摘要
针对战术导弹高过载、大动态范围的测试要求,设计了无陀螺微惯性测量组合电路。无陀螺微惯性测量组合电路采用了十加速度计的配置方案,可以直接解算得到战术导弹的角速度,因而只需要1次积分就可以得到角度,减小了累积误差。电路选用高精度的单轴加速度计,提高了测试精度,并以CPLD作为中心逻辑控制单元,实现了对多加速度计信号的采集和存储,可以为战术导弹的角速度解算提供稳定可靠的数据。
Aiming at the high overload and the dynamic range of test requirements for tactical missile, design non-gyro micro inertial measurement unit circuit. Non-gyro micro inertial measurement unit circui based on a ten-accelerometer configuration, can be directly calculate the angular velocity of tactical missile, so it can gain angle through one integral, reducing the accumulative errors. The circuit selects high-precision single-axis accelerometer to improve the accuracy of the test, and uses CPLD as the central control unit to achieve a multi-accelerometer signal acquisition and storage, provide stable and reliable data for the calculating of angular velocity. It introduces the non-gyro micro inertial measurement unit circuit principle of work, the system composition and the hardware design in detail.
出处
《电子测量技术》
2009年第1期43-45,共3页
Electronic Measurement Technology
基金
多加速度计和地磁传感器测试弹丸姿态的技术研究(9140A17080307BQ0409)
