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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。
The traditional integrated navigation simulation algorithm uses position and velocity information combination mode, which leads to large error of result due to calculation error and measurement error. In this paper, according to the characteristics of orbital maneuvering vehicle, the real trajectory of GPS satellite ephemeris and maneuvering vehicle from initial orbit to target orbit is simulated by STK satellite simulation software respectively. By using SINS / GPS compact combined navigation system based on pseudorange and pseudo-range, Transfer process of mathematical simulation. The results show that based on the combination of pseudorange / range-rate combined navigation method, not only the constant drift of inertial element can be corrected, but also the estimation of velocity and position error of the orbit transfer section can be well estimated, and the navigation precision can be obtained.