Equivalent plate analysis of aircraft wing box structures with general planform geometry

Giles, G. L.

doi:10.2514/3.45393

Cited by 100 publications

(32 citation statements)

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“…This approach has shown very good results for both static and dynamic analysis of wings (Giles, 1986 and1987). It can handle fairly general planform geometries and boundary conditions, model complex wing cross-section geometries, include rib and spar caps, and permit the use of composite materials and the consideration of thermal loading.…”

Section: Structural Modelmentioning

confidence: 99%

“…While n, is varied, the discretization of the structural model is held fixed ( N , = 5, Ny = 6) because, as indicated by Giles (1986), it cannot be increased significantly without risking singularities in the stiffness matrix. Table I1 shows the effect that aerodynamic discretization has on the convergence of the induced drag, the divergence dynamic pressure, as well as their derivatives.…”

Section: Convergence Of Calculated Parameters With Respect To Nmentioning

confidence: 99%

“…The Nx and Ny values are chosen by the user; Giles (1986) suggests an upper limit of 7 for both of them. Also defined by the user are constant normalization lengths Xmax and Y m a .…”

Section: Appendix B Aerodynamic Matrix and Derivativesmentioning

confidence: 99%

“…It combines Weissinger's L-method (Weissinger, 1947) to predict the wing spanwise lift distribution with Giles' equivalent plate analysis method (Giles, 1986) for structural analysis. The calculation of the sensitivity derivatives is described next.…”

Section: Introductionmentioning

confidence: 99%

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Shape sensitivity analysis of wing static aeroelastic characteristics

Barthélémy

Bergen

1989

Journal of Aircraft

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A method is presented to calculate analytically the sensitivity derivatives of wing static aeroelastic characteristics with respect to wing shape parameters. The wing aerodynamic response under fixed total load is predicted with Weissinger's L-method; its structural response is obtained with Giles' equivalent plate method. The characteristics of interest in this study include the spanwise distribution of lift, trim angle of attack, rolling and pitching moments, induced drag, as well as the divergence dynamic pressure. The shape parameters considered are the wing area, aspect ratio, taper ratio, sweep angle, and tip twist angle. Results of sensitivity studies indicate that (1) approximations based on analytical sensitivity derivatives can be used for wide ranges of variations of the shape parameters considered, and (2) the analytical calculation of sensitivity derivatives is significantly less expensive than the conventional finite-difference alternative.

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Section: Structural Modelmentioning

confidence: 99%

Section: Convergence Of Calculated Parameters With Respect To Nmentioning

confidence: 99%

“…The Nx and Ny values are chosen by the user; Giles (1986) suggests an upper limit of 7 for both of them. Also defined by the user are constant normalization lengths Xmax and Y m a .…”

Section: Appendix B Aerodynamic Matrix and Derivativesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Shape sensitivity analysis of wing static aeroelastic characteristics

Barthélémy

Bergen

1989

Journal of Aircraft

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“…The equivalent plate model can also be used to design a wind tunnel model to match the stiffness characteristics of the wing box of a full-scale aircraft wing model while satisfying strength-based requirements [2]. An equivalent plate analysis procedure based on the Ritz method was proposed at NASA Langley Research Center as early as 1986 [3]. In the Ritz method-based equivalent plate theory, the aircraft wing structure is modeled with several trapezoidal segments.…”

Section: Introductionmentioning

confidence: 99%

Frequencies and Flutter Speed Estimation for Damaged Aircraft Wing Using Scaled Equivalent Plate Analysis

Krishnamurthy

2010

51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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Equivalent plate analysis is often used to replace the computationally expensive finite element analysis in initial design stages or in conceptual design of aircraft wing structures. The equivalent plate model can also be used to design a wind tunnel model to match the stiffness characteristics of the wing box of a full-scale aircraft wing model while satisfying strength-based requirements An equivalent plate analysis technique is presented to predict the static and dynamic response of an aircraft wing with or without damage. First, a geometric scale factor and a dynamic pressure scale factor are defined to relate the stiffness, load and deformation of the equivalent plate to the aircraft wing. A procedure using an optimization technique is presented to create scaled equivalent plate models from the full scale aircraft wing using geometric and dynamic pressure scale factors. The scaled models are constructed by matching the stiffness of the scaled equivalent plate with the scaled aircraft wing stiffness. It is demonstrated that the scaled equivalent plate model can be used to predict the deformation of the aircraft wing accurately. Once the full equivalent plate geometry is obtained, any other scaled equivalent plate geometry can be obtained using the geometric scale factor. Next, an average frequency scale factor is defined as the average ratio of the frequencies of the aircraft wing to the frequencies of the full-scaled equivalent plate. The average frequency scale factor combined with the geometric scale factor is used to predict the frequency response of the aircraft wing from the scaled equivalent plate analysis. A procedure is outlined to estimate the frequency response and the flutter speed of an aircraft wing from the equivalent plate analysis using the frequency scale factor and geometric scale factor. The equivalent plate analysis is demonstrated using an aircraft wing without damage and another with damage. Both of the problems show that the scaled equivalent plate analysis can be successfully used to predict the frequencies and flutter speed of a typical aircraft wing.

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Flutter Analysis of Supersonic Low Aspect Ratio Composite Wings Using FSI Methodology
Babin¹,
Sangeetha²
2018
Lecture Notes in Mechanical Engineering
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Equivalent plate analysis of aircraft wing box structures with general planform geometry

Cited by 100 publications

References 2 publications

Shape sensitivity analysis of wing static aeroelastic characteristics

Shape sensitivity analysis of wing static aeroelastic characteristics

Frequencies and Flutter Speed Estimation for Damaged Aircraft Wing Using Scaled Equivalent Plate Analysis

Flutter Analysis of Supersonic Low Aspect Ratio Composite Wings Using FSI Methodology

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