CN218317272U

CN218317272U - Aircraft cabin door attach fitting

Info

Publication number: CN218317272U
Application number: CN202222688186.7U
Authority: CN
Inventors: 尹凯军; 杜鹏良; 陈卫锋
Original assignee: AVIC First Aircraft Institute
Current assignee: AVIC First Aircraft Institute
Priority date: 2022-10-12
Filing date: 2022-10-12
Publication date: 2023-01-17
Anticipated expiration: 2032-10-12

Abstract

The utility model belongs to aircraft structural design field, for an aircraft hatch door attach fitting, bottom plate including integrative setting, stand and auricle, when to the pressurization in the aircraft cabin, the pressure boost load passes through door frame and hatch door transmission to attach fitting's auricle and bottom plate department, then support the load of the transmission of auricle and bottom plate through the stand, and through setting up the auricle downward sloping, stand tilt up, make the middle part of auricle be in on roughly the same straight line with the bottom plate, when receiving the pressure boost load in the aircraft cabin, the transmission of both forces is more high-efficient, can reduce pressure differential between the two as far as possible, thereby effectively prevent that the hatch door from being pushed away. The bottom plate, the upright post and the lug are integrally machined, so that the cabin door mechanism is simple in structure, universal and high in interchangeability, and can effectively ensure the movement of the cabin door mechanism; meanwhile, the design requirements of short design period, low manufacturing cost, product serialization, generalization and high interchangeability degree are met.

Description

Aircraft cabin door attach fitting

Technical Field

The application belongs to the field of aircraft structural design, and particularly relates to an aircraft cabin door connecting joint.

Background

The airplane cabin door mechanism has direct influence on airplane safety, a cabin door in a passenger cabin is used as an emergency exit to directly influence the emergency evacuation time of passengers, the cabin door is used as the largest opening of a fuselage to directly influence structural integrity and safety, and meanwhile, the cabin door is a component directly operated by a unit and passengers, and the comfort, the advance and the reliability of the operation of the cabin door directly influence the judgment on the advance of the airplane. Historically, many flight accidents have been initiated by hatches.

The aircraft cabin door mechanism support structure is an important guarantee that the cabin door is not opened accidentally. When the pressure in the cabin is increased, the support structure bears the pressure increasing load of the cabin door, and the cabin door is prevented from being pushed away due to huge pressure difference. In order to better transmit the pressurization load in the cabin and meet the design requirements of short design period, low manufacturing cost, product serialization, universalization and high interchangeability to the greatest extent, a novel aircraft cabin door supporting structure needs to be designed.

Disclosure of Invention

The utility model aims at providing an aircraft hatch door attach fitting to solve among the prior art problem that the support structure is difficult to satisfy current design demand to the support of hatch door.

The technical scheme of the application is as follows: the utility model provides an aircraft hatch door attach fitting, includes integrative bottom plate, stand and the auricle that sets up, the stand slope is located on the bottom plate, the auricle is located the stand and is kept away from the one end of bottom plate, the earhole has been seted up on the auricle, the earhole passes through the bolt and links to each other with the fuselage, the bolt hole has been seted up on the bottom plate, the downthehole bolt of passing through of bolt is connected with hatch door inner skin, the auricle slope sets up and the auricle downward sloping, the stand tilt up.

Preferably, the angle between the upper surface of the lug and the upper surface of the upright post is 45 degrees.

Preferably, the tabs are partially scribed.

Preferably, the bottom plate is provided with a buffer section at a position corresponding to two sides of the upright post, and the thickness of the buffer section is gradually reduced from the upright post to the edge of the bottom plate.

Preferably, the bottom plate, the upright post and the lug are all made of titanium alloy materials.

The utility model provides an aircraft hatch door attach fitting, bottom plate including integrative setting, stand and auricle, when to the pressurization in the aircraft cabin, the pressure boost load passes through door frame and hatch door transmission to attach fitting's auricle and bottom plate department, then support the load of the transmission of auricle and bottom plate through the stand, and through setting up the auricle downward sloping, the stand tilt up, make the middle part of auricle and bottom plate be in on roughly the same straight line, when receiving the pressure boost load in the aircraft cabin, the transmission of both forces is more high-efficient, can reduce the pressure differential between the two as far as possible, thereby effectively prevent that the hatch door from being pushed away. The bottom plate, the upright post and the lug are integrally machined, so that the cabin door mechanism is simple in structure, universal and high in interchangeability, and can effectively ensure the movement of the cabin door mechanism; meanwhile, the design requirements of short design period, low manufacturing cost, product serialization, generalization and high interchangeability degree are met.

Drawings

In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.

FIG. 1 is an isometric view of the overall structure of the present application;

FIG. 2 is a side view of the overall structure of the present application;

fig. 3 is a schematic view of the connection structure of the connection joint and the inner skin of the cabin door.

1. A base plate; 2. a column; 3. a tab; 4. an ear hole; 5. a cabin door inner skin; 6. and a buffer section.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.

The utility model provides an aircraft hatch door attach fitting, as shown in fig. 1-3, bottom plate 1 including integrative setting, stand 2 and auricle 3, stand 2 slope is located on bottom plate 1, auricle 3 locates the one end that bottom plate 1 was kept away from to stand 2, stand 2 reduces from auricle 3 to bottom plate 1 one side width gradually, auricle 3 is last to have seted up ear hole 4, ear hole 4 links to each other with the fuselage through the bolt, a plurality of bolt holes have been seted up on bottom plate 1, the both sides of bottom plate 1 are located to a plurality of bolt hole symmetries, the downthehole bolt is connected with hatch door inner skin 5 through the bolt, auricle 3 slope sets up and auricle 3 downward sloping, stand 2 tilt up.

When the pressurization to aircraft cabin in, pressurization load passes through door frame and hatch door and transmits lug 3 and bottom plate 1 department to attach fitting, then support the load of the transmission of lug 3 and bottom plate 1 through stand 2, and through setting up lug 3 downward sloping, stand 2 tilt up, make the middle part of lug 3 be in on the roughly the same straight line with bottom plate 1, when receiving the pressurization load in the aircraft cabin, the transmission of both forces is more high-efficient, can reduce the pressure differential between the two as far as, thereby effectively prevent that the hatch door from being pushed away. The bottom plate 1, the upright post 2 and the lug piece 3 are integrally machined, so that the structure is simple, the universality is high, the interchangeability degree is high, and the movement of the cabin door mechanism can be effectively ensured; meanwhile, the design requirements of short design period, low manufacturing cost, product serialization, generalization and high interchangeability degree are met.

Preferably, the angle between the upper surface of the tab 3 and the upper surface of the post 2 is 45 °, which provides a more stable force transfer.

Preferably, in order to reduce the weight of the connection joint, the tabs 3 are partially scored while ensuring the structural strength.

Preferably, the bottom plate 1 is provided with the buffer section 6 at the position corresponding to the two sides of the upright post 2, the thickness of the buffer section 6 is gradually reduced from the upright post 2 to the edge of the bottom plate 1, and the buffer section 6 enables the load at the position between the bottom plate 1 and the upright post 2 to be slowly changed rather than suddenly changed when the load is transmitted between the two, so that cracks are prevented from occurring, and the service life is prolonged.

Preferably, the bottom plate 1, the upright post 2 and the lug 3 are made of titanium alloy materials, and the titanium alloy materials are high in strength, good in corrosion resistance and more stable in bearing performance compared with other materials.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. An aircraft door attach fitting, characterized by: including bottom plate (1), stand (2) and auricle (3) of integrative setting, stand (2) slope is located on bottom plate (1), the one end of bottom plate (1) is kept away from in stand (2) is located auricle (3), earhole (4) have been seted up on auricle (3), earhole (4) link to each other with the fuselage through the bolt, the bolt hole has been seted up on bottom plate (1), be connected through bolt and hatch door inner skin (5) in the bolt hole, auricle (3) slope sets up and auricle (3) downward sloping, stand (2) tilt up.

2. The aircraft door attachment joint of claim 1, wherein: the included angle between the upper surface of the lug (3) and the upper surface of the upright post (2) is 45 degrees.

3. The aircraft door attachment joint of claim 1, wherein: and the lug (3) is partially scribed and milled.

4. The aircraft door attachment joint of claim 1, wherein: the bottom plate (1) is equipped with buffer segment (6) corresponding to the position department on stand (2) both sides, the edge of the thickness of buffer segment (6) from stand (2) to bottom plate (1) reduces gradually.

5. The aircraft door interface joint of claim 1, wherein: the bottom plate (1), the upright post (2) and the lug (3) are all made of titanium alloy materials.