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Equivalent plate analysis of aircraft wing box structures with general planform geometryA new equilvalent plate analysis formulation is described which is capable of modeling aircraft wing structures with a general planform such as cranked wing boxes. Multiple trapezoidal segments are used to represent such planforms. A Ritz solution technique is used in conjunction with global displacement functions which encompass all the segments. This Ritz solution procedure is implemented efficiently into a computer program so that it can be used by rigorous optimization algorithms for application in early preliminary design. A direct method to interface this structural analysis procedure with aerodynamic programs for use in aeroelastic calculations is described. This equivalent plate analysis procedure is used to calculate the static deflections and stresses and vibration frequencies and modes of an example wing configuration. The numerical results are compared with results from a finite element model of the same configuration to illustrate typical levels of accuracy and computation times resulting from use of this procedure.
Document ID
19860012483
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Giles, G. L.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
March 1, 1986
Subject Category
Structural Mechanics
Report/Patent Number
NAS 1.15:87697
AIAA PAPER 86-0940-CP
NASA-TM-87697
Meeting Information
Meeting: AIAA/ASME/ASCE/ANS Stuctures, Structural Dynamics and Materials Conference,
Location: San Antonio, TX
Country: United States
Start Date: May 19, 1986
End Date: May 21, 1986
Accession Number
86N21954
Funding Number(s)
PROJECT: RTOP 505-63-11-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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