弹载滚转稳定平台相对转角测量电路设计

提高常规高旋弹药飞行姿态参数测量精度的难点是如何解决惯性器件量程与精度互相矛盾的问题。采用滚转稳定平台能够解决弹体高旋对惯性器件量程的影响，能够采用小量程、高精度的陀螺仪测量弹体的飞行姿态参数。然而滚转稳定平台的惯性测量组合与弹体之间有相对转动，此时惯性测量组合所测参数并不是弹体的飞行参数，需要一个能够测量相对转角的装置才能得到弹体完整的飞行姿态参数。针对此问题，本文利用增量式光电编码器设计相对转角测量电路，并对增量式光电编码器在实际应用过程中出现的问题进行了研究，最后通过三轴飞行仿真转台试验进行验证。试验证明，该相对转角测量电路具有一定的可行性和有效性，能够有效测量惯性测量组合与弹体之间的相对转角，具有一定的工程应用价值。

The relative angle measurement circuit design of stable roll platform for missile

The difficulty to improve the measurement precision of attitude parameter for conventional high-spin munitions is how to solve the conflicting issues between range and precision of inertial devices. Roll stable platform can diminish the impact of high spin projectile on range of inertial devices and can measure flight attitude parameters by gyro that is small-scale and high-precision. However, there is a relative rotation between the IMU and missile roll stabilized platform. Inertial measurement parameters that are not flying projectile need a device of measuring the relative angle to get the complete missile flight attitude parameters. In order to solve the problem, the paper designed relative angle measuring circuit by an incremental optical encoder and made research on some problems of incremental photoelectric encoder in the actual application process, and finally verified by the three-axis flight simulator tests. Tests show that the relative angle measurement circuit that is feasible and effective can measure effectively the relative angle between IMU and projectile and has a certain value in engineering.