This paper summarizes the flight evaluation of the DGPS-INS hybrid navigation system conducted as a preliminary study for constructing a next-generation navigation system at the National Aerospace Laboratory (NAL). First, the configuration used in the flight experiments, including ground facilities and the measurement systems, is described. Secondly, the design concept for a method of estimating navigation errors using a Kalman filter is presented. Thirdly, flight profiles employed in the experiments are defined, and the experimental results of GPS, DGPS, INS in both stand-alone and hybrid modes which correspond to each profile are shown. Also, improvement in navigation performance by introducing the DGPS-INS hybrid navigation system available for future space vehicles has been successfully completed.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    A Preliminary Evaluation Test of GPS/DGPS Navigation System

    Ishikawa, Kazutoshi / Murata, Masaaki / Ono, Takatsugu et al. | SAE Technical Papers | 1994


    Current Status of Flight Evaluation of DGPS-INS Hybrid Navigation System at NAL

    Shingu, H. / Murata, M. / Ono, T. et al. | British Library Conference Proceedings | 1994



    Flight Evaluation of the DGPS-INS Hybrid Navigation System for Category III Automatic Landing

    Harigae, M. / Murata, M. / Tsujii, T. et al. | British Library Conference Proceedings | 1996


    Flight Evaluations of Carrier DGPS/INS Hybrid Navigation for Automatic Landing

    Harigae, M. / Tsujii, T. / Ono, T. et al. | British Library Conference Proceedings | 1998