RKF‐based fault tolerant integrated INS/radar altimeter

Abstract

In this study, the integrated navigation system, consisting of radio and inertial navigation system (INS) altimeters, is presented. INS and the radio altimeter have different benefits and drawbacks. The integration is achieved by using an indirect Kalman filter. Hereby, the error models of the navigators are used by the Kalman filter to estimate vertical channel parameters of the navigation system. In the open loop system, INS is the main source of information, and radio altimeter provides discrete aiding data to support the estimations. At the next step of the study, in case of abrupt faults, the performance of the integrated system is examined. The optimal Kalman filter reacts with abnormal estimates to this situation as expected. To recover such a possible malfunctioning, the robust Kalman filter algorithm is suggested.

Citation

Hajiyev, C. and Saltoglu, R. (2004), "RKF‐based fault tolerant integrated INS/radar altimeter", Aircraft Engineering and Aerospace Technology, Vol. 76 No. 1, pp. 38-46. https://doi.org/10.1108/00022660410514991