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

Huang, Min; Wang, Zhongwei

doi:10.1155/2015/672423

Cited by 33 publications

(11 citation statements)

References 91 publications

(142 reference statements)

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“…Brief definitions of the VFT can be found in Huang and Wang. 1 Therefore, the VFT concept is not repeatedly introduced in this paper. Up to now, the VFT test technique has found many applications, such as dynamic derivatives identification, [2][3][4][5][6][7] researching the coupling characteristics between aerodynamics and flight mechanics, [8][9][10] spin recovery strategy evaluation, 11,12 and flight control system evaluation.…”

Section: Necessity Of Evaluating Fcss With Vftmentioning

confidence: 99%

Design of the wind tunnel based virtual flight testing evaluation method for flight control systems

Huang

Wang

Zhang

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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In order to provide a method for evaluating flight control systems with the wind tunnel based virtual flight testing and provide a guide for building virtual flight testing systems, the virtual flight testing evaluation method was researched. The virtual flight testing evaluation method consisted of three parts: virtual flight testing method, virtual flight testing data processing method, and flight control system performance determination method, which were respectively designed for a pitching control system. Then, the hardware-in-the-loop simulation evaluation method was presented, and comparisons between the virtual flight testing and hardware-in-the-loop simulation evaluation method were conducted to highlight the characteristics of virtual flight testing evaluation method. Finally, virtual flight testing simulation models of a sample air vehicle were built and virtual flight testing were simulated to demonstrate the virtual flight testing evaluation method, which is helpful for the understanding of the virtual flight testing evaluation method with more sensibility. The evaluation results show that the virtual flight testing evaluation method designed can be used for flight control system evaluation.

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Section: Necessity Of Evaluating Fcss With Vftmentioning

confidence: 99%

Design of the wind tunnel based virtual flight testing evaluation method for flight control systems

Huang

Wang

Zhang

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

Self Cite

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“…Many of the flight research is based on wind tunnel and flight data collected during flights devoted to a particular investigation, which is both risky and expensive. It is also done through virtual flight-testing, theoretical and analytical techniques (Huang, 2015). The speed brake, the airdrop and the landing gear effects have been identified using a nonlinear maximum likelihood parameter estimation method (Jategaonkar, 1997).…”

Section: Introductionmentioning

confidence: 99%

Developed Criteria to Improve Pilot Reporting of Airplane Vortex Encounters

Al-Mahadin

Dalkılıç

2020

Aviation

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Leading airplane vortices can be hazardous to following airplanes. The regulated minimum separations between following and leading airplanes are sometimes overjudged, hence causing reduction in the capacity of airports. In other instances, they are underjudged and subsequently causing airplane incidences. A vital contribution to the establishment and adjustment of vortex-related minimum airplane separations rely on the identification of vortex encounters through pilot reporting with a manual analysis of flight data from FDRs (flight data recorders). This current process relies on judgment of both the pilot and the airline analysist. Hence, it is subjective and sometimes lacks the required accuracy. Therefore, it is desirable to set a number of criteria, which can be utilized to evaluate the accuracy of wake vortex encounter identification. These criteria can save time, and are both accurate and simple. This study investigates 54 pilot reports of flight events to establish a set of criteria that enable concerned aviation organizations to confirm airplane vortex encounters with higher accuracy. This also helps airlines and aviation stakeholders to introduce new regulations and enhancements such as pilots and FDR analysts training on vortex identification. Such measures will enhance safety, improve aviation operation efficiency and allow revision of vortex-separation regulations.

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“…Due to the advantages of wind tunnel tests with control, many departments were developing the wind tunnel test techniques with control [4] in an attempt to predict flight performances and evaluate the flight control laws in wind tunnels. The Arnold Engineering Development Center (AEDC) [5] built an 8-wire suspended 2-DOF (degrees-of-freedom) wind tunnel test system with control and the Physical Sciences Incorporation (PSI) [6] in USA built an 6-wire suspended 3-DOF (pitch, yaw and roll) wind tunnel test system with control to reappear and predict the coupling motions that may occur in the real flights.…”

Section: Introductionmentioning

confidence: 99%

Preliminary Validation of the Wind Tunnel Based Flight Control System Evaluation Method

Huang¹,

Wang

Yang³

et al. 2018

MATEC Web Conf.

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Abstract. As mathematical models of aircraft aerodynamics and rudder loadings always have to be built in the hardware-in-the-loop simulation, wind tunnel based flight control system (FCS) evaluation methods were proposed in order to test and evaluate the flight control systems under real aerodynamic and rudder loading environment. To validate the evaluation method, a wind tunnel based flight control system test was performed in a hypersonic wind tunnel facility. As the aircraft support rig in the wind tunnel is static, the aircraft angle of attack cannot be changed in this test. During the test, the elevator response, the lift force and the pitching moment were measured. By analysing the measured data, the elevator control performance of the pitch control system was determined, and the pitch angle was successfully predicted, but the open-loop pitch control performance was not determined. These results validate the feasibility of evaluating the elevator control performance and predicting the pitch angle of a FCS by the wind tunnel based FCS evaluation method.

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

Cited by 33 publications

References 91 publications

Design of the wind tunnel based virtual flight testing evaluation method for flight control systems

Design of the wind tunnel based virtual flight testing evaluation method for flight control systems

Developed Criteria to Improve Pilot Reporting of Airplane Vortex Encounters

Preliminary Validation of the Wind Tunnel Based Flight Control System Evaluation Method

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