飞行数据相容性检验方法  

Method for Flight Data Compatibility Analysis

作　　者：李富刚[1] 张聪[1] 田福礼[1] 张喆[1] Li Fugang;Zhang Cong;Tian Fuli;Zhang Zhe(Flight Simulation Laboratory, Chinese Flight Test Establishment, Xi’an 710089, China)

机构地区：[1]中国飞行试验研究院飞行仿真实验室,西安710089

出　　处：《航空工程进展》2017年第4期479-485,共7页Advances in Aeronautical Science and Engineering

摘　　要：飞行试验测量数据中存在过程噪声和测量噪声,导致飞行数据之间不相容,国内目前常用的输出误差法不适用于耦合严重的直升机飞行数据相容性检验。采用增广卡尔曼滤波方法进行状态估计,大幅度地消除测量值中的误差;再用输出误差法对增广卡尔曼滤波估计的结果进行相容性检验,并将其应用于直升机四阶纵向等效模型辨识中。结果表明:提出的这种方法既解决了单独使用增广卡尔曼滤波进行数据相容性分析时由于初期收敛过程造成的滤波误差问题,又克服了单独使用输入误差法进行数据相容性时需手动修改时间延迟问题和测量值中误差过大时输出误差法无法收敛问题,使得检验效果与计算效率大幅提升。Process noises and measure noises exist in flight test data,which lead to incompatibility of flight data.The output error method that is the popular method used in flight test data compatibility checking recently is not fit for helicopter model data compatibility checking with serious coupling.Extended Kalman filter is applied for states estimation and error in the measured value is eliminated drastically.Compatibility analysis for results of extended Kalman filter is carried on by way of output error method.This technology is used in the fourth order liner equivalent model identification of helicopter longitudinal.By this technology,problems of wave filtering errors which are caused by extended Kalman filter primary convergence are solved,and problems of time delay modification by hand in output error method is conquered and non convergence of output error method when errors in measuring data are big is solved,respectively.Verification effect and computational efficiency are greatly improved.

关 键 词：增广卡尔曼滤波 相容性检验 飞行试验 状态估计 

分 类 号：V217[航空宇航科学与技术—航空宇航推进理论与工程]