Authors: JiHong Zhu WenJie Guo WeiHong Zhang Tao Liu
Publish Date: 2016/12/29
Volume: 56, Issue: 1, Pages: 21-45
Abstract
The purpose of this paper is to present an extended integrated layout and topology optimization method dealing with the multiframe and multicomponent fuselage structure systems design Considering an aircraft or aerospace fuselage system including main structure numbers of frames and featured components located on the frames a simultaneous optimization procedure is proposed here including geometrical design variables of components and frames as well as topological design variables of main structure and frame structures The multipoint constraints MPC scheme is used to simulate the rivets or bolts connecting the components frames and structures The finite circle method FCM is implemented to avoid the overlaps among different components and frames Furthermore to deal with the difficulties of large numbers of nonoverlapping constraints a penalty method is used here to compose the global strain energy and nonoverlapping constraints into a single objective function To guarantee the fuselage system’s balance the constraint on the system centroid is also introduced into the optimization Different numerical examples are tested and the optimized solutions have demonstrated the validity and effectiveness of the proposed formulation
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