Optimum Design of Composite Wing Structures with Twist Constraint for Aeroelastic Tailoring.

Abstract

The objective of this effort was to develop a method to design a minimum weight, fiber reinforced, composite wing structure with a specific twist constraint. Designing a wing for the desired twist is one of the main objectives in the concept of aeroelastic tailoring. The structure is analyzed by a finite element method and the design variables are modified by using a recurrence relation based on an optimality criteria. To demonstrate the method, a wing structure is designed to have a specific negative or positive twist corresponding to 'wash out' and 'wash in' conditions. The designs satisfy the twist constraint and the strength criteria in all elements. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1976
Accession Number
ADA038029

Entities

People

  • K. Schrader
  • L. Berke
  • N. S. Khot
  • V. B. Venkayya

Organizations

  • Flight Dynamics Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Aircraft Wings
  • Aircrafts
  • Composite Materials
  • Composite Wings
  • Deflection
  • Dynamics
  • Finite Element Analysis
  • Government Procurement
  • Graphitic Materials
  • Laminates
  • Mechanics
  • Optimization
  • Shear Modulus
  • Shear Stresses
  • Stiffness
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Control Systems Engineering.
  • Reinforced Composite Materials
  • Structural Health Monitoring of Composite Structures.