Assessment of Tabular Models Using CFD

McCracken, A.J.; Kennett, David; Badcock, K. J.; Ronch, Andrea Da

doi:10.2514/6.2013-4978

Cited by 4 publications

(5 citation statements)

References 19 publications

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“…Equation (3) can provide convincing insights into the application of the aerodynamic stability derivatives approach. Whereas a large body of work has been done on prescribed flight mechanics trajectories, [6][7][8]28 a consistent study to assess the stability derivatives approach for a flying vehicle is missing, apart from a recent work by McCracken et al 29 This research work aims to expand previous investigations. The aerodynamic moment around the centre of gravity can be expressed as…”

Section: Ivb1 Model Based On Aerodynamic Stability Derivativesmentioning

confidence: 86%

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Assessing the Impact of Aerodynamic Modelling on Manoeuvring Aircraft

Ronch

McCracken

Tantaroudas

et al. 2014

AIAA Atmospheric Flight Mechanics Conference

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This paper investigates the impact of aerodynamic models on the dynamic response of a free-flying aircraft wing. Several options for the aerodynamics are evaluated, from two-dimensional thin aerofoil aerodynamics and unsteady vortex-lattice method up to computational fluid dynamics. A nonlinear formulation of the rigid body dynamics is used in all cases. Results are generated using a numerical framework that will allow in the near future multi-disciplinary fluid/structure/flight analysis. In this paper, flexibility effects are neglected. A validation for fluid/flight models is presented. The well-established approach based on stability derivatives is also used, and is found in good agreement with solutions obtained from linear aerodynamic models. The uncertainties in predicted trajectories of the free-flying wing are, in general, large and attributed to the aerodynamics only. This suggests that a careful control law synthesis should be done to account for uncertainties from modelling techniques.

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Section: Ivb1 Model Based On Aerodynamic Stability Derivativesmentioning

confidence: 86%

“…The static data used in these comparisons has been obtained from an aerodynamic tabular model as described in Ref. 29 It is seen that there is a substantial difference between the three sources. The traditional approach of using forced motions predicts the greatest aerodynamic damping, whereas the CFD free response identification is the least well damped.…”

mentioning

confidence: 99%

Assessing the Impact of Aerodynamic Modelling on Manoeuvring Aircraft

Ronch

McCracken

Tantaroudas

et al. 2014

AIAA Atmospheric Flight Mechanics Conference

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“…occurs in a flow field [1]. At this point, aerodynamics depend not only on the current exercise state but also on their time history [2], and the conventional aerodynamic derivative modeling method becomes difficult to apply [3]. Thus, the study of unsteady aerodynamic modeling methods is required.…”

Section: Introductionmentioning

confidence: 99%

Unsteady aerodynamics modeling using Volterra series expansed by basis function

Chen

Gao

2018

MATEC Web Conf.

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Unsteady aerodynamics modeling must accurately describe nonlinear aerodynamic characteristics in addition to unsteady aerodynamic characteristics. The Volterra series has attracted increasing attention as a powerful tool for nonlinear system modeling. It is essential to incorporate the influence of the second-order Volterra kernel or higher-order kernels to build a nonlinear unsteady aerodynamics model. The main difficulty in the identification of higher-order kernels is that the number of parameters to be identified increases exponentially with the order of a kernel. This paper expands the Volterra kernels with the four-order B-spline wavelet on the interval as the basis function, converts the problem into the solution of low-dimensional equations, and obtains a stable solution. A nonlinear unsteady aerodynamics model is built by identifying the second-order and third-order kernels of the lift, drag, and pitching moment coefficients of the NACA0012 airfoil. Then the model is verified at different reduced frequencies using CFD.

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“…For cases where an aeroelastic interface is required to couple non-coincident and nonoverlapping aerodynamic/structural models, the method described in Ref. 23 provides an excellent solution to the problem.…”

Section: Geometrically-nonlinear Flexible Wingmentioning

confidence: 99%

“…(24) are dynamic gains that need to be solved and at the end will be required to converge to the values that provide a solution to Eq. (23). The closed loop dynamics of the nonlinear reduced model at this point can be expressed as…”

Section: Model Reference Adaptive Controlmentioning

confidence: 99%

An Adaptive Aeroelastic Control Approach using Non Linear Reduced Order Models

Tantaroudas

Ronch

Gai

et al. 2014

14th AIAA Aviation Technology, Integration, and Operations Conference

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A systematic approach to the model order reduction of high fidelity coupled fluidstructure/flight dynamics models and the subsequent control design is described. It uses information on the eigenspectrum of the coupled-system Jacobian matrix and projects the system through a series expansion onto a small basis of eigenvectors representative of the full-model dynamics. A nonlinear reduced order model is derived and is exploited for a worst case gust and adaptive control design. The investigation focuses on a flight control design based on the model reference adaptive control scheme via the Lyapunov stability approach. The novelty of this paper is two-fold. Firstly, it uses a single nonlinear reduced model for parametric worst case gust search. Secondly, it is shown that it makes feasible an implementation of a complex control methodology for a large nonlinear system. The adaptive controller is able to alleviate gust loads for a three degrees-of-freedom aerofoil and for an unmanned aerial vehicle. An investigation for the adaptation parameters is performed and their effect on control input actuation and aeroelastic closed-loop response is discussed.= plunge stiffness,torsional and flap stiffness about elastic axis= plunge, torsional and flap third order terms of stiffness

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Assessment of Tabular Models Using CFD

Cited by 4 publications

References 19 publications

Assessing the Impact of Aerodynamic Modelling on Manoeuvring Aircraft

Assessing the Impact of Aerodynamic Modelling on Manoeuvring Aircraft

Unsteady aerodynamics modeling using Volterra series expansed by basis function

An Adaptive Aeroelastic Control Approach using Non Linear Reduced Order Models

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