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.
Static Aeroelastic Considerations in the Definition of Design Loads for Fighter Airplanes
1986
20 pages
Report
Keine Angabe
Englisch
Aerodynamics , Fluid Mechanics , Aeroelasticity , Aerodynamic control surfaces , Aerodynamic loading , Structural components , Statics , Corrections , Mathematical models , Optimization , Flaps(Control surfaces) , Reprints , Foreign technology , Military aircraft , Structural loads , Component reports