A clamping device for fixing the horizontal and vertical tail of an aircraft

Abstract

The invention discloses a clamping device for fixing the horizontal and vertical tail of an aircraft, which comprises a disc-shaped base assembly and a claw assembly, wherein: the disc-shaped base assembly includes a disc-shaped base body and a A suction cup at one end of the disc-shaped base body; the claw assembly is arranged on the disc-shaped base body and away from the end of the suction cup; the claw assembly includes a slide plate, a joint arm hinged with the slide plate, and a detachable A clamping portion installed on the articulated arm and away from one end of the slide plate, the slide plate is connected with the disc-shaped base body and can move circularly around the central axis of the disc-shaped base body. According to the disclosed solution, the clamping device used for fixing the horizontal and vertical tail of an aircraft can achieve the purpose of improving assembly accuracy.

Description

technical field [0001] The invention relates to the field of aviation technology, in particular to a clamping device for fixing the vertical tail of an aircraft. Background technique [0002] In the field of aerospace, the assembly of horizontal tail, vertical tail and fuselage of aircraft is mostly shaft-hole assembly or single- and double-ear plug-in assembly, which requires high assembly precision. The current assembly method mostly adopts manual hoisting and clamping. The operation method of manual hoisting and clamping is as follows: the assembly worker first installs the lifting point joint on the surface of the horizontal tail and vertical tail; through a special spreader, one end is connected to the hook of the crane in the factory building, and the other end is connected to the lifting point joint of the aircraft’s horizontal tail and vertical tail. The factory crane lifts the horizontal tail and vertical tail of the aircraft to the position of the fuselage to be a...

AI Technical Summary

Problems solved by technology

[0003] This traditional clamping method adopts the manual lifting operation method, which has the following disadvantages: First, the lifting point joint is rigidly connected with the horizontal tail and vertical tail, and cannot be adjusted after installation, so the lifting point needs to be specially designed for each aircraft product The design and calculation workload of the joint and the calculation of the lifting point position is heavy; secondly, the connection between the lifting point joint and the horizontal tail and the vertical tail is connected by borrowing the connection holes between the aircraft frame and the skin, resulting in the riveting of the horizontal tail and the vertical tail cannot be fully completed. It is necessary to reserve a process hole to install the lifting point. After the assembly is completed, the riveting work will be carried out to increase the assembly workload; then, during the hoisting process of the horizontal tail and vertical tail, it is through the soft connection method of the lifting rope. During the assembly process, the crane moves It will lead to unavoidable random swing of the product, low reliability, which is not conducive to high-precision alignment and assembly operations, increases the difficulty of assembly, and is prone to collisions between aircraft products, bringing quality and safety risks

[0004] To sum up, the traditional clamping method of hoisting cannot meet the high-precision assembly requirements of horizontal and vertical tails. The assembly workers need to complete the shaft-hole fit or single- and double-ear plug-in assembly through repeated trial and error.

At the same time, the traditional clamping method of hoisting cannot meet the clamping and fixing requirements of different products. When the product size changes or the product is changed, it is necessary to redesign the lifting point joint and calculate the lifting point position, which affects production efficiency.

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