Abstract: This paper deals with aeroelastic tailoring of composite wing surfaces. The objective function is structural weight. Multi-constraints, such as displacements, flutter speed and gauge requirements, are taken into consideration. Finite element method is used to the static analysis. Natural vibration modes are obtained by the spectral transformation Lanczos method. SUM onic doublet lattice method is used to obtain the unsteady aerodynamics. The critical flutter speed is generated by V-g method. The optimal problem is solved by the feasible direction method. The thickness of tke composite wing skin is simulated by bi-cubic polynomials, whose coefficients and the cross-sectional areas or thicknesses of other finite elements are the design variables. The scale of the problem is reduced by variable linkage. Derivative analysis is performed analytically. One composite wing box and a sweptback composite wing are optimized at the end of the paper.

Key words: composit, wing surfaces, aeroela:aic tailoring