Composite material aeroelastic tailoring is presently explored as a means for the correction of the roll trim imbalance of oblique-wing aircraft configurations. The concept is demonstrated through the analysis of a realistic oblique wing by a static aeroelastic computational procedure encompassing the full potential transonic aerodynamic code FLO22 and a Ritz structural plate program that models the stiffness due to symmetrical-but-unbalanced composite wing skins. Results indicate that asymetric composite tailoring reduces the aileron deflection needed for roll equilibrium, and reduces control surface hinge moment and drag. Wing skin stresses are, however, very high.
Aeroelastic tailoring for oblique wing lateral trim
Structures, Structural Dynamics and Materials Conference ; 1988 ; Williamsburg, VA, United States
01.01.1988
Aufsatz (Konferenz)
Keine Angabe
Englisch
Aeroelastic tailoring for oblique wing lateral trim
AIAA | 1988
|Aeroelastic control of oblique-wing aircraft
NTRS | 1986
|Aeroelastic Control of Oblique-Wing Aircraft
NTIS | 1986
|