Roll Control of Morphing Aircraft with Synthetic Jet Actuators at a High Angle of Attack
Flow separation and dynamic stall occurring at a high angle of attack will lead to difficulty in control and maneuverability for morphing aircraft. This study proposes a novel active flow control technology using a synthetic jet actuator for the roll motion of morphing aircraft. With the help of the...
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doaj-e7f1eeeb84c94cd5bf4e19786f0fc9a42021-01-07T00:05:39ZengMDPI AGApplied Sciences2076-34172021-01-011150550510.3390/app11020505Roll Control of Morphing Aircraft with Synthetic Jet Actuators at a High Angle of AttackWencheng Li0Wenyun Wang1Xiaomao Huang2Shun Zhang3Chenyang Li4College of Engineering, Huazhong Agricultural University, Wuhan 430070, ChinaThe 9th Designing of China Aerospace Science and Industry Corporation, Wuhan 430040, ChinaCollege of Engineering, Huazhong Agricultural University, Wuhan 430070, ChinaCollege of Engineering, Huazhong Agricultural University, Wuhan 430070, ChinaCollege of Engineering, Huazhong Agricultural University, Wuhan 430070, ChinaFlow separation and dynamic stall occurring at a high angle of attack will lead to difficulty in control and maneuverability for morphing aircraft. This study proposes a novel active flow control technology using a synthetic jet actuator for the roll motion of morphing aircraft. With the help of the computational fluid dynamics method and vortex lattice method, the roll control model of morphing aircraft undergoing large shape change at a high angle of attack is established. In this model, both the array of the actuator with an optimized cavity shape and morphing span, which are subject to the input saturation constraint, are used to mimic the conventional control surface. Integrated flight control based on the sliding mode control method is designed to ensure the desired closed-loop asymptotic stability, wherein the radial basis function neural network is employed to provide the compensation induced by the input saturation constraint. To demonstrate the effectiveness of the control scheme, various control strategies for different combinations of input are proposed to maintain the roll motion. The numerical results show that the designed control law could track the target signal well, which suggests that the virtual control surface is an effective tool for maintaining the high flight performance of morphing aircraft.https://www.mdpi.com/2076-3417/11/2/505morphing aircraftsynthetic jet actuatorsliding mode controlinput saturation constraint |
collection |
DOAJ |
language |
English |
format |
Article |
sources |
DOAJ |
author |
Wencheng Li Wenyun Wang Xiaomao Huang Shun Zhang Chenyang Li |
spellingShingle |
Wencheng Li Wenyun Wang Xiaomao Huang Shun Zhang Chenyang Li Roll Control of Morphing Aircraft with Synthetic Jet Actuators at a High Angle of Attack Applied Sciences morphing aircraft synthetic jet actuator sliding mode control input saturation constraint |
author_facet |
Wencheng Li Wenyun Wang Xiaomao Huang Shun Zhang Chenyang Li |
author_sort |
Wencheng Li |
title |
Roll Control of Morphing Aircraft with Synthetic Jet Actuators at a High Angle of Attack |
title_short |
Roll Control of Morphing Aircraft with Synthetic Jet Actuators at a High Angle of Attack |
title_full |
Roll Control of Morphing Aircraft with Synthetic Jet Actuators at a High Angle of Attack |
title_fullStr |
Roll Control of Morphing Aircraft with Synthetic Jet Actuators at a High Angle of Attack |
title_full_unstemmed |
Roll Control of Morphing Aircraft with Synthetic Jet Actuators at a High Angle of Attack |
title_sort |
roll control of morphing aircraft with synthetic jet actuators at a high angle of attack |
publisher |
MDPI AG |
series |
Applied Sciences |
issn |
2076-3417 |
publishDate |
2021-01-01 |
description |
Flow separation and dynamic stall occurring at a high angle of attack will lead to difficulty in control and maneuverability for morphing aircraft. This study proposes a novel active flow control technology using a synthetic jet actuator for the roll motion of morphing aircraft. With the help of the computational fluid dynamics method and vortex lattice method, the roll control model of morphing aircraft undergoing large shape change at a high angle of attack is established. In this model, both the array of the actuator with an optimized cavity shape and morphing span, which are subject to the input saturation constraint, are used to mimic the conventional control surface. Integrated flight control based on the sliding mode control method is designed to ensure the desired closed-loop asymptotic stability, wherein the radial basis function neural network is employed to provide the compensation induced by the input saturation constraint. To demonstrate the effectiveness of the control scheme, various control strategies for different combinations of input are proposed to maintain the roll motion. The numerical results show that the designed control law could track the target signal well, which suggests that the virtual control surface is an effective tool for maintaining the high flight performance of morphing aircraft. |
topic |
morphing aircraft synthetic jet actuator sliding mode control input saturation constraint |
url |
https://www.mdpi.com/2076-3417/11/2/505 |
work_keys_str_mv |
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