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Rivet clamping assembly and method for using rivet clamping assembly to manufacture airplane skin maintenance gasket

A technology for clamping components and aircraft skins, which is applied in the direction of pins, connecting components, mechanical equipment, etc., can solve the problems of high drill size, shape and operation requirements, need for grinding, drilling deviation, etc., and improve the production success rate and work efficiency , The effect of easy disassembly and assembly

Pending Publication Date: 2018-12-07
TAIKOO XIAMEN AIRCRAFT ENG CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The main reasons are summarized as follows: In the absence of special rivet clamping tools, since the stem of the rivet is round, the surface is smooth, and the size is small, it is easy to slip when clamping the rivet with pliers or vise, resulting in Drilling deviation during the drilling process; the size, shape and operation requirements of the drill bit are high, and the operation process is prone to errors; burrs will appear in the drill bit, which needs to be polished, and it is difficult to grasp the appropriate angle to obtain the required size in the actual manual grinding operation

Method used

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  • Rivet clamping assembly and method for using rivet clamping assembly to manufacture airplane skin maintenance gasket
  • Rivet clamping assembly and method for using rivet clamping assembly to manufacture airplane skin maintenance gasket
  • Rivet clamping assembly and method for using rivet clamping assembly to manufacture airplane skin maintenance gasket

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Embodiment Construction

[0032] Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and thus their detailed descriptions will be omitted.

[0033]Although relative terms such as "upper" and "lower" are used in this specification to describe the relative relationship of one component of an icon to another component, these terms are used in this specification only for convenience, for example, according to the description in the accompanying drawings directions for the example described above. It will be appreciated that if the illustrated device is turned over so ...

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Abstract

The invention provides a rivet clamping assembly used for manufacturing a maintenance gasket needed by maintaining of airplane skin. The rivet clamping assembly comprises a first fixing plate, a second fixing plate and a locking nut. The first fixing plate is provided with a round hole and a screw rod. The second fixing plate is provided with a countersunk head rivet hole and a through hole. The countersunk head rivet hole comprises a conical countersunk head rivet part and a round hole part. The screw rod on the first fixing plate is matched with the through hole in the second fixing plate, and thus the first fixing plate and the second fixing plate are fixed together through the locking nut. When the second fixing plate and the first fixing plate are fixed together, the countersunk headrivet part of the countersunk head rivet hole in the second fixing plate faces one side, provided with the screw rod, of the first fixing plate, and the round hole in the first fixing plate is alignedto the round hole part of the countersunk head rivet hole in the second fixing plate. In addition, the invention further provides a method for using the rivet clamping assembly to manufacture the maintenance gasket needed by maintaining of the airplane skin.

Description

technical field [0001] The invention relates to the technical field of aircraft manufacturing, in particular to a method for manufacturing a repair gasket required for aircraft skin repair and a rivet clamping assembly used in the method. Background technique [0002] In the existing technology, such as figure 1 As shown, the aircraft skin 12 is an important structure coated on the outside of the body frame, and the aircraft skin 12 and the body structure 14 as well as the aircraft skin 12 and the aircraft skin 12 are usually assembled together by many rivets 13, In order to ensure the smoothness of the outer surface of the aircraft, countersunk rivets 13 are generally used, and the heads of the countersunk rivets 13 installed in the countersunk rivet holes are on the outermost skin. However, if the aircraft skin 12 is damaged and needs to be repaired, all original rivets 13 at the position to be repaired need to be removed, and then the repair skin 17 is installed at this ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16B13/10
CPCF16B13/04F16B13/10
Inventor 耿晓刚许珊珊王芳淮
Owner TAIKOO XIAMEN AIRCRAFT ENG CO LTD
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