Information Fusion Based on Complementary Filter for SINS/CNS/GPS Integrated Navigation System of Aerospace Plane

In order to solve the problems of heavy computational load and poor real time of the information fusion method based on the federated Kalman filter (FKF), a novel information fusion method based on the complementary filter is proposed for strapdown inertial navigation (SINS)/celestial navigation sys...

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Main Authors: Yanming Zhao, Gongmin Yan, Yongyuan Qin, Qiangwen Fu
Format: Article
Language:English
Published: MDPI AG 2020-12-01
Series:Sensors
Subjects:
Online Access:https://www.mdpi.com/1424-8220/20/24/7193
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spelling doaj-d49aedfb814d44bda2a17d40ef285b082020-12-16T00:03:56ZengMDPI AGSensors1424-82202020-12-01207193719310.3390/s20247193Information Fusion Based on Complementary Filter for SINS/CNS/GPS Integrated Navigation System of Aerospace PlaneYanming Zhao0Gongmin Yan1Yongyuan Qin2Qiangwen Fu3School of Automation, Northwestern Polytechnical University, Xi’an 710129, ChinaSchool of Automation, Northwestern Polytechnical University, Xi’an 710129, ChinaSchool of Automation, Northwestern Polytechnical University, Xi’an 710129, ChinaSchool of Automation, Northwestern Polytechnical University, Xi’an 710129, ChinaIn order to solve the problems of heavy computational load and poor real time of the information fusion method based on the federated Kalman filter (FKF), a novel information fusion method based on the complementary filter is proposed for strapdown inertial navigation (SINS)/celestial navigation system (CNS)/global positioning system (GPS) integrated navigation system of an aerospace plane. The complementary filters are designed to achieve the estimations of attitude, velocity, and position in the SINS/CNS/GPS integrated navigation system, respectively. The simulation results show that the proposed information fusion method can effectively realize SINS/CNS/GPS information fusion. Compared with FKF, the method based on complementary filter (CF) has the advantages of simplicity, small calculation, good real-time performance, good stability, no need for initial alignment, fast convergence, etc. Furthermore, the computational efficiency of CF is increased by 94.81%. Finally, the superiority of the proposed CF-based method is verified by both the semi-physical simulation and real-time system experiment.https://www.mdpi.com/1424-8220/20/24/7193aerospace planeintegrated navigationcomplementary filterinformation fusion
collection DOAJ
language English
format Article
sources DOAJ
author Yanming Zhao
Gongmin Yan
Yongyuan Qin
Qiangwen Fu
spellingShingle Yanming Zhao
Gongmin Yan
Yongyuan Qin
Qiangwen Fu
Information Fusion Based on Complementary Filter for SINS/CNS/GPS Integrated Navigation System of Aerospace Plane
Sensors
aerospace plane
integrated navigation
complementary filter
information fusion
author_facet Yanming Zhao
Gongmin Yan
Yongyuan Qin
Qiangwen Fu
author_sort Yanming Zhao
title Information Fusion Based on Complementary Filter for SINS/CNS/GPS Integrated Navigation System of Aerospace Plane
title_short Information Fusion Based on Complementary Filter for SINS/CNS/GPS Integrated Navigation System of Aerospace Plane
title_full Information Fusion Based on Complementary Filter for SINS/CNS/GPS Integrated Navigation System of Aerospace Plane
title_fullStr Information Fusion Based on Complementary Filter for SINS/CNS/GPS Integrated Navigation System of Aerospace Plane
title_full_unstemmed Information Fusion Based on Complementary Filter for SINS/CNS/GPS Integrated Navigation System of Aerospace Plane
title_sort information fusion based on complementary filter for sins/cns/gps integrated navigation system of aerospace plane
publisher MDPI AG
series Sensors
issn 1424-8220
publishDate 2020-12-01
description In order to solve the problems of heavy computational load and poor real time of the information fusion method based on the federated Kalman filter (FKF), a novel information fusion method based on the complementary filter is proposed for strapdown inertial navigation (SINS)/celestial navigation system (CNS)/global positioning system (GPS) integrated navigation system of an aerospace plane. The complementary filters are designed to achieve the estimations of attitude, velocity, and position in the SINS/CNS/GPS integrated navigation system, respectively. The simulation results show that the proposed information fusion method can effectively realize SINS/CNS/GPS information fusion. Compared with FKF, the method based on complementary filter (CF) has the advantages of simplicity, small calculation, good real-time performance, good stability, no need for initial alignment, fast convergence, etc. Furthermore, the computational efficiency of CF is increased by 94.81%. Finally, the superiority of the proposed CF-based method is verified by both the semi-physical simulation and real-time system experiment.
topic aerospace plane
integrated navigation
complementary filter
information fusion
url https://www.mdpi.com/1424-8220/20/24/7193
work_keys_str_mv AT yanmingzhao informationfusionbasedoncomplementaryfilterforsinscnsgpsintegratednavigationsystemofaerospaceplane
AT gongminyan informationfusionbasedoncomplementaryfilterforsinscnsgpsintegratednavigationsystemofaerospaceplane
AT yongyuanqin informationfusionbasedoncomplementaryfilterforsinscnsgpsintegratednavigationsystemofaerospaceplane
AT qiangwenfu informationfusionbasedoncomplementaryfilterforsinscnsgpsintegratednavigationsystemofaerospaceplane
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