A design procedure is presented which utilizes (1) the active control technologies such as Flutter Mode Control, Gust Load Alleviation and Maneuver Load Control to relax the strength and stiffness requirements on wing structure, and (2) structural optimization to derive the minimum weight composite wing structures satisfying the relaxed structural requirements. The design procedure is applied to the preliminary design study of a Supersonic Commercial Transport configuration with laminated composite wing structure. Four design configurations are compared. Maximum of about 30% structural weight reduction was achieved from the quasi-isotropic design. Also some insights on the characteristics of the Supersonic Commercial Transport configuration are discussed.