基于全局收敛多维牛顿迭代法的飞行配平算法研究  

Flight trim algorithm based on global-convergence multi-dimensional Newton iteration

作　　者：吴成富[1] 程鹏飞[1] 段晓军[1] 郭月[2] 

机构地区：[1]西北工业大学无人机特种技术重点实验室,西安710065 [2]西北工业大学自动化学院,西安710072

出　　处：《计算机应用研究》2015年第1期56-58,97,共4页Application Research of Computers

基　　金：国家自然科学基金资助项目(61201320);解放军总装预研项目(513250202)

摘　　要：研究全局收敛数值方法以此来解决机翼不对称损伤无人机的飞行配平问题。首先,提出解决此特殊构型飞机配平问题的多维牛顿迭代方法和其全局收敛性证明方法;其次,简要分析机翼损伤对质量特性和气动特性的影响,推导适合数值求解的配平方程并依其原理给出选取飞行配平初始点的方法;最后,给出了左翼损失40%面积矩某小型电动无人机(SEPUAV)的配平结果,并通过对比讨论其优劣性。仿真结果表明,当保证全局收敛时,该方法不仅解决了迭代初值点选取困难问题,而且能够快速地给出一般构型飞机(如机翼不对称损伤飞机)的纵侧向飞行配平点集,提高飞行配平的实时性和通用性。This paper mainly presented the global-convergence numerical method for solving flight trim of Wing damaged asym- metric UAV. First, it gave multidimensional Newton iteration accompanied with the strict proof of its global convergence. Then, it briefly introduced the properties of mass and aerodynamics of damaged aircraft. Next it established the equations of flight trim for numerical solution and discussed how to choose initial points. Finally, it gave the simulation results of flight trim for discussing about the pros and cons of this method. The results show that under the global convergence, this method can on- ly resolve the problem of choosing iteration＇ s initial points, but also quickly work out longitudinal / lateral trim point sets of aircraft in general configuration （such as wing damaged asymmetric aircraft）. So it improves versatility and real-time perform- ance of flight trim.

关 键 词：损伤无人机 飞行配平 多维牛顿迭代法 全局收敛 迭代初值点 

分 类 号：TP301.6[自动化与计算机技术—计算机系统结构]