电光与控制, 2016, 23 (7): 11, 网络出版: 2021-01-26
发射惯性系下GPS/SINS组合导航方法研究
GPS/SINS Integrated Navigation in Launch Inertial Coordinate System
发射惯性系 组合导航 数字仿真实验 跑车实验 launch inertial coordinate system integrated navigation digital simulation vehicle experiment
摘要
针对弹道导弹的特点, 研究了在发射惯性坐标系下, 基于速度/位置的GPS/SINS组合导航算法, 给出了该坐标系下的捷联惯导误差方程, 建立了该坐标系下的GPS/SINS组合导航系统的状态方程和量测方程。数字仿真实验和跑车实验, 表明提出的发射惯性系下GPS/SINS组合导航算法有较高的导航精度。
Abstract
In view of the characteristics of ballistic missiles, the GPS/SINS integrated navigation algorithm based on speed/location in the launch inertial coordinate system is studied. The strapdown inertial navigation error equation is derived in this coordinates. The state equations and measurement equations for GPS/SINS integrated navigation system are established. The digital simulation and vehicle experiment indicate that this GPS/SINS integrated navigation algorithm can improve navigation accuracy effectively.
董亮, 陈帅, 韩乃龙. 发射惯性系下GPS/SINS组合导航方法研究[J]. 电光与控制, 2016, 23(7): 11. DONG Liang, CHEN Shuai, HAN Nai-long. GPS/SINS Integrated Navigation in Launch Inertial Coordinate System[J]. Electronics Optics & Control, 2016, 23(7): 11.