Design method for vertical tail docking structure

Abstract

The invention provides a design method for a vertical tail docking structure. The design method is characterized in that an amount of single lug joints are respectively arranged at the root of a vertical tail at two sides of a course, a same amount of double lug joints are correspondingly arranged at a docking structure of the vertical tail, the diameters of holes in the single lug joints are equal to those of holes in the corresponding double lug joints, the axes of the holes are coaxial, bushes are pressed into docking through holes of the single lug joints and the double lug joints, and the single lug joints and the double lug joints are fixedly connected in a bolt connection mode. According to the invention, docking between the box section of a vertical tail composite material and fuselage lugs is realized in multi-point docking manner, so connection processing amount is reduced, connection workload is reduced, docking weight is lowered down, assembling workload is decreased, rapid docking between the vertical tail and a fuselage is realized, and connection of a few points enables the purpose of docking to be achieved and requirements on usage of an airplane to be met; thus, a development period is shortened, production cost is reduced, and maintainability and replaceability of a product are improved.

Description

technical field [0001] The invention belongs to the technical field of aircraft structure design, and in particular relates to a vertical tail butt joint structure design method. Background technique [0002] The docking structure of the vertical tail and the fuselage, wing, etc. generally adopts a profile-type docking plane to be docked in the form of bolt tension, or adopts dense ingot joint-type scattered points to dock in the form of bolt tension. These structural forms are difficult to assemble, and the docking plane needs to be finished, and the processing volume is large; for the safety of the structure, the weight of the docking is relatively large; the time required for the docking is long; the load bearing of the butt bolts in tension is not very ideal. See figure 1 and figure 2 shown. With the requirements of the current and future aircraft development cycle, rapid design, rapid manufacturing, and rapid assembly have become factors that must be considered in a...

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is: the vertical tail composite material box section is docked with the fuselage lugs in the form of multi-point docking, so as to solve the problems of rapid aircraft design, manufacture, assembly, maintenance, replacement, etc., and at the same time meet the minimum weight requirements of aircraft structure docking, and meet the Design requirements for aircraft structure butt joint strength and stiffness

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