A riveting tool and riveting method suitable for aircraft composite material vertical tail wing box

Abstract

The invention relates to a sealing and riveting tool and a sealing and riveting method applicable to a composite vertical tail wing box of an airplane. According to a technical scheme in the invention, the sealing and riveting tool is such structured that a handle is connected with an extension tube; the extension tube is connected with a magnetic chuck; one end of a wind pipe is connected with awind-controlled switch, and the other end of the wind pipe passes through the handle and the extension tube and then communicates with the magnetic chuck; and an endoscope lens is mounted on the magnetic chuck and is connected with a display screen through a wire. As the sealing and riveting tool is employed for sealing and riveting of the composite vertical tail wing box of the airplane, a fastener can be inserted into a pre-drilled fastener hole in the enclosed wing box under the guidance of the endoscope lens, and then the wind-controlled switch on the wind pipe is turned on so as to fix stringers and / or angular pieces in an enclosed box section via the fastener. According to the invention, the assembling sequence of the wing box is rationally formulated, an endoscope is cooperatively used for observation and is manually hand-held, and the installation of fasteners between stringers and angular pieces is realized through an inherent lightening hole in the wing box, so engineering requirements are met.

Description

technical field [0001] The invention relates to a riveting tool and a riveting method, in particular to a riveting tool and a riveting method suitable for installing fasteners inside a closed aircraft vertical tail box. Background technique [0002] The vertical tail wing box of the C919 large passenger aircraft is made of advanced composite materials. It is very difficult to install fasteners (single-sided threaded core pulling nails) for the connection between the pieces. At present, there is only the inherent "lightening hole" on the beam that constitutes the lower end of the "closed box section" of the vertical empennage box, and the diameter of this hole is only φ104mm, and the maximum distance from the location where the fastener is installed is about 700mm. At present, domestic, There are two methods of external closure riveting: rolling riveting and dismantling after pre-installation to provide access. However, due to the constraints of the selected material and str...

AI Technical Summary

Problems solved by technology

[0002] The vertical tail wing box of the C919 large passenger aircraft is made of advanced composite materials. The connection between the pieces, the installation of fasteners (single-sided thread core pulling nails) is very difficult

At present, there is only the inherent "lightening hole" on the beam that constitutes the lower end of the "closed box section" of the vertical empennage box, and the diameter of this hole is only φ104mm, and the maximum distance from the location where the fastener is installed is about 700mm. At present, domestic, There are two methods of external closure riveting: rolling riveting and dismantling after pre-installation to provide access. However, due to the constraints of the selected material and structural shape factors, the two methods cannot be adopted on this aircraft. Since the panel structure is composite material, the inner surface of the skin There are glued long trusses, so the skin riveting scheme cannot be implemented; in addition, the front and rear beams are both I-shaped and have a closed angle design, so the beams cannot be dismantled or reset after pre-installation, and the access scheme for dismantling parts cannot be implemented. Implementation; due to the large size of the product structure, conventional installation tools cannot reach the position of each corner piece

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