Abstract: The integrated design of a flexible structure flutter active control law is researched. For the aeroservoelastic model carrying accelerated sensors with output feedback,the sensitive derivatives of the flutter speed with respect to the structural and control design variables are established in Laplace domain,and the analytical derivative of singular value with respect to the structural design variable is contributed also. Satisfactory results have been obtained by use of a rectangular wing model.The objective function is the minimal structural weight,subject to the inequal constraints of the flutter speed,and robust stability of the closed loop system.

Key words: integrated design, aeroser voelasticity, derivative, robust