Whole oil tank structure of airplane

Abstract

A whole oil tank structure of an airplane comprises a plurality of oil tank inner containers made of composite materials, a front beam, a rear beam, an upper wall board and a lower wall board; the oil tank inner containers are arranged between the upper wall board and the lower wall board; the front beam and the rear beam are connected with the front edges and rear edges of the upper wall board and the lower wall board respectively; adjacent walls among the oil tank inner containers are bonded to structural ribs of a wing; the oil tank inner containers are sealed containers prefabricated through composite materials; and the outer walls of the oil tank inner containers are in bonding curing with the adjacent upper wall board, the lower wall board, the front beam and the rear beam.

Description

technical field [0001] The invention relates to the aircraft design technology, in particular to the structural design of the integral fuel tank of the wing made of composite materials. Background technique [0002] The integral fuel tank of the wing of the aircraft is a device that uses the sealed space formed by the wing structure to store fuel. It has a simple structure and can effectively use the wing space and reduce the wing load. It is the main fuel tank structure in modern aircraft design. The existing integral fuel tank of the wing makes full use of the closed space formed by the structure itself to be sealed, so as to achieve the purpose of not only storing fuel but also providing lift of the aircraft, and saving the weight of the soft fuel tank. Modern integral fuel tanks are mainly metal structural integral fuel tanks, and some aircraft integral fuel tanks use a small amount of composite materials. Due to the superior properties of light weight, high strength an...

AI Technical Summary

Problems solved by technology

The reasons are as follows: firstly, the performance of composite materials was not well utilized, and the previous design of the integral fuel tank of the wing was directly copied, and the assembly method was adopted, which was difficult to assemble and it was difficult to ensure the assembly accuracy; secondly, according to the previous integral fuel tank design method, the main The mechanical structural parts ensure the oil-tight and air-tight requirements of the fuel tank, increase the overall assembly accuracy and structural rigidity requirements, and need to design a special sealing structure with high manufacturing requirements and small deformation capacity, and wing deformation is inevitable during aircraft flight , it is more difficult to manufacture technology with existing composite materials

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