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2017•Unpublished venueRequires access

Full-dimension attitude determination based on two-antenna GPS/SINS integrated navigation system

Lifan Zhang, Deqiang Han, Jean Dezert

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Abstract

A practical method for full-dimension attitude determination based on the combination of two-antenna global positioning system (GPS) and strapdown inertial navigation system (SINS) is presented. In view of the fact that two-antenna GPS can only provide two attitude angles using carrier phase difference measurements, not all of the SINS attitude errors can be directly corrected by the integrated navigation system. The proposed method makes use of the coordinate transformation about the attitude and the related measurements provided by two-antenna GPS and SINS to solve the full-dimension attitude determination problem through information fusion. The simulation results indicate that the proposed method can effectively determine the required attitude in real time.

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What this paper is about

A practical method for full-dimension attitude determination based on the combination of two-antenna global positioning system (GPS) and strapdown inertial navigation system (SINS) is presented. In view of the fact that two-antenna GPS can only provide two attitude angles using carrier phase difference measurements, not all of the SINS attitude errors can be directly corrected by the integrated navigation system. The proposed method makes use of the coordinate transformation about the attitude and the related measurements provided by two-antenna GPS and SINS to solve the full-dimension attitude determination problem through information fusion. The simulation results indicate that the proposed method can effectively determine the required attitude in real time.

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Available abstract

A practical method for full-dimension attitude determination based on the combination of two-antenna global positioning system (GPS) and strapdown inertial navigation system (SINS) is presented. In view of the fact that two-antenna GPS can only provide two attitude angles using carrier phase difference measurements, not all of the SINS attitude errors can be directly corrected by the integrated navigation system. The proposed method makes use of the coordinate transformation about the attitude and the related measurements provided by two-antenna GPS and SINS to solve the full-dimension attitude determination problem through information fusion. The simulation results indicate that the proposed method can effectively determine the required attitude in real time.

Key concepts: Global Positioning System, Dimension (graph theory), Computer science, Antenna (radio), Telecommunications, Mathematics, Pure mathematics

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