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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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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1724381918820040704 |