Aircraft flight safety envelope protection under icing conditions based on adaptive neural network dynamic inversion

WEI Yang; XU Haojun; XUE Yuan; ZHENG Wuji; LI Zhe; PEI Binbin

doi:10.7527/S1000-6893.2018.22488

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2019 , Vol. 40 >Issue 5: 122488 - 122488

DOI: https://doi.org/10.7527/S1000-6893.2018.22488

Fluid Mechanics and Flight Mechanics

Aircraft flight safety envelope protection under icing conditions based on adaptive neural network dynamic inversion

WEI Yang ,
XU Haojun ,
XUE Yuan ,
ZHENG Wuji ,
LI Zhe ,
PEI Binbin

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1. Aeronautics Engineering College, Air Force Engineering University, Xi'an 710038, China;
2. Fourth Training Brigade, Shijiazhuang Flighting College of Air Force, Baoding 074212, China

Received date: 2018-06-27

Revised date: 2018-07-18

Online published: 2018-09-19

Supported by

National Basic Research Program of China (2015CB755802); National Natural Science Foundation of China (61503406); Civil Aircraft Special Research (MJ-2015-F-019)

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Abstract

Flight safe envelope protection of iced aircraft has become an effective solution to the flight safety under icing conditions. Based on the good tracking performance and strong robustness of the adaptive neural network dynamic inversion control, an envelope protection method is proposed to obtain the available deflection angle of control surface by using the limit value of the key flight safety parameters as input of control loop. The dynamic model of the aircraft is established, and a high precision numerical simulation method is used to obtain the icing aerodynamic database. The adaptive neural network dynamic inversion control law for an aircraft is designed. By introducing the single hidden layer neural network in dynamic inversion, the uncertainty inverse error is compensated adaptively, and the robustness of the control system is enhanced. The closed loop envelope protection system in pitch attitude hold mode under icing conditions is designed. An automatic throttle control system is designed on the assumption that the minimum flying speed is the same as the estimated value of the minimum level of the flight speed and the design is used to protect the flight speed. The simulation results show that the designed control law has strong robustness. The dynamic response of the aircraft state parameters is analyzed in the case of the linear increase of icing severity. The simulation results show that the designed envelope protection system can realize the real-time protection of the key security parameters such as the angle of attack and the speed during the ice-tolerant flight.

Key words： aircraft icing; envelope protection; adaptive neural network dynamic inversion; pitch attitude hold; key security parameters

Cite this article

WEI Yang , XU Haojun , XUE Yuan , ZHENG Wuji , LI Zhe , PEI Binbin . Aircraft flight safety envelope protection under icing conditions based on adaptive neural network dynamic inversion[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019 , 40(5) : 122488 -122488 . DOI: 10.7527/S1000-6893.2018.22488

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