Efficient Method for Aeroelastic Tailoring of Composite Wing to Minimize Gust Response

Table 1

Initial and optimized laminate layups, stiffness, and deflection.

Status	Panels	Laminate layup (deg)	Stiffness and deformation
Initial design	Upper skin	[0.0/45.0/−45.0/90.0] s	EI = 6.80 ⋅10^5 KN⋅m^2
	Lower skin	[0.0/45.0/−45.0/90.0] s	GJ = 3.77 ⋅ 10^5 KN⋅m^2
	Upper/lower skin thickness	2 mm for each layer	Wingtip deflection: 0.32 m
	Front spar web	[0.0/45.0/−45.0/90.0] s	Wingtip twist: −0.94 deg
	Rear spar web	[0.0/45.0/−45.0/90.0] s	Shear force at wing root: 142.7 KN
	Front/rear spar thickness	6 mm for each layer	Torque at wing root: −87.7 KN⋅m
Optimized design	Upper skin	[0.0/76.2/−84.1/90.0] s	EI = 5.49 ⋅ 10^5 KN⋅m^2
	Lower skin	[0.0/76.2/−84.1/90.0] s	GJ = 1.09 ⋅ 10^5 KN⋅m^2
	Upper/lower skin thickness	2 mm for each layer	Wingtip deflection: 0.36 m
	Front spar web	[0.0/89.9/−89.9/90.0] s	Wingtip twist: −1.70 deg
	Rear spar web	[0.0/89.9/−89.9/90.0] s	Shear force at wing root: 127.2 KN
	Front/rear spar thickness	6 mm for each layer	Torque at wing root: −78.2 KN⋅m