摘要
传统的组合导航仿真算法采用位置、速度信息组合模式,由于计算误差和测量误差的存在,导致结果误差偏大。本文针对轨道机动飞行器的特点,通过STK卫星仿真软件分别模拟GPS卫星星历及机动飞行器从初始轨道向目标轨道过渡真实轨迹,采用基于伪距、伪距率的SINS/GPS紧密组合导航系统对飞行器转移过程进行数学仿真计算。结果表明,基于伪距/伪距率组合导航方法,不仅可以修正惯性元件的常值漂移,并且对轨道转移段的速度、位置误差有很好的估计,获得较高的导航精度。
Traditional integrated navigation simulation algorithm using position and velocity information combination because of the existence of calculation error and the error of measurement results lead to big error. In this paper,according to the characteristics of the orbital maneuver flight,by the simulation software STK satellite respectively simulated GPS satellite ephemeris and motor vehicle real trajectories of transition to target trajectory from the initial orbit,based on pseudorange and pseudorange rate SINS/GPS integrated navigation system for vehicle transfer process in mathematical simulation calculation,results show that the integrated navigation method based on pseudorange/pseudorange rate not only can be fixed constant drift of inertial components,and speed,the position error of orbit transfer period has a very good estimate,higher navigation accuracy.
出处
《飞机设计》
2015年第6期8-14,38,共8页
Aircraft Design
关键词
伪距
伪距率
组合导航
仿真
pseudorange
pseudorange rate
integrated navigation
simulation
