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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 major difficulties encountered when using micromechanical gyroscopes for the measurement of rocket projectile attitude angles is that the rocket launchers require a short time between the receipt of a launch order and their launch, which takes only a few seconds. The micromechanical gyro from the cold to the heat balance generally takes a few minutes to ten minutes, so the gyro must be compensated for thermal drift. In this paper, the initial drift of the micromechanical gyroscope is studied, the mathematical model of the initial drift of the micromechanical gyroscope is established, and the recursive formula is given. Experimental results show that the method presented in this paper can model the initial drift of the micromachined gyroscope using the data of a few seconds before launch and accurately predict the drift after launch.