Abstract: This paper describes an optimum design method that is to use DASCM program for solving the structure design of the composite wings with inner integrated tanks and multiple external stores. A sensitivity analysis and derivative homogenization of laminating design for composite structures are used in this paper. An example of a composite wing is illustrated in this paper. After optimum design the weight of this wing was increased only by 0.84kg, but the flutter speed was raised by 22.6%.

Key words: composite, wing, laminating design