| Boarding door is an important and special moving part bearing high differential pressure load inthe fuselage. It must meets the design requirements including stiffness, strength, fatigue, air tightnessand reliability. In addition, the structure should be as light as possible. Using composite materials inaircraft structures is an important way to reduce weight. In this paper, a research on structure designand analysis of composite boarding door was carried out according to the CCAR and design criteriafor composite structure and the problems in the design of composite boarding door has beenresearched. So this paper has laid a foundation for the engineering use of composite doors. The mainfeatures for this paper were stated as follows:(1) Brief introduction and the background of the boarding door were summarized, and thepresent research situation of composite doors was also given out. After that the criterion of boardingdoor according to the requirement of airworthiness and composite structure design was determined. Atthe same time the design principle of mechanical connection for composite material was alsointroduced;(2) Then the preliminary layout of the boarding door including the geometric configurations andthe layup of the major components was determined. The main connection of the structure had alsobeen determined;(3) Next three different design options of longitudinal beam based on the preliminary layoutwere established. The design options were analyzed using FEM and then the best one was chosenaccording to the strain analysis result and the weight of structure;(4) At last the strain of the best design option were analyzed under all required loadingconditions, after that the structural strength was analyzed: Firstly the bolt load distribution of the doorwas calculated by using fastener element in model, then the strength of fasteners and metalcomponents was checked; at last the pulling out and bearing strength of structural components wereanalyzed using single-bolt model. |
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