In order to control an aircraft without rudder and improve its aerodynamic performance through variable camber wing, a lightweight structure that is capable of withstanding loads and changing shape should be designed coordinately. The cost and weight of traditional mechanism and the load-carrying ability of smart material must be fully considered. Thus, traditional mechanism and smart material should be configured according to the aerodynamic loads on the wing. Combined with topology optimization, a variable camber wing with load-carrying capability and deformability is realized by integrated design of structure and mechanism. The results show that the aircraft is able to change its shape in different flight environments and withstand various loading conditions. It is concluded that aircraft with variable camber wings by integrated design of structure and mechanism can adapt its aerodynamic shape to obtain better performances, such as flight efficiency and ability to adjust to flight environments.