A Review of Wind Tunnel Based Virtual Flight Testing Techniques for Evaluation of Flight Control Systems

Wind tunnel based Virtual Flight Testing (VFT) is a dynamic wind tunnel test for evaluating flight control systems (FCS) proposed in recent decades. It integrates aerodynamics, flight dynamics, and FCS as a whole and is a more realistic and reliable method for FCS evaluation than traditional ground...

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Main Authors: Min Huang, Zhong-wei Wang
Format: Article
Language:English
Published: Wiley 2015-01-01
Series:International Journal of Aerospace Engineering
Online Access:http://dx.doi.org/10.1155/2015/672423
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author Min Huang
Zhong-wei Wang
author_facet Min Huang
Zhong-wei Wang
author_sort Min Huang
collection DOAJ
description Wind tunnel based Virtual Flight Testing (VFT) is a dynamic wind tunnel test for evaluating flight control systems (FCS) proposed in recent decades. It integrates aerodynamics, flight dynamics, and FCS as a whole and is a more realistic and reliable method for FCS evaluation than traditional ground evaluation methods, such as Hardware-in-the-Loop Simulation (HILS). With FCS evaluated by VFT before flight test, the risk of flight test will be further reduced. In this paper, the background, progress, and prospects of VFT are systematically summarized. Specifically, the differences among VFT, traditional dynamic wind tunnel methods, and traditional FCS evaluation methods are introduced in order to address the advantages of evaluating FCS with VFT. Secondly, the progress of VFT is reviewed in detail. Then, the test system and key technologies of VFT for FCS evaluation are analyzed. Lastly, the prospects of VFT for evaluating FCS are described.
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spelling doaj-art-4b42f38849c54a9f8a7588905eda16502025-08-20T02:38:35ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742015-01-01201510.1155/2015/672423672423A Review of Wind Tunnel Based Virtual Flight Testing Techniques for Evaluation of Flight Control SystemsMin Huang0Zhong-wei Wang1Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha, Hunan 410073, ChinaScience and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha, Hunan 410073, ChinaWind tunnel based Virtual Flight Testing (VFT) is a dynamic wind tunnel test for evaluating flight control systems (FCS) proposed in recent decades. It integrates aerodynamics, flight dynamics, and FCS as a whole and is a more realistic and reliable method for FCS evaluation than traditional ground evaluation methods, such as Hardware-in-the-Loop Simulation (HILS). With FCS evaluated by VFT before flight test, the risk of flight test will be further reduced. In this paper, the background, progress, and prospects of VFT are systematically summarized. Specifically, the differences among VFT, traditional dynamic wind tunnel methods, and traditional FCS evaluation methods are introduced in order to address the advantages of evaluating FCS with VFT. Secondly, the progress of VFT is reviewed in detail. Then, the test system and key technologies of VFT for FCS evaluation are analyzed. Lastly, the prospects of VFT for evaluating FCS are described.http://dx.doi.org/10.1155/2015/672423
spellingShingle Min Huang
Zhong-wei Wang
A Review of Wind Tunnel Based Virtual Flight Testing Techniques for Evaluation of Flight Control Systems
International Journal of Aerospace Engineering
title A Review of Wind Tunnel Based Virtual Flight Testing Techniques for Evaluation of Flight Control Systems
title_full A Review of Wind Tunnel Based Virtual Flight Testing Techniques for Evaluation of Flight Control Systems
title_fullStr A Review of Wind Tunnel Based Virtual Flight Testing Techniques for Evaluation of Flight Control Systems
title_full_unstemmed A Review of Wind Tunnel Based Virtual Flight Testing Techniques for Evaluation of Flight Control Systems
title_short A Review of Wind Tunnel Based Virtual Flight Testing Techniques for Evaluation of Flight Control Systems
title_sort review of wind tunnel based virtual flight testing techniques for evaluation of flight control systems
url http://dx.doi.org/10.1155/2015/672423
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