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Aircraft cap rotation hinge device

A technology of rotating hinges and flaps, which is applied to aircraft power units, aircraft power unit components, and aircraft accessories. It can solve the problems of affecting local aerodynamic performance and poor sealing performance, and achieves the problem of sealing performance and occupying internal space. contradictory effect

Inactive Publication Date: 2019-01-29
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] 1. It is necessary to reserve a gap for the hinge strip in the structure, resulting in poor sealing;
[0004] 2. The P-type head of the hinge will protrude from the surface of the theoretical shape and affect the local aerodynamic performance

Method used

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specific Embodiment

[0018] The invention provides a rotary hinge device for an aircraft hatch such as figure 1 As shown, it can be used in the connecting part of the quick-release maintenance cover, which includes hinge 1 and hinge skin 2. Hinge 1 is preferably made of 2A12-T4-XC01-6 hard aluminum alloy material, and hinge skin 2 is preferably Made of 2A12-O aluminum alloy material, hinge 1 includes left hinge piece 11 and right hinge piece 12, hinge skin 2 is integrally formed structure, one end of which is the first skin section 21, and the other end is the third cover Leather segment 23, the middle of the first skin segment 21 and the third skin segment 23 is the second skin segment 22;

[0019] Such as figure 2 As shown, the right hinge piece 12 of the hinge 1 is fixed to the frame 5 of the fuselage, and the first skin segment 21 is flat and fixed to the left hinge piece 11 of the hinge 1, which is preferably fixed by riveting , the third skin section 23 is flat and fixed with the mouth co...

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PUM

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Abstract

The invention relates to the technical field of aircraft structural design, in particular to an aircraft cap rotation hinge device. The devcie comprises a hinge and a hinge skin. A right hinge leaf ofthe hinge is fixed to a fuselage frame. The hinge skin is integrally formed, and two ends of the hinge skin are respectively a first skin segment and a third skin segment, and a second skin segment is between the first skin segment and the third skin segment. The first skin segment is flat and is fixed with a left hinge leaf of the hinge. The third skin segment is flat and is fixed to a cap. Thehinge device does not need an additional accessory structure and does not need to add unnecessary gaps on a structure body and the cap, and can ensure sealing property of the cap and maximization of an opening angle. Thus, a contradiction of sealing property and internal space occupation of a traditional cap connecting method is solved. The device also does not highlight a theoretical shape, and can solve a connection problem of a maintenance cap having sealing requirement with a system that is close to the structure.

Description

technical field [0001] The invention relates to the technical field of aircraft structure design, in particular to an aircraft flap hinge device. Background technique [0002] At present, the commonly used connection method of the maintenance cover on the aircraft engine nacelle is a hinge connection method, which is to connect two hinges to the cover and the structural body respectively. This hinge connection method has the following disadvantages: [0003] 1. It is necessary to reserve a gap for the hinge strip in the structure, resulting in poor sealing; [0004] 2. The P-shaped head of the hinge will protrude from the surface of the theoretical shape and affect the local aerodynamic performance. Contents of the invention [0005] In order to overcome at least one defect in the above-mentioned prior art, the present invention provides a rotary hinge device for an aircraft hatch, comprising a hinge and a hinge skin, the right hinge of the hinge is fixed to the frame of ...

Claims

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Application Information

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IPC IPC(8): B64D29/04B64C1/14E05D5/02
CPCB64D29/04B64C1/14E05D5/02E05Y2900/502
Inventor 李振孟兆康雷黎明梁力
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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