一种大动态惯导技术在旋转弹上的仿真与实验研究  

The Simulation and Experiment Research of Inertial Navigation System Used for Shell in High Dynamic Environment

作　　者：王磊[1] 郝永平[1] 肖长[1] 韩政达[2] 

机构地区：[1]沈阳理工大学微系统技术中心,沈阳110168 [2]北京航空航天大学机械工程与自动化学院,北京100191

出　　处：《弹箭与制导学报》2009年第2期4-8,共5页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：总装备部基金资助

摘　　要：针对大动态环境下旋转弹的特点,在无陀螺惯性测量系统的基础上,采用一种基于MEMS双陀螺多加速度计的捷联惯导方案。该方案可以克服单纯加速度计的惯导方案对加速度测量和安装精度的苛刻要求,实现对弹轴方向角速度的解算。计算机仿真结果表明,导航解算的误差可以满足旋转弹的精度要求。在仿真分析基础上,给出了一种面向炮弹系统,基于FPGA双核处理器结构惯导系统的硬件实现方案。According to the character of shell, a scheme of MEMS＇ two- gyroscope and multi-accelerometer configuration is proposed along with its mathematic model based on the conventional gyroscope free strap-down inertial navigation system（DF SINS） theory. Compared with DF SINS, the scheme could calculate the accurate angular velocity of rotary axis in condition of low measuring and fixing accuracy for the accelerometer. Simulation results show that the computational accuracy of navigation system can be satisfied with the demand of shell. In addition, a concrete realization project of hardware based on FPGA, dual core processor＇s navigation system used for shell is introduced.

关 键 词：大动态 无陀螺捷联惯导系统 姿态角速度 双核系统 FPGA 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程] V249.322[航空宇航科学与技术—飞行器设计]