摘要
为了验证GPS/GLONASS定位系统用于弹道导弹的导航效果,文中对其进行了仿真计算。首先获取了GPS/GLONASS定位信息接收系统的地面静态偏差信息,将地面静态偏差作为实时导航的关机点参数修正误差,接着解算弹道求落点偏差,得到了地面静态偏差引起导航误差的大小。
The paper verifies navigation effect of GPS/GLONASS orientation system used in ballistic missile by simulation calculation. First, ground static deviation information of GPS/GLONASS orientation system is get and is regarded as modification error of shut down point parameters while real-timely navigating, then the impact deviation is gained by calculating trajectory , that is navigation error caused by ground static deviation is get.
出处
《弹箭与制导学报》
CSCD
北大核心
2007年第2期94-96,99,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
