一种无陀螺捷联惯导的九加速度计测姿方法  

Nine-accelerometer attitude determination method for gyroscope free strap-down inertial navigation system

作　　者：王东江 杨新民[1] 

机构地区：[1]南京理工大学瞬态物理国家重点实验室,南京210000

出　　处：《电子测量技术》2017年第10期70-74,共5页Electronic Measurement Technology

摘　　要：通过对无陀螺捷联惯导系统的姿态测量原理进行分析,为了从工程安装角度提出一种简易的实现无陀螺捷联惯导的九加速度计安装方式,首先对该九加速度计配置方案的简易性和合理性进行了理论分析。基于捷联惯导原理对这种九加速度计安装方式的计算原理进行了数学推导,详细论述并计算了该无陀螺捷联惯导的实现算法,从而最终得出了该九加速度计配置方式可行的结论。与此同时对该九加速度计无陀螺惯导系统建立了角加速度和线加速度的数学模型,在假设没有随机白噪声和常值误差等测量误差的前提下对其进行了MATLAB仿真,给出了该系统的角速度和角速度误差值从而再次佐证了这种九加速度计的配置方式简易可行。Based on the gyro free strap-down inertial attitude measurement principle of missile system is analyzed.From the point of view of engineering installation,this paper puts forward a kind of simple installation method of the nine accelerometer which can realize the gyro free strap-down inertial navigation system.The simplicity and rationality of the nine accelerometer configuration scheme are analyzed.The calculation principle of the guiding principle of installation of the nine acceleration are deduced based on the detailed calculation of the algorithm of GFSINS,which proves the feasibility of the nine accelerometer configuration.Finally,the mathematical model of angular acceleration and linear acceleration is established.On the assumption that there is no random white noise and constant error,through the MATLAB simulation,the angular velocity and angular velocity error of the system are given,and it is proved that the configuration of the nine accelerometer is simple and feasible.

关 键 词：无陀螺捷联惯导 九加速度计 姿态测量 姿态解算 

分 类 号：V249.322[航空宇航科学与技术—飞行器设计]