Optimisation of stiffened panels using finite strip models. The key features of the finite strip buckling analysis program VICONOPT are described. A bi-level strategy, for the efficient optimum design of composite stiffened panels is also presented. Panel level optimization finds a minimum weight cross-sectional geometry based on a substitution of equivalent orthotropic plates for laminated plates. Optimization at the laminate level finds stacking sequences satisfying laminate design rules using either manual selection or a genetic algorithm. VICONOPT models are validated with ABAQUS finite element models, and with experimental compressive testing of two blade-stiffened panels. The buckling and postbuckling behaviour of the two panels, with initial buckling in the stiffeners and skin, respectively, is investigated in a high load and high strain range. The bi-level strategy is evaluated by design of a Z-stiffened example, which has been manufactured and tested, and also by design of a wing cover panel which is subject to compression and lateral pressure. The optimum wing panel, considering a variety of stiffener shapes, is 17% lighter than an existing datum design.

References in zbMATH (referenced in 18 articles )

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  1. Butler, Richard; Rhead, Andrew T.; Liu, Wenli; Kontis, Nikolaos: Compressive strength of delaminated aerospace composites (2012)
  2. Montemurro, Marco; Vincenti, Angela; Vannucci, Paolo: A two-level procedure for the global optimum design of composite modular structures -- application to the design of an aircraft wing (2012)
  3. Butler, Richard; Liu, Wenli: Optimisation of stiffened panels using finite strip models (2008)
  4. Rhead, Andrew T.; Butler, Richard; Hunt, Giles W.: Post-buckled propagation model for compressive fatigue of impact damaged laminates (2008)
  5. Casimir, J.B.; Kevorkian, S.; Vinh, T.: The dynamic stiffness matrix of two-dimensional elements: application to Kirchhoff’s plate continuous elements (2005)
  6. Lamberti, Luciano; Venkataraman, Satchi; Haftka, Raphael T.; Johnson, Theodore F.: Preliminary design optimization of stiffened panels using approximate analysis models (2003)
  7. Williams, Frederic W.; Kennedy, David; Djoudi, Mohamed S.: The member stiffness determinant and its uses for the transcendental eigenproblems of structural engineering and other disciplines. (2003)
  8. Chan, K. L.; Kennedy, D.; Williams, F. W.: Parallel design methods for optimising lightweight structures (2000)
  9. Sun, G.; Kennedy, D.; Williams, F.W.: A post-buckling analysis for isotropic prismatic plate assemblies under axial compression (2000)
  10. Watson, A.; Kennedy, D.; Williams, F.W.: Design of structures by a splitting method (1999)
  11. Edwards, Dyfan A.; Williams, Fred W.; Kennedy, David: Cost optimization of stiffened panels using VICONOPT (1998)
  12. Watson, Andrew; Williams, Fred W.; Kennedy, David: Buckling load reduction for stiffened panels due to cutouts in ribs (1998)
  13. York, C.B.; Williams, F.W.: Aircraft wing panel buckling analysis: Efficiency by approximations (1998)
  14. Powell, S.M.; Kennedy, D.; Williams, F.W.: Efficient multi-level substructuring with constraints for buckling and vibration analysis of prismatic plate assemblies (1997)
  15. Sun, G.; Williams, F.W.: An initial post-buckling analysis for prismatic plate assemblies under axial compression (1997)
  16. Butler, R.; Tyler, A.A.; Cao, W.: Optimum design and evaluation of stiffened panels with practical loading (1994)
  17. Anderson, Melvin S.; Kennedy, David: Transverse shear deformation in exact buckling and vibration of composite plate assemblies (1993)
  18. Bushnell, David: Optimization of composite, stiffened, imperfect panels under combined loads for service in the postbuckling regime (1993)