中国空间科学技术

中国空间科学技术 ›› 2015, Vol. 35 ›› Issue (2): 9-.doi: 10.3780/j.issn.1000-758X.2015.02.002

• 研究探讨 • 上一篇    下一篇

发射系下SINS/GPS/CNS多组合导航系统算法及实现

潘加亮，熊智，赵慧，郁丰，王丽娜   

  1. （1 南京航空航天大学导航研究中心，南京 210016）（2 南京航空航天大学航天学院，南京 210016）（3 北京航天自动控制研究所，北京 100854）
  • 出版日期:2015-04-25 发布日期:2015-04-25

SINS/GPS/CNS Multi-integrated Navigation System Algorithm inLaunch Inertial Coordinate System and Realization

PAN Jialiang，XIONG Zhi，ZHAO Hui， YU Feng，WANG Lina   

  1. (1Navigation Research Center, Nanjing University of Aeronautics and Astronautics, Nanjing 210016) (2 College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016)(3 Beijing Aerospace Automatic Control Institute, Beijing 100854)
  • Published:2015-04-25 Online:2015-04-25

PDF (PC)

1642

被引次数

2

摘要： 首先建立了发射惯性系下的组合导航系统模型，据此设计了基于联邦滤波器的SINS/GPS/CNS组合导航算法，最后研制了基于PC104硬件平台的组合导航算法验证样机。通过实时半物理仿真测试得出，三组合导航系统的姿态误差小于15″，位置误差小于10m,速度误差小于0.2m/s,表明所设计的组合导航系统算法正确，实现合理。

关键词: 发射惯性系, 组合导航, 系统实现, 硬件平台

Abstract: A single integrated navigation system cannot meet the long-endurance high precision requirement of space long-range missile, so a SINS/GPS/CNS multi-integrated navigation system in launch inertial coordinate system was designed. Firstly, an integrated navigation model was built in the launch inertial coordinate system. Secondly, a SINS/GPS/CNS integrated navigation algorithm based on the federal Kalman filter was designed. Finally, an integrated navigation algorithm verification prototype based on PC104 was developed. Through the real time semi-physical simulation tests, the attitude error of triple integrated navigation system is below 15″, the position error is below 10m and the velocity error is below 0.2m/s. It indicates that the integrated navigation system algorithm designed is right and the realization of the system is reasonable.

Key words: Launch inertial coordinate system, Integrated navigation, System realization, Hardware platform