Inclusion of transverse shear deformation in optimum design of aircraft wing panels
Inclusion of transverse shear deformation in optimum design of aircraft wing panels
- New search for: Williams, P.W.L.
- New search for: Williams, F.W.
- New search for: Kennedy, D.
- New search for: Williams, P.W.L.
- New search for: Williams, F.W.
- New search for: Kennedy, D.
The well established computer program VICONOPT has been used to investigate the effects of using transverse shear deformation plate theory (SDPT) instead of classical plate theory (CPT) when designing prismatic, stiffened, laminated panels, e.g. aircraft wing panels, for minimum mass. The use of SDPT for final design is found to be advisable, with CPT being appropriate for preliminary design, because SDPT design gives a mass only slightly higher than that of CPT design but analysis of the CPT design by SDPT shows that it is unable to carry the design load by as much as 7 % or more. These differences occur for the many design situations for which local buckling is an active constraint, i.e. critical, at the optimum design but not for the many other situations in which local buckling is not critical. Results are given to indicate how these differences vary with skin thickness, out-of-plane shear moduli, design load, multiple load cases, permissible fiber strains, type of stiffener, stiffener pitch, the introduction of skew into the panel, etc.
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Inclusion of transverse shear deformation in optimum design of aircraft wing panels
Einbeziehung der Querscherverformung in die Optimalauslegung von Flugzeug-Tragflügelfeldern
1996
8 Seiten, 7 Bilder, 9 Tabellen, 12 Quellen
Conference paper
English
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