Application of GPS-INS-STAR integrated navigation system in spacecraft

Details Application of GPS-INS-STAR integrated navigation system in spacecraft Application of GPS-INS-STAR integrated navigation system in spacecraft

Oct 1988

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1988acaas...9..448z&link_type=abstract

Acta Aeronautica et Astronautica Sinica (ISSN 1000-6893), vol. 9, Oct. 1988, p. B448-B453. In Chinese, with abstract in English.

Computer Science

Performance

Celestial Navigation, Global Positioning System, Inertial Navigation, Satellite Navigation Systems, Space Navigation, Block Diagrams, Computerized Simulation, Kalman Filters, Star Trackers, Strapdown Inertial Guidance

Scientific paper

In this paper the spacecraft stellar-inertial system is briefly reviewed. In order to generate high grade translational and rotational information of the spacecraft, a concept of GPS-INS-STAR optimal integrated navigation system is studied. The problems discussed include system composition, design philosophy, performance analysis, inertial measurement unit redundancy management techniques, and Kalman filter configuration. Computer simulation results show that this approach would lead to an accurate, autonomous, cost-effective and fault-tolerant navigation system.

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