bố trí thiết bị nhà máy và tạo ra các thiết kế thiết bị. Những mô tả này được dự định để cung cấp một cái nhìn tổng quan cao cấp, biết thêm thông tin chi tiết có thể được tìm thấy trong bài báo, tờ thông tin được liệt kê sau. Xin hỏi đối tác kênh của bạn cho một bản sao hoặc tải về trực tiếp từ | Altair Engineering The Altair Technology Conference 2004 Topology Optimization of Aircraft Wing Box Ribs Lars Krog Alastair Tucker Airbus UK New Technical Centre Filton House Filton Bristol BS99 7AR and Martin Kemp Richard Boyd Altair Engineering Ltd Vanguard Centre Sir William Lyons Road Coventry CV4 7EZ kemp@ AIRBUS Altair Engineering Abstract This paper considers the application of conventional energy based topology optimization methods for design of aircraft wing box ribs. Compared to standard topology optimization work undertaken at Airbus the topology optimization of wing box ribs posed several additional challenges mainly due to the wing box ribs being embedded in a redundant wing box structure. Several approaches to solving this problem have been investigated and are being reported as part of this paper including a global analysis optimization approach and two local analysis optimization approaches. The paper also deals with both the selection of a suitable objective constraint function formulation for topology optimization and selection of a suitable formulation for handling multiple load cases in topology optimization but does not deal with any detailed sizing optimization of topology optimized designs. Keywords Design Optimization OptiStruct Wing Rib Topology Substructuring Introduction Airbus has recently been using topology optimization methods as an efficient gateway to obtain new and lighter component designs for the A380 aircraft. Most successful were the redesign of the A380 inboard inner fixed leading edge ribs the redesign of the A380 inboard outer fixed leading edge ribs 1 and finally the redesign of A380 fuselage door intercostals 1 . The three A380 topology optimization applications are today believed to have contributed weight savings in the order of 1000kg per aircraft. Initial Airbus applications of topology optimization were limited to consider components with well defined local loads. Both the .
