摘要
将微机械陀螺用于火箭炮弹姿态角的测量时 ,遇到的一个主要困难是火箭炮从接到发射指令到实施发射的时间间隔很短 ,大约只有几秒钟。而微机械陀螺从冷态到热平衡一般需要几分钟到十几分钟 ,因此必须对陀螺的热漂移进行补偿。本文研究了微机械陀螺的初始漂移 ,建立了微机械陀螺的初始漂移的数学模型 ,并给出了计算的递推公式。实验结果表明 ,本文给出的方法可以利用发射前的几秒钟的数据对微机械陀螺的初始漂移进行建模 ,并且能对发射后的漂移进行准确预报。
One of the principle difficulties in the application of micromachined gyro to the measurement of the attitude of projectile shells is that the time interval between launch instruction and the actual shooting is too short,about several seconds, while it needs for several minutes to more than ten minutes for a gyro to reach the thermal equilibrium.So the initial drift must be compensated before the gyro can be applied to the measuring of the attitude.This paper presents the study of the initial drift and the modelling of it.A recursive method for identifying the model is also given.The experiment results show that the method presented in this paper can model the initial drift with the data acquired within several seconds before the launch and the model can well predict the drift after the launch.
出处
《中国惯性技术学报》
EI
CSCD
2000年第1期59-62,共4页
Journal of Chinese Inertial Technology
