摘要
本文采用最优估计方法——信息平方根滤波和平滑算法,利用飞行数据对J-7原型机安装的92/BJ311型风标式迎角传感器的迎角测量误差进行了估计,给出了飞行迎角的校准公式。状态估计系统方程采用六自由度非线性方程。飞行动作采用推拉机动方法.飞行试验结果与风洞值进行了比较分析,证明飞行试验获得的误差修正系数和零偏误差是合理的。
A method of estimating angle of attack and its measurement error is presented in this paper. The algorithm uses an information square root filter and smooth method (ISRF/S). Flight test aircraft is a prototype J-7 with a sensor of angle of attack (92/BJ311) on nose boom. System equations use a set of six degree nonlinear kinematic equations. Control inputs employed during the flight test were roller costs. Flight test results were compared with wind tunnel test and analyzed. The comparison shows that the error factors and biases of angle of attack obtained from flight test were reasonable.
出处
《飞行力学》
CSCD
北大核心
1991年第2期56-62,共7页
Flight Dynamics
关键词
状态估计
参数辨识
迎角
飞机
state estimation
paramater identification
calibration of angle of attack
