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2018 | OriginalPaper | Chapter

18. Integration of Baro-Inertial-GPS Altimeter via Complementary Kalman Filter

Authors : Alberto Mañero Contreras, Chingiz Hajiyev

Published in: Advances in Sustainable Aviation

Publisher: Springer International Publishing

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Abstract

The objective of integrated navigation systems is to estimate the navigation states reliability, which includes position and velocity of the aircraft, from the inertial measurements and the external aids despite the possible occurrence of devices faults. In this study three different integrated systems have been studied without taking into consideration any faulty case: integrated baro-inertial (IBI), integrated inertial-GPS (IIG) and integrated baro-inertial-GPS (IBIG). IBI and IIG navigation systems have been designed using a complementary Kalman filter (CKF), which estimates the error model parameters. Simulation results show that fluctuations for IIG altimeter errors are the largest ones for the three altimeters. The second largest errors are acquired by IBI altimeter and finally, the best results are obtained by the fused IBIG altimeter.

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Metadata
Title
Integration of Baro-Inertial-GPS Altimeter via Complementary Kalman Filter
Authors
Alberto Mañero Contreras
Chingiz Hajiyev
Copyright Year
2018
Book
Advances in Sustainable Aviation

Print ISBN: 978-3-319-67133-8

Electronic ISBN: 978-3-319-67134-5

Copyright Year: 2018

DOI
https://doi.org/10.1007/978-3-319-67134-5_18

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