Static Aeroelastic Considerations in the Definition of Design Loads for Fighter Airplanes,

Abstract

This paper first discusses some typical effects of static aeroelastic correction factors in context with the definition of structural design loads for major aircraft components. The influences on response parameters and resulting design loads are shown as well as the aeroelastic optimization of trailing edge flaps with respect to geometry, efficiency and hinge moments.

Document Details

Document Type
Technical Report
Publication Date
Oct 03, 1986
Accession Number
ADP005856

Entities

People

  • G. Schmidinger
  • O. Sensburg

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircraft Equipment
  • Aircrafts
  • Airplanes
  • Efficiency
  • Fighter Aircraft
  • Fixed Wing Aircraft
  • Geometry
  • Mathematics
  • Military Aircraft
  • Optimization
  • Topology
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Software Engineering.