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Sealing and riveting tool and sealing and riveting method applicable to composite vertical tail wing box of airplane

A composite material and vertical tail technology, which is applied to household appliances, other household appliances, household components, etc., can solve the problems of inability to reset, large product structure and difficult installation of fasteners, etc., to achieve a wide range of applications and improve product quality. , the effect of reducing the impact of structural strength

Active Publication Date: 2019-01-01
AVIC SAC COMML AIRCRAFT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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

Method used

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  • Sealing and riveting tool and sealing and riveting method applicable to composite vertical tail wing box of airplane
  • Sealing and riveting tool and sealing and riveting method applicable to composite vertical tail wing box of airplane
  • Sealing and riveting tool and sealing and riveting method applicable to composite vertical tail wing box of airplane

Examples

Experimental program
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Effect test

Embodiment 1

[0026] Such as figure 1 with figure 2 As shown, a riveting tool suitable for an aircraft composite material vertical tail wing box includes an endoscope lens 1, a magnetic chuck 2, an extension tube 3, a handle 4, a wind pipe 5, a wind control switch 6 and a display screen 7. .

[0027] The handle 4 is connected with the extension tube 3, and the extension tube 3 is connected with the magnetic chuck 2. One end of the air tube 5 is connected to the wind control switch 6, and the other end passes through the handle 4 and the extension tube 3 and then communicates with the magnetic chuck 2. The endoscope lens 1 is installed on the magnetic chuck 2, and the endoscope lens 1 is connected to the display screen 7 through a wire.

[0028] The magnetic chuck 2 is provided with a groove 2-1, and a permanent magnet 2-2 is arranged in the groove 2-1.

Embodiment 2

[0030] During the assembly process of the aircraft, the vertical tail wing box of the aircraft is composed of the right side wall plate I10 and the left side wall plate II20 to form a "closed box section". The beam at the lower end of the "closed box section" is provided with a "lightening hole" 40. The inside of the "closed box section" that constitutes the wing box is supported by ribs. All of the above are composite materials. At the joint between the ribs and the long truss, the design uses connecting corners to strengthen the structural strength. There are 82 corners in total, and each corner is on Two fasteners need to be installed in a closed space.

[0031] A method for sealing riveting suitable for aircraft composite material vertical tail wing box, using the riveting tool suitable for aircraft composite material vertical tail wing of embodiment 1, includes the following steps:

[0032] 1) Such as image 3 As shown, the two wall panels that constitute the vertical tail wi...

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PUM

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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 wing box. Background technique [0002] The vertical tail wing box of C919 large passenger aircraft is made of advanced composite materials, the structure is closed, the assembly space is narrow, and the range of internal operation space is very limited, especially the long truss and ribs and corners of the inner (left and right) wall panels of the wing box. For the connection between the pieces, it is difficult to install the fasteners (single threaded core nails). At present, there is only the inherent "lightening hole" in the beam forming the lower end of the "closed box section" of the vertical tail wing box. The diameter of this hole is only φ104mm, and the maximum distance to the installation fastener position is about 700mm. The external closed riveting methods...

Claims

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Application Information

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IPC IPC(8): B29C65/56B29L31/30
CPCB29C65/56B29L2031/3085
Inventor 宋强李论刘振山于潇李艳军姚嘉宁白庆国
Owner AVIC SAC COMML AIRCRAFT
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