Accession Number:

ADA359832

Title:

Design Optimization of Stiffened Composite Panels With Buckling and Damage Tolerance Constraints; Presented at the AIAA-SDM Conference (39th) Held at Long Beach, California on April 20-23 1998

Descriptive Note:

Corporate Author:

NATIONAL AEROSPACE LAB AMSTERDAM (NETHERLANDS)

Report Date:

1998-01-01

Pagination or Media Count:

15.0

Abstract:

The design of stiffened, composite wing panels must satisfy a range of requirements related to performance, economy and safety. In particular, the design must be damage tolerant to satisfy a number of different performance requirements for various states of damage. To obtain an optimum configuration that satisfies these requirements simultaneously, optimization code PANOPT was extended with a multi-model capability. First, the effect of damage tolerance constraints on postbuckled optimum design was established for blade- I- and hat-stiffened panels with stiffener flanges embedded in the skin. The classical order of efficiency for optimized panels designed for buckling alone hats, Is, blades was no longer valid, as the masses of the three panel types were approximately equal. To obtain realistic damage models, the failure mechanisms and damage tolerance of the panel concept with embedded stiffeners were determined in an experimental programme. Finally, the multi-model capability PANOPT was demonstrated with the simultaneous optimization of undamaged panel carrying design ultimate load, the same panel with a separated stiffener carrying design limit load, and the panel with a cut stiffener carrying seventy percent of the design limit load. An optimum design was found with an additional mass of only five percent compared to a panel optimized for the undamaged case alone.

Subject Categories:

  • Aircraft
  • Laminates and Composite Materials
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE