Identification Method of SINS Error Parameters Utilizing Artificial Neural Network for Hypersonic Vehicle

Identification Method of SINS Error Parameters Utilizing Artificial Neural Network for Hypersonic Vehicle

To improve the navigation accuracy of hypersonic vehicle, an error parameter identification method of strap-down inertial navigation system (SINS) based on artificial neural network is proposed. Firstly, the inertial measurement unit (IMU) error model and the SINS navigation calculation model are es...

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Bibliographic Details
Main Authors: Weilin Guo, Yong Xian, Daqiao Zhang, Zhaoqiang Wang
Format: Article
Language:English
Published: IEEE 2019-01-01
Series:IEEE Access
Subjects:
Hypersonic vehicle
integrated navigation system
artificial neural network
structure optimization
error parameter identification
gradient particle swarm optimization
Online Access:https://ieeexplore.ieee.org/document/8896837/

Internet

https://ieeexplore.ieee.org/document/8896837/

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