飞行器静操纵性评估方法研究  

Research on vehicle static control performance evaluation approach

作　　者：程艳青[1] 王文正[1] 钱炜祺[1] 何开锋[1] 

机构地区：[1]中国空气动力研究与发展中心空气动力学国家重点实验室,四川绵阳621000

出　　处：《实验流体力学》2011年第2期13-16,40,共5页Journal of Experiments in Fluid Mechanics

基　　金：空气动力学国家重点实验室基金资助(SKLA2009A0103)

摘　　要：建立了一种基于优化思想的配平舵偏求解方法,在此基础上对飞行器静操纵性进行了评估。具体采用三通道线性叠加模型,结合多维线性插值和牛顿-拉夫森算法,对大量的飞行器风洞试验数据进行处理,快速准确地求解出各个状态下的配平舵偏。与传统求解方法相比,该方法求解精度不受搜索间隔限制,求解时间大大缩短。通过对求解结果进行分析,评估飞行器的静操纵性,提高了静操纵性的评估效率和准确性。An approach of trim rudder solution based on optimization method is established,and static control performance of a vehicle was evalued by this approach.Use three-channel linear superposition model,trim rudder deflection of various state is fastly and exactly solved by multi-dimensional linear interpolation and Newton-Raphson method with mass wind tunnel test data.Comparing with tranditional approach,accuracy is not restricted by search interval and less time is spent.By analysing result of trim rudder deflection of various state,static control performance is evaluated,and efficiency and accuracy of static control performance evaluation is greatly enhanced.

关 键 词：牛顿-拉夫森算法 静态操纵性 舵面效率 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]