A novel integrity monitoring method for slowly growing errors in inertial navigation system/global navigation satellite system integrated navigation system
Abstract An integrity monitoring of integrated navigation in the presence of slowly growing errors (SGEs) is proposed. SGEs with gradual growth over time are the worst category of latent failures. Tightly coupled inertial navigation system (INS)/Global Navigation Satellite System integration is pres...
| Main Authors: | , , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Wiley
2024-03-01
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| Series: | IET Radar, Sonar & Navigation |
| Subjects: | |
| Online Access: | https://doi.org/10.1049/rsn2.12488 |
| _version_ | 1827313783719067648 |
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| author | Shaohua Yang Xiaodong Zhang Guanjie Wang Rui Zhang Zhenwei Li |
| author_facet | Shaohua Yang Xiaodong Zhang Guanjie Wang Rui Zhang Zhenwei Li |
| author_sort | Shaohua Yang |
| collection | DOAJ |
| description | Abstract An integrity monitoring of integrated navigation in the presence of slowly growing errors (SGEs) is proposed. SGEs with gradual growth over time are the worst category of latent failures. Tightly coupled inertial navigation system (INS)/Global Navigation Satellite System integration is presented by taking INS errors, bias and drift of receiver clock, baro‐altitude, pseudo‐range errors and ionospheric errors into consideration. Based on the RTCA performance standards DO‐229 and DO‐384, the simplified multi‐filters solution separation is employed for fault detection and calculation of corresponding outputs. For the fault exclusion part, the authors introduce a post pseudo‐range residual and measurement averaging method that is designed to quickly and effectively address SGEs and large measurement noises. Furthermore, the authors have designed a reconstruction logic for the filters that guarantees the continuity of the civil aviation system by considering the variation of visible satellites and historical information. The simulation results demonstrate that the proposed approach satisfies the performance requirements for civil aviation of En‐route and is able to correctly exclude faults and respond quickly in the presence of different levels of SGEs and measurement noises. |
| first_indexed | 2024-04-24T22:22:08Z |
| format | Article |
| id | doaj.art-19e82bdd950e4091870d673eab55792b |
| institution | Directory Open Access Journal |
| issn | 1751-8784 1751-8792 |
| language | English |
| last_indexed | 2024-04-24T22:22:08Z |
| publishDate | 2024-03-01 |
| publisher | Wiley |
| record_format | Article |
| series | IET Radar, Sonar & Navigation |
| spelling | doaj.art-19e82bdd950e4091870d673eab55792b2024-03-20T05:06:46ZengWileyIET Radar, Sonar & Navigation1751-87841751-87922024-03-0118343444710.1049/rsn2.12488A novel integrity monitoring method for slowly growing errors in inertial navigation system/global navigation satellite system integrated navigation systemShaohua Yang0Xiaodong Zhang1Guanjie Wang2Rui Zhang3Zhenwei Li4School of Automation Northwestern Polytechnical University Xi'an ChinaNational Key Laboratory of Science and Technology on Aircraft Control FACRI Xi'an ChinaNational Key Laboratory of Science and Technology on Aircraft Control FACRI Xi'an ChinaSchool of Automation Southeast University Nanjing ChinaSchool of Automation Northwestern Polytechnical University Xi'an ChinaAbstract An integrity monitoring of integrated navigation in the presence of slowly growing errors (SGEs) is proposed. SGEs with gradual growth over time are the worst category of latent failures. Tightly coupled inertial navigation system (INS)/Global Navigation Satellite System integration is presented by taking INS errors, bias and drift of receiver clock, baro‐altitude, pseudo‐range errors and ionospheric errors into consideration. Based on the RTCA performance standards DO‐229 and DO‐384, the simplified multi‐filters solution separation is employed for fault detection and calculation of corresponding outputs. For the fault exclusion part, the authors introduce a post pseudo‐range residual and measurement averaging method that is designed to quickly and effectively address SGEs and large measurement noises. Furthermore, the authors have designed a reconstruction logic for the filters that guarantees the continuity of the civil aviation system by considering the variation of visible satellites and historical information. The simulation results demonstrate that the proposed approach satisfies the performance requirements for civil aviation of En‐route and is able to correctly exclude faults and respond quickly in the presence of different levels of SGEs and measurement noises.https://doi.org/10.1049/rsn2.12488aircraft navigationglobal positioning systemGNSS spoofinginertial navigationKalman filters |
| spellingShingle | Shaohua Yang Xiaodong Zhang Guanjie Wang Rui Zhang Zhenwei Li A novel integrity monitoring method for slowly growing errors in inertial navigation system/global navigation satellite system integrated navigation system IET Radar, Sonar & Navigation aircraft navigation global positioning system GNSS spoofing inertial navigation Kalman filters |
| title | A novel integrity monitoring method for slowly growing errors in inertial navigation system/global navigation satellite system integrated navigation system |
| title_full | A novel integrity monitoring method for slowly growing errors in inertial navigation system/global navigation satellite system integrated navigation system |
| title_fullStr | A novel integrity monitoring method for slowly growing errors in inertial navigation system/global navigation satellite system integrated navigation system |
| title_full_unstemmed | A novel integrity monitoring method for slowly growing errors in inertial navigation system/global navigation satellite system integrated navigation system |
| title_short | A novel integrity monitoring method for slowly growing errors in inertial navigation system/global navigation satellite system integrated navigation system |
| title_sort | novel integrity monitoring method for slowly growing errors in inertial navigation system global navigation satellite system integrated navigation system |
| topic | aircraft navigation global positioning system GNSS spoofing inertial navigation Kalman filters |
| url | https://doi.org/10.1049/rsn2.12488 |
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