zhang Bo. A Control Allocation Method for Flying Wing Aircraft with Control Effector Interactions Considered[J]. Northwestern polytechnical university

一种考虑交叉耦合效应的飞翼布局飞机控制分配方法
徐明兴1, 祝小平2, 周洲1, 王怿1, 张波1
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
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。
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   
A Control Allocation Method for Flying Wing Aircraft with Control Effector Interactions Considered
Xu Mingxing1, Zhu Xiaoping2, Zhou Zhou1, Wang Yi1, Zhang Bo1
1. Science and Technology on UAV Laboratory, Northwestern Polytechnical University, Xi'an 710072, China;
2. UAV Research Institute, Northwestern Polytechnical University, Xi'an 710072, China
Abstract:
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 certain error. Sequential linear programming can solve the problem of considering the control interactions,but its performance 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.
Key words:    aircraft    attitude control    control surfaces    errors    linear programming    matrix algebra    MATLAB    rudders    control allocation    control effector interactions    flying wing aircraft    sequential linear programming    split-rudder   
收稿日期: 2013-04-18     修回日期:
DOI:
基金项目: 国家自然科学基金(11302178);西北工业大学基础研究基金(JCT20130110)资助
通讯作者:     Email:
作者简介: 徐明兴(1986-),西北工业大学博士研究生,主要从事飞行器飞行动力学、制导与控制的研究。
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