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A novel SINS/CNS Integrated Navigation Method Using Model Constraints for Ballistic Vehicle Applications

Published online by Cambridge University Press:  11 July 2017

Dingjie Wang ,
Hanfeng Lv  and
Jie Wu
Dingjie Wang*
Affiliation:
(Staff Room of Flight Dynamics and Control, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, Hunan, 410073, China)
Hanfeng Lv
Affiliation:
(Staff Room of Flight Dynamics and Control, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, Hunan, 410073, China)
Jie Wu
Affiliation:
(Staff Room of Flight Dynamics and Control, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, Hunan, 410073, China)
*
(E-mail: wangdingjie11@nudt.edu.cn)
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Abstract

The major challenge of current Strapdown Inertial Naviagtion System/Celestial Navigation System (SINS/CNS) integrated systems is navigation accuracy degradation due to the failure to accurately estimate the accelerometer bias even when using stellar refraction information (e.g. the number of refraction stars is less than three). To solve this problem, this paper presents a new method for improving the accuracy of the traditional inertial-based integrated systems installed on ballistic vehicles. In an analogy with nonholonomic constraints in land navigation, this algorithm exploits the constraints that govern the motion of a ballistic vehicle in the free flight phase to obtain accelerometer bias observations. Improvements in dynamic equations are used to reduce the propagation of navigation errors, and high-rate virtual constraints are used to reduce the impact of bias errors. An information filter is devised to fuse the multi-rate observations from multiple sources, i.e. SINS, CNS and model constraints. The proposed method is also evaluated by long-range ballistic vehicle navigation simulations. The results indicate that the proposed constrained algorithm can address the degradation problem with remarkable accuracy improvements without adding extra sensors, enhancing the SINS-based navigation performance for ballistic applications.

Keywords

Strapdown Inertial Navigation System (SINS)Celestial Navigation System (CNS)Virtual ConstraintsStellar RefractionBallistic missile
Type
Research Article
Information
The Journal of Navigation , Volume 70 , Issue 6 , November 2017 , pp. 1415 - 1437
Copyright
Copyright © The Royal Institute of Navigation 2017 

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