Analysis On Composite Wing Fuel Tank Seal Deformation

In recent years, the overall use more advanced form of aircraft fuel tank structure, domesticthird-generation combat aircraft are beginning to use the whole tank structure. On large mannedaircraft, its overall fuel tank usually rigid aluminum or titanium alloy produced better overallstrengthening of siding and skeleton, connected by a seal to form the entire structure. Use of spaceinside the aircraft structure to the overall arrangement of the wing fuel tank, you can in order toincrease aircraft fuel storage and prolong life, reduce the weight of the aircraft structure, improveflight performance of the aircraft. Therefore, the rational design of the overall structure of the aircraftfuel tanks, aircraft design is not only an indispensable part of, but also easy to use and maintenanceof aircraft.In this thesis, the overall composite wing tank structural arrangement and consider the overalldeformation of the tank sealed connection between the skin panels and beams, rib cage. Under thewing bending deformation conditions exist between the wing skin panels and spar of relatively largerelative deformation, and therefore the focus of this project is connected deformation analysis of skinpanels and spar between the bars. Related to the factors that affect the size of the seal deformation lot,this article aims to come up with a simple box-segment model factors and laws, and then seal appliedresearch to guide the overall design of the actual wing tank. In the analysis process, step by stepanalysis of the influence of oil on the seal deformation; Then change the connection rivets margins,row spacing, and the establishment of a simplified beam element model, using the finite elementresults with the theoretical model results were compared to verify and derive rivets margins influenceof row spacing. For sealing deformation characteristics for targeted analyzes, the study skin, spar capmodel variability law under axial loads, and create a theoretical model to calculate the equivalentstiffness, transformed into simplified beam element model of composite laminates stiffness influenceof deformation on the size of the seal. Based on the final results, the actual guidance of the wing sealdesign model and optimized to achieve the structural design and seal design requirements.