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Air Data Estimation by Fusing Navigation System and Flight Control System

Published online by Cambridge University Press:  30 April 2018

Chen Lu
Affiliation:
(Key Laboratory of Internet of Things and Control Technology in Jiangsu Province, Nanjing 20016, China) (Navigation Research Center, College of Automation Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China)
Rong-Bing Li
Affiliation:
(Key Laboratory of Internet of Things and Control Technology in Jiangsu Province, Nanjing 20016, China) (Navigation Research Center, College of Automation Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China)
Jian-Ye Liu
Affiliation:
(Key Laboratory of Internet of Things and Control Technology in Jiangsu Province, Nanjing 20016, China) (Navigation Research Center, College of Automation Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China)
Ting-Wan Lei
Affiliation:
(Chengdu Aircraft Design and Research Institute, Chengdu 610000, China)
Corresponding
E-mail address:

Abstract

A novel synthetic air data estimation method without using air data sensors is presented, and the method only relies on the information from the Navigation System (NS) and Flight Control System (FCS). The aircraft's aerodynamic model is also required to make a connection between the FCS control parameters and the NS measurements. The airspeed, angle of attack and sideslip, angular velocity and wind speed are defined as state vectors, and state equations are established through the aircraft's aerodynamic model and dynamics. Linear velocity and angular velocity provided by the navigation system are considered as the measurement vector. To deal with variable wind fields, a novel Initialised Three-step Extended Kalman Filter (ITEKF), which considers the wind speed as an unknown input, is developed to track the variation of wind speed. Simulation results based on a Generic Hypersonic Vehicle (GHV) model are presented and compared with an existing method. Factors affecting the method's accuracy include the navigation system accuracy and the aerodynamic model error, are also discussed.

Type
Research Article
Copyright
Copyright © The Royal Institute of Navigation 2018 

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