Authors: Chingiz Hajiyev; Deniz Burak Kamiloğlu
Addresses: Istanbul Technical University (ITU), Faculty of Aeronautics and Astronautics, 34469, Maslak, Istanbul, Turkey ' Istanbul Technical University (ITU), Faculty of Aeronautics and Astronautics, 34469, Maslak, Istanbul, Turkey
Abstract: Inertial navigation systems (INSs) require some type of aiding and updating in the long term to remain valid. In many applications for purpose of INSs error compensation its integration by GPS is preferred. In this study, the Kalman filter-based loosely-coupled integrated INS/GPS is designed and investigated on the Boeing-747 aircraft model. The INS errors are modelled, estimated and compared with integrated navigation system errors which are position, velocity and attitude for each axis. The proposed integrated navigation system has high accuracy than stand-alone INS and it provides more reliable navigation information.
Keywords: integrated navigation system; inertial navigation system; INS; Kalman filter; GPS; loosely-coupled integrated INS/GPS.
International Journal of Sustainable Aviation, 2018 Vol.4 No.3/4, pp.163 - 177
Received: 14 Apr 2018
Accepted: 27 Sep 2018
Published online: 13 Mar 2019 *