Installation method of aircraft panel and calculation method of assembly gap between aircraft panel and framework

Abstract

The invention relates to an installation method of an aircraft panel and a calculation method of an assembly gap between the aircraft panel and a framework, and belongs to the technical field of digital assembly of large aircrafts. The installation method comprises an assembly clearance calculation step, a pressing scheme design step and a fixed connection step. In the assembly clearance calculation step, the assembly clearance of a wing box panel is represented by obtaining the inner contour curve of the panel and the outer contour curve of the framework and solving the area of the clearancebetween the two contour curves through curve integration. In the pressing scheme design step, whether the area of the clearance is larger than the area of the critical clearance or not is judged, andif yes, pressing treatment needs to be conducted. In the fixed connection step, according to the result obtained in the pressing scheme design step, a pressing device is used for extruding an assembling clearance between an inner-shaped boss and the framework appearance till the area of the current clearance is smaller than the area of the critical clearance. The mounting method can effectively eliminate the assembly clearance of a wing box panel, and can be widely applied to the technical field of manufacturing of large aircrafts.

Description

technical field [0001] The invention relates to the technical field of digital assembly of large aircraft, in particular to an installation method of an aircraft panel and a calculation method for an assembly gap between a wing box panel and a frame. Background technique [0002] In the aircraft manufacturing process, assembly accounts for about 40%-50% of the total manufacturing labor, and directly determines the final quality, production cost and manufacturing cycle of the product. Although the equipment disclosed in patent documents such as publication number CCN105665605A is used to carry out automatic hole making and assembly of parts such as wall panels, in the assembly process of large parts of the aircraft, because a considerable part of the components are large-scale weak rigid thin-walled structures, As a result, these parts and components are extremely prone to errors and deformations during part processing, component assembly, and component assembly; However, va...

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Problems solved by technology

Although the equipment disclosed in patent documents such as publication number CCN105665605A is used to carry out automatic hole making and assembly of parts such as wall panels, in the assembly process of large parts of the aircraft, because a considerable part of the components are large-scale weak rigid thin-walled structures, As a result, these parts and components are extremely prone to errors and deformations during part processing, component assembly, and component assembly; However, various error sources continue to spread and accumulate during the step-by-step assembly process, which makes the aircraft panel and frame deviate from their nominal shape and size, so that the internal shape and frame of the aircraft panel There is a non-negligible assembly gap between the shapes

[0003] During the installation of the wing panel, the existence of the assembly gap will lead to the following problems: (1) The burr from the hole can easily enter the assembly gap and scratch the product; (2) When the panel is disassembled and reset, the fastening hole on the frame It is difficult to align the position; (3) After the wallboard is connected to the frame, it is easy to cause the wallboard to bulge

[0004] In order to solve the above technical problems, the common practice is to use cushioning compensation and wall plate compression to solve this problem, in which the assembly gap is measured and evaluated manually with a feeler gauge, and it is difficult to accurately obtain the assembly gap by this measurement and evaluation method. The overall situation has resulted in the padding and compaction process relying heavily on manual experience and technical level, which hinders the realization of the digital padding and compaction process

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