Equivalent plate modeling for conceptual design of aircraft wing structures

Giles, G. L.

doi:10.2514/6.1995-3945

Cited by 42 publications

(24 citation statements)

References 3 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…Where G is the constraint to be satisfied in the optimization problem; E P is the total load applied in the Equivalent plate model; and The general purpose finite element code ABAQUS [7] is used for the finite element analysis. The optimization code DOT [8] is used in step 5 to minimize the difference in displacements in Equation 1. This procedure is further explained in the context of the following two numerical examples.…”

Section: Equivalent Plate Theory Developmentmentioning

confidence: 99%

“…Equivalent plate analysis has been used to replace the computationally expensive finite element analysis in initial design stages or in conceptual design of aircraft wing structures [1]. In equivalent plate modeling, the model characteristics are represented with polynomials, which require only a small fraction of the input data that would be required by a corresponding finite element model.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Equivalent Plate Analysis of Aircraft Wing with Discrete Source Damage

Krishnamurthy¹,

Mason²

2006

47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

12
0
10
0

View full text Add to dashboard Cite

An equivalent plate procedure is developed to provide a computationally efficient means of matching the stiffness and frequencies of flight vehicle wing structures for prescribed loading conditions. First, the equivalent plate is used to match the stiffness of a stiffened panel without damage and the stiffness of a stiffened panel with damage. For both stiffened panels, the equivalent plate models reproduce the deformation of a corresponding detailed model exactly for the given loading conditions. Once the stiffness was matched, the equivalent plate models were then used to predict the frequencies of the panels. Two analytical procedures using the lumped-mass matrix were used to match the first five frequencies of the corresponding detailed model. In both the procedures, the lumped-mass matrix for the equivalent plate is constructed by multiplying the diagonal terms of the consistent-mass matrix by a proportionality constant. In the first procedure, the proportionality constant is selected such that the total mass of the equivalent plate is equal to that of the detailed model. In the second method, the proportionality constant is selected to minimize the sum of the squares of the errors in a set of pre-selected frequencies between the equivalent plate model and the detailed model. The equivalent plate models reproduced the fundamental first frequency accurately in both the methods. It is observed that changing only the mass distribution in the equivalent plate model did not provide enough flexibility to match all of the frequencies.

show abstract

Section: Equivalent Plate Theory Developmentmentioning
confidence: 99%

Section: Introductionmentioning
confidence: 99%

Equivalent Plate Analysis of Aircraft Wing with Discrete Source Damage
Krishnamurthy¹,
Mason²
2006
47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
12
0
10
0
View full text Add to dashboard Cite

show abstract

“…Equivalent plate analysis is often used to replace the computationally expensive detailed finite element analysis in initial design stages or in conceptual design of aircraft wing structures [1]. In equivalent plate modeling, the model characteristics are represented with polynomials, which require only a small fraction of the input data that would be required by a corresponding finite element model.…”

Section: Introductionmentioning
confidence: 99%

Static and Dynamic Structural Response of an Aircraft Wing with Damage Using Equivalent Plate Analysis
Krishnamurthy
¹
,
Tsai
²

2008
49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference &Amp;lt;br> 16th AIAA/ASME/AHS Ada
7
0
3
0
View full text Add to dashboard Cite

A process to generate an equivalent plate based on an optimization approach to predict the static and dynamic response of flight vehicle wing structures is proposed. Geometricscale and frequency-scale factors are defined to construct an equivalent plate with any desired scale to use in simulation and wind tunnel experiments. It is shown that the stiffness and the displacements are scaled linearly with the geometric-scale factor, whereas the load is scaled as the square of the geometric-scale factor. The scaled stiffness of the reference flight vehicle is matched first to construct the equivalent plate. Then the frequency-scale factor is defined to scale the flight vehicle frequencies. The scaled flight vehicle frequencies are matched by placing arbitrary point masses along the equivalent plate geometry. Two simple stiffened-plate examples, one with damage and another without damage, were used to demonstrate the accuracy of the optimization procedure proposed. Geometric-scale factors ranging from 0.2 to 1.0 were used in the analyses. In both examples, the static and dynamic response of the reference stiffened-panel solution is matched accurately. The scaled equivalent plate predicted the first five frequencies of the stiffened panel very accurately. Finally, the proposed equivalent plate procedure was demonstrated in a more realistic typical aircraft wing structure. Two scale equivalent plate models were generated using the geometric-scale factors 1.0 and 0.2. Both equivalent plate models predicted the static response of the wing structure accurately. The equivalent plate models reproduced the first five frequencies of the wing structure accurately.

show abstract

Section: Introductionmentioning
confidence: 99%

Frequency Response of an Aircraft Wing with Discrete Source Damage Using Equivalent Plate Analysis
Krishnamurthy
¹
,
Eldred
²

2007
48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
6
0
2
0
View full text Add to dashboard Cite

An equivalent plate procedure is developed to provide a computationally efficient means of matching the stiffness and frequencies of flight vehicle wing structures for prescribed loading conditions. Several new approaches are proposed and studied to match the stiffness and first five natural frequencies of the two reference models with and without damage. One approach divides the candidate reference plate into multiple zones in which stiffness and mass can be varied using a variety of materials including aluminum, graphite-epoxy, and foam-core graphite-epoxy sandwiches. Another approach places point masses along the edge of the stiffness-matched plate to tune the natural frequencies. Both approaches are successful at matching the stiffness and natural frequencies of the reference plates and provide useful insight into determination of crucial features in equivalent plate models of aircraft wing structures.

show abstract

Equivalent plate modeling for conceptual design of aircraft wing structures

Abstract: This paper describes an analysis method that generates conceptual-level design data for aircraft wing structures.

Cited by 42 publications

References 3 publications

Equivalent Plate Analysis of Aircraft Wing with Discrete Source Damage

Equivalent Plate Analysis of Aircraft Wing with Discrete Source Damage

Static and Dynamic Structural Response of an Aircraft Wing with Damage Using Equivalent Plate Analysis

Frequency Response of an Aircraft Wing with Discrete Source Damage Using Equivalent Plate Analysis

Contact Info

Product

Resources

About