Application of Topology Optimization in the Design of Composite Fuselages of Civil Aircraft

Due to the many problems in the traditional design scheme of civil aircraft, such as low structural efficiency caused by traditional material distribution, contradiction between lightweight and airworthiness requirements, limitations of complex structure manufacturing process, and full life cycle cost control, this paper proposes to use topology optimization method to design lightweight composite fuselage structure, combine advanced manufacturing technology with structural optimization, and promote the engineering application of composite materials. In this paper, the method of literature analysis and review is mainly studied to study the topology optimization method of civil aircraft composite fuselage structure oriented to manufacturing constraints, and analyzes the synergistic optimization of ply parameters and topological configuration and the feasibility verification of its application to engineering. After analysis, this paper finds that the aircraft fuselage designed with this scheme takes into account both strength and fatigue resistance. Specifically, by collaboratively optimizing the material distribution and fiber laying direction, the weight of the fuselage structure can be reduced under the premise of meeting the core requirements such as strength, stiffness and fatigue performance, thereby reducing fuel consumption and carbon emissions.