A Multi-Degree-of-Freedom Rig for the Wind Tunnel Determination of Dynamic Data

Pattinson, John; Löwenberg, Mark; Goman, Mikhail

doi:10.2514/6.2009-5727

Cited by 12 publications

(13 citation statements)

References 13 publications

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“…This mathematical model is very essential to know the dynamics of the two-body rig-aircraft system and also useful along with the well-known parameter estimation methods such as least square, filter error method, MLE, etc. rather than Lagrange formula mentioned in Pattinson and Lowenberg [15]. Using the MLE method, close agreement was achieved between estimates of longitudinal and lateral-directional derivatives and corresponding analytical values used for generating simulated flight data.…”

Section: Resultsmentioning

confidence: 85%

Mathematical modelling, simulation, and estimation of aircraft parameters using five degree-of-freedom dynamic test rig

Peyada¹,

Ghosh

Go³

2011

Proceedings of the Institution of Mechanical Engineers, Part G:

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This article proposes a scheme to estimate the aerodynamic derivatives of aircraft using a wind tunnel dynamic test rig system. A five-degree-of-freedom (DOF) rig system has been used to simulate near free flight manoeuvres inside the wind tunnel by exciting a scaled down model aircraft through various types of control surface deflections. A mathematical model that incorporates five DOF in aircraft motion has been developed. The five DOF equations of motion of the rig system are formulated using a vector and matrix approach. The simulated flight data, generated from a five DOF mathematical model, has been used to estimate the aerodynamic parameters of the aircraft. The maximum likelihood method has been used to achieve close estimates of the parameters by minimizing the error between simulated and computed response.

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Section: Resultsmentioning

confidence: 85%

Mathematical modelling, simulation, and estimation of aircraft parameters using five degree-of-freedom dynamic test rig

Peyada¹,

Ghosh

Go³

2011

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…The degrees of freedom permitted by the rig are shown in Figure 18. The range of motion that the rig permits is ±30 degrees of rotation in roll and pitch, 360 degrees in yaw, and a translation of approximately 0.75 m in the vertical [106], and 5-DOF [107,108] dynamic wind tunnel rig were built. The 5-DOF rig is shown in Figure 19, which allows model pitch, model yaw, model roll, rig pitch (model heave), and rig yaw (model sway), as illustrated in Figure 20.…”

Section: Progress Of Vft In the United Kingdom Research Departments mentioning

confidence: 99%

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

Huang

Wang

2015

International Journal of Aerospace Engineering

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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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“…The resulting 'physical simulation' allows for the observation of aircraft behaviour, including the influence of nonlinear and/or time-dependent aerodynamics such as that responsible for the onset of upset/departure; and the motion data from such tests -or from forced motions driven by the rig compensator system -can then be used to carry out parameter estimation for mathematical model development. A couple of prototypes of the manoeuvre rig have been developed recently to obtain aerodynamic data from wind tunnel multi-DOF dynamic tests, 14 to characterise the oscillatory longitudinal pitch and heave motions of an aircraft model 15 and to numerically simulate free flight manoeuvres of a delta-wing aircraft model in a wind tunnel. 16 Following the development and initial testing of this rig concept at the University of Bristol, 17 various follow-on activities were identified.…”

Section: Introductionmentioning

confidence: 99%

Evaluation of Aircraft Model Upset Behaviour Using Wind Tunnel Manoeuvre Rig

Araujo-Estrada

Löwenberg

Neild

et al. 2015

AIAA Atmospheric Flight Mechanics Conference

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This paper discusses the development of a novel multi-degree-of-freedom dynamic manoeuvre rig aimed at investigation of aircraft upset/LOC-related behaviour in the wind tunnel. The motivation behind the development and characteristics of the rig are first described, along with example behaviour of an aircraft model exhibiting nonlinear timedependent aerodynamics in an open-jet low-speed wind tunnel. Test objectives for assessment of upset onset scenarios -both for parameter estimation purposes and to 'physically simulate' the behaviour -are then described, as is the design of the upgraded instrumentation system to facilitate experimental investigastion. Finally, examples of relevant behaviour involving real-time control of the rig to explore nonlinear conditions leading to upset are presented; these are evaluated in terms of prospects for such testing in aircraft development and analysis projects.

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A Multi-Degree-of-Freedom Rig for the Wind Tunnel Determination of Dynamic Data

Cited by 12 publications

References 13 publications

Mathematical modelling, simulation, and estimation of aircraft parameters using five degree-of-freedom dynamic test rig

Mathematical modelling, simulation, and estimation of aircraft parameters using five degree-of-freedom dynamic test rig

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

Evaluation of Aircraft Model Upset Behaviour Using Wind Tunnel Manoeuvre Rig

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