Integrated Approach combining Doppler Positioning and Celestial Navigation based on UKF

Paper number

IAC-06-B3.P.6.04

Author

Dr. Qi Zhenqiang, Beijing Aerospace Automatic Control Institute, China

Coauthor

Dr. Yang Zhaohua, Beijing University of Aeronautics and Astronautics, China

Year

2006

Abstract

In autonomous satellite celestial navigation system, the state model is founded according to the motion principle and the measurement model is founded according to the celestial measurement information. The satellite guidance parameters are gained by using advanced estimation filter methods. As an autonomous guidance method, only the angle information of celestial bodies is utilized in celestial navigation system, so the positioning precision is lower. But the anti-interference ability of the celestial navigation system is strong.

   On the other hand, limited by the geographic conditions, it is difficult for ground station wireless guidance system to realize the all orbit positioning and guidance. Moreover, with the development of the satellite application technology, the number of spacecrafts is increasing. The information transfering between the satellites and ground stations is also increasing acutely. So, the information jam and heavy burden is happened in ground station measurement system. Furthermore, the anti-interference ablity of the ground station guidance system is not strong.

   In this paper, a complex navigation method combining the celestial navigation system and the single-pass Doppler frequency shift positioning system is studied. Firstly, the angle information from celestial navigation system and the position information from the Doppler positioning system are filtered using the UKF respectively. Then, the resulting two sub-optimal estimation values of the state variables are fused by intelligence information fusion methods. During the process of information fusion, the dynamic information assigning factor, which is optimized by the immune genetic algorithm (IGA), is utilized to gain the global optimal estimation value of the state variable. Finally, the navigation and positioning accuracy of the system is promoted. The proposed navigation approach makes use of the measurement devices in the satellites and the ground station and integrates the advantages of the two navigation methods. The computer simulation results show that the proposed approach is valid and the navigation accuracy and fault-tolerant ability of the system are improved.

Abstract document

IAC-06-B3.P.6.04.pdf

Manuscript document

IAC-06-B3.P.6.04.pdf (🔒 authorized access only).

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