Simulation Platform for SINS/GPS Integrated Navigation System of Hypersonic Vehicles Based on Flight Mechanics
In this study, a simulation platform for an integrated navigation algorithm for hypersonic vehicles based on flight mechanics is designed. In addition, the generation method of inertial measurement unit data and satellite receiver data is introduced. First, the interface relationship between a high-...
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MDPI AG
2020-09-01
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Series: | Sensors |
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Online Access: | https://www.mdpi.com/1424-8220/20/18/5418 |
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author | Kai Chen Fuqiang Shen Jun Zhou Xiaofeng Wu |
author_facet | Kai Chen Fuqiang Shen Jun Zhou Xiaofeng Wu |
author_sort | Kai Chen |
collection | DOAJ |
description | In this study, a simulation platform for an integrated navigation algorithm for hypersonic vehicles based on flight mechanics is designed. In addition, the generation method of inertial measurement unit data and satellite receiver data is introduced. First, the interface relationship between a high-precision six-degree-of-freedom (6DoF) model and the simulation platform in the launch-centered Earth-fixed frame is introduced. Three-axis theoretical specific force and angular velocity are output by the 6DoF model. Accelerometer and gyroscope error models are added, and integral processing of the specific force and angular velocity is performed to obtain velocity increment of the accelerometer and the angular increment of the gyroscope. These data are quantified to obtain the accelerometer and gyroscope pulses. The satellite’s pseudo-range and pseudo-range rate as well as its position and velocity are obtained from the theoretical position, velocity, the attitude of the hypersonic vehicle’s 6DoF model output, and the global positioning system (GPS) satellite broadcast ephemeris. The simulation data can be used for the verification of the loose and tight coupling integrated navigation algorithms. The simulation test verifies the accuracy of the designed method. |
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id | doaj.art-16183c6a07ba4f03b4027764f7f6d6a0 |
institution | Directory Open Access Journal |
issn | 1424-8220 |
language | English |
last_indexed | 2024-03-10T16:09:21Z |
publishDate | 2020-09-01 |
publisher | MDPI AG |
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spelling | doaj.art-16183c6a07ba4f03b4027764f7f6d6a02023-11-20T14:33:03ZengMDPI AGSensors1424-82202020-09-012018541810.3390/s20185418Simulation Platform for SINS/GPS Integrated Navigation System of Hypersonic Vehicles Based on Flight MechanicsKai Chen0Fuqiang Shen1Jun Zhou2Xiaofeng Wu3Northwestern Polytechnical University, Xi’an, Shanxi 710072, ChinaNorthwestern Polytechnical University, Xi’an, Shanxi 710072, ChinaNorthwestern Polytechnical University, Xi’an, Shanxi 710072, ChinaSchool of Aerospace, Mechanical and Mechatronic Engineering, The University of Sydney, Sydney 2006, AustraliaIn this study, a simulation platform for an integrated navigation algorithm for hypersonic vehicles based on flight mechanics is designed. In addition, the generation method of inertial measurement unit data and satellite receiver data is introduced. First, the interface relationship between a high-precision six-degree-of-freedom (6DoF) model and the simulation platform in the launch-centered Earth-fixed frame is introduced. Three-axis theoretical specific force and angular velocity are output by the 6DoF model. Accelerometer and gyroscope error models are added, and integral processing of the specific force and angular velocity is performed to obtain velocity increment of the accelerometer and the angular increment of the gyroscope. These data are quantified to obtain the accelerometer and gyroscope pulses. The satellite’s pseudo-range and pseudo-range rate as well as its position and velocity are obtained from the theoretical position, velocity, the attitude of the hypersonic vehicle’s 6DoF model output, and the global positioning system (GPS) satellite broadcast ephemeris. The simulation data can be used for the verification of the loose and tight coupling integrated navigation algorithms. The simulation test verifies the accuracy of the designed method.https://www.mdpi.com/1424-8220/20/18/5418trajectory generatorhypersonic vehicleSINS/GPS integrated navigationhardware-in-the-loop simulation |
spellingShingle | Kai Chen Fuqiang Shen Jun Zhou Xiaofeng Wu Simulation Platform for SINS/GPS Integrated Navigation System of Hypersonic Vehicles Based on Flight Mechanics Sensors trajectory generator hypersonic vehicle SINS/GPS integrated navigation hardware-in-the-loop simulation |
title | Simulation Platform for SINS/GPS Integrated Navigation System of Hypersonic Vehicles Based on Flight Mechanics |
title_full | Simulation Platform for SINS/GPS Integrated Navigation System of Hypersonic Vehicles Based on Flight Mechanics |
title_fullStr | Simulation Platform for SINS/GPS Integrated Navigation System of Hypersonic Vehicles Based on Flight Mechanics |
title_full_unstemmed | Simulation Platform for SINS/GPS Integrated Navigation System of Hypersonic Vehicles Based on Flight Mechanics |
title_short | Simulation Platform for SINS/GPS Integrated Navigation System of Hypersonic Vehicles Based on Flight Mechanics |
title_sort | simulation platform for sins gps integrated navigation system of hypersonic vehicles based on flight mechanics |
topic | trajectory generator hypersonic vehicle SINS/GPS integrated navigation hardware-in-the-loop simulation |
url | https://www.mdpi.com/1424-8220/20/18/5418 |
work_keys_str_mv | AT kaichen simulationplatformforsinsgpsintegratednavigationsystemofhypersonicvehiclesbasedonflightmechanics AT fuqiangshen simulationplatformforsinsgpsintegratednavigationsystemofhypersonicvehiclesbasedonflightmechanics AT junzhou simulationplatformforsinsgpsintegratednavigationsystemofhypersonicvehiclesbasedonflightmechanics AT xiaofengwu simulationplatformforsinsgpsintegratednavigationsystemofhypersonicvehiclesbasedonflightmechanics |