INS/GPS组合系统初始滚转角空中粗对准方法  

Roll Angle In-flight Initial Alignment Method of INS/GPS Integrated System

作　　者：屈新芬[1] 李世玲[1] 徐林[1] 

机构地区：[1]中国工程物理研究院电子工程研究所,四川绵阳621900

出　　处：《探测与控制学报》2015年第4期58-61,共4页Journal of Detection & Control

基　　金：国家联合基金项目资助(U1330133);行业预研项目资助(0203090211)

摘　　要：针对惯性/卫星(INS/GPS)组合系统空中动态启动下初始滚转角给定依赖外部测量或弹道滚转角必须可预测的问题,提出了基于GPS测量信息和INS测量加速度信息的INS/GPS组合系统的空中动态初始滚转角粗对准的方法。该方法利用GPS接收机测量速度和INS中加速度计测量加速度信息直接解算初始滚转角,充分利用了这两类信息测量精度较高的优点,且算法简单、计算量小、粗对准需要的信息量少和时间短,不需要增加外部传感器。试验结果分析表明,该方法对载体动态运动滚转角粗对准的精度受到载体运动加加速度大小、载体运动攻角和侧滑角大小的影响。为了提高系统的适应性和精度,必须进一步采用高精度非线性模型及滤波算法进行精对准。Aiming at the problems of in-flight initial alignment of the dynamic roll angle for INS/GPS integrated navigation system relying on external measurement or trajectory must be predicable, a dynamic roll angle in-flight initial alignment method based on only GPS infmation and INS acceleration was proposed. This method used the velocity raeasured by GPS receiver and the acceleration measured by accelerator to calculate the in-flight dynamic roll angle directly, it was sim- ple and fast, meanwhile large amount of calculation and datum are unn^essary, external sensors are unnecessary.

关 键 词：捷联惯性导航系统 初始对准 GPS 加速度 

分 类 号：U666.1[交通运输工程—船舶及航道工程]