CAJ | 학술논문

飞行器竖立在发射阵地时，会受到阵风的干扰产生振动，从而影响惯性平台的标定精度。为了更好发辨识阵风干扰下的平台漂移误差系数，根据弹体结构力学原理选用了达文波特（Davenport）阵风模型计算出了飞行器在一定风速下的最大振幅，并将振动理想化为欠阻尼振动进行建模。将这个振动加入平台漂移误差建模的过程中。通过建立起平台欧拉角变化率与漂移角速率建立描述平台漂移的状态空间方程，将误差系数看作状态变量，利用扩展卡尔曼滤波算法进行辨识。辨识效果图显示参数收敛速度快且趋于稳定，在加入随机噪声的情况下计算3组数据，得出稳定、可信的结果。
비행기수립재발사진지시，회수도진풍적간우산생진동，종이영향관성평태적표정정도。위료경호발변식진풍간우하적평태표이오차계수，근거탄체결구역학원리선용료체문파특（Davenport）진풍모형계산출료비행기재일정풍속하적최대진폭，병장진동이상화위흠조니진동진행건모。장저개진동가입평태표이오차건모적과정중。통과건립기평태구랍각변화솔여표이각속솔건립묘술평태표이적상태공간방정，장오차계수간작상태변량，이용확전잡이만려파산법진행변식。변식효과도현시삼수수렴속도쾌차추우은정，재가입수궤조성적정황하계산3조수거，득출은정、가신적결과。
When a missile erected, it will be affected by the gust wind. The resulting vibration can influence the precision of the platform. In order to identify the error parameters better, the maximum amplitude is calculated using the Davenport wind model according to missile mechanics, and the vibration is idealized to be under damping vibration. The vibration is incorporated into the modeling of the INS platform. The state space equations to describe the platform drift are established with the Euler angle change rate and drift angular rate of a platform. The error coefficient is seen as the state variables and is identified with extended Kalman filter. The coefficient identification figure shows that convergence is fast and stable. Three groups of data are calculated in condition of adding into random white noise, and its result is relatively stable and reliable.