Airplane blocking type cabin door and force bearing beam thereof

Abstract

The utility model belongs to the technical field of structural design of aircraft blocking type cabin doors, and particularly relates to an aircraft blocking type cabin door and a force bearing beam of the aircraft blocking type cabin door. The two edge strips are integrally formed on the edges of the two sides of the web plate; each pair of reinforcing ribs is integrally formed on the side walls of the two sides of the web plate, and the two ends of each pair of reinforcing ribs are connected to the inner sides of the two edge strips; the two end plates are integrally formed at the two ends of the web plate, and the side wall of each end plate is connected to the ends of the two edge strips; each pair of angle plates is integrally formed on the side walls of the two sides of the web plate and connected to the inner side of the side wall of one end plate; and the two stop joints are connected to the outer sides of the side walls of the two end plates.

Description

Technical Field

[0001] This application belongs to the technical field of the structural design of aircraft plug-type hatches, and particularly relates to an aircraft plug-type hatch and its load-bearing beam. Background Art

[0002] The aircraft plug-type hatch uses a load-bearing beam arranged in the heading direction as the main load-bearing structure. Currently, the load-bearing beam mostly adopts a structure composed of profiles and webs. The combined assembly requires a large number of fasteners and special tooling, resulting in poor economy and easy to generate large assembly errors. Moreover, when assembling on the hatch, the docking with the support ribs requires special positioning tooling, and the process is cumbersome.

[0003] In view of the existence of the above technical defects, this application is proposed. Utility Model Content

[0004] The purpose of this application is to provide an aircraft plug-type hatch and its load-bearing beam to overcome or mitigate at least one aspect of the known technical defects.

[0005] The technical solution of this application is as follows:

[0006] On the one hand, a load-bearing beam for an aircraft plug-type hatch is provided, including:

[0007] Web;

[0008] Two flanges, integrally formed on both side edges of the web;

[0009] Multiple pairs of stiffeners, each pair of stiffeners integrally formed on both side walls of the web and connected to the two flanges at both ends;

[0010] Two end plates, integrally formed at both ends of the web, and the inner side wall of each end plate is connected to the ends of the two flanges;

[0011] Two gusset plates, each pair of gusset plates integrally formed on both side walls of the web and connected to the inner side wall of one end plate;

[0012] Two stop joints, connected to the outer side walls of the two end plates.

[0013] According to at least one embodiment of this application, in the above load-bearing beam of the aircraft plug-type hatch, it further includes:

[0014] Two stop screws, threadedly connected to the two stop joints.

[0015] According to at least one embodiment of this application, in the above load-bearing beam of the aircraft plug-type hatch, the web, its flanges, stiffeners, end plates, and gusset plates are made of aluminum alloy material.

[0016] According to at least one embodiment of the present application, in the above-mentioned aircraft plug-type hatch door load-bearing beam, the web, its flanges, stiffeners, end plates, and gusset plates are integrally machined.

[0017] On the other hand, an aircraft plug-type hatch door is provided, including:

[0018] Skin;

[0019] Multiple pairs of support ribs, connected to the inner side of the skin;

[0020] Any one of the above-mentioned aircraft plug-type hatch door load-bearing beams, wherein,

[0021] One flange is connected to the inner side of the skin;

[0022] The ends of each pair of stiffeners are connected to the ends of each pair of support ribs.

[0023] The present application has at least the following beneficial technical effects:

[0024] A load-bearing beam for an aircraft plug-type hatch door is provided, in which the main load-bearing structure, such as the web, flanges, and stiffeners, is integrally formed, without the need for a large number of fasteners and special tooling for assembly. Moreover, when assembling on the hatch door, the stiffeners can be used as the positioning reference for the support ribs, without the need for special tooling for positioning. In addition, when the hatch door is closed, two stop joints can be abutted against the hatch door frame, specifically against the stop bosses provided on the hatch door frame, to prevent the hatch door from excessive sinking and to participate in the load transfer between the hatch door and the hatch door frame, giving full play to the load-bearing role. Description of the Drawings

[0025] Figure 1 is a schematic diagram of the load-bearing beam of the aircraft plug-type hatch door provided by the embodiment of the present application;

[0026] Figure 2 is a schematic diagram of the aircraft plug-type hatch door provided by the embodiment of the present application;

[0027] Wherein:

[0028] 1 - web; 2 - flange; 3 - stiffener; 4 - end plate; 5 - gusset plate; 6 - stop joint; 7 - stop screw; 8 - skin; 9 - support rib.

[0029] For better illustration of this embodiment, some components in the drawings are omitted, enlarged or reduced, which do not represent the dimensions of the actual product. In addition, the drawings are only for illustrative purposes and cannot be construed as a limitation to the present application. Detailed Embodiments

[0030] To make the technical solutions and their advantages of this application clearer, the following will further describe the technical solutions of this application clearly and completely in conjunction with the accompanying drawings. It can be understood that the specific embodiments described herein are only partial embodiments of this application, which are only used to explain this application rather than limit this application. It should be noted that for the convenience of description, only the parts related to this application are shown in the drawings, and other related parts can refer to the general design.

[0031] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The terms indicating directions used in the description of this application are only used to represent relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. The "including" used in the description of this application means that the elements or objects appearing before this word cover the elements or objects listed after this word and their equivalents, without excluding other elements or objects.

[0032] In addition, it should also be noted that unless otherwise clearly specified and limited, the similar terms such as "installation" and "connection" used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. Those skilled in the art can understand their specific meanings in this application according to the specific situation.

[0033] On the one hand, a plug-type cabin door load-bearing beam for an aircraft is provided, including:

[0034] A web 1;

[0035] Two flanges 2, integrally formed on both side edges of the web 1;

[0036] Multiple pairs of stiffeners 3, each pair of stiffeners 3 integrally formed on both side walls of the web 1, with both ends connected to the two flanges 2 to improve the stability of the web 1 and improve the processing performance of the web 1;

[0037] Two end plates 4, integrally formed at both ends of the web 1, and the inner side wall of each end plate 4 is connected to the ends of the two flanges 2;

[0038] Two diagonal plates 5, each pair of diagonal plates 5 integrally formed on both side walls of the web 1 and connected to the inner side wall of one end plate 4 to support the end plate 4;

[0039] Two stop joints 6, connected to the outer side walls of the two end plates 4.

[0040] For the plug-type cabin door load-bearing beam of an aircraft disclosed in the above embodiments, the main body web 1, flange 2, stiffener 3, etc. of its load-bearing structure are integrally formed, without the need for a large number of fasteners and special tooling for assembly. When assembling on the cabin door, the stiffener 3 can be used as the positioning reference for the support rib 9, without the need for special tooling for positioning. In addition, when the cabin door is closed, two stop joints 6 can be abutted against the cabin door frame, specifically against the stop protrusions provided on the cabin door frame, to prevent the cabin door from moving outwards excessively and to participate in the load transfer between the cabin door and the cabin door frame, giving full play to the load-bearing function.

[0041] In some alternative embodiments, in the above plug-type cabin door load-bearing beam of an aircraft, it further includes:

[0042] Two stop screws 7, threadedly connected to the two stop joints 6. When the cabin door is closed, the two stop screws 7 can be abutted against the cabin door frame to prevent the cabin door from moving outwards excessively, and enable the plug-type cabin door load-bearing beam of the aircraft to participate in the load transfer between the cabin door and the cabin door frame, giving full play to the load-bearing function. In addition, the length of the two stop screws 7 protruding from the stop joints 6 can be adjusted by screwing, so as to meet the actual requirements.

[0043] In some alternative embodiments, in the above plug-type cabin door load-bearing beam of an aircraft, the web 1, its flange 2, stiffener 3, end plate 4, and gusset plate 5 are made of aluminum alloy material.

[0044] In some alternative embodiments, in the above plug-type cabin door load-bearing beam of an aircraft, the web 1, its flange 2, stiffener 3, end plate 4, and gusset plate 5 are integrally machined, and can have relatively high machining accuracy.

[0045] On the other hand, a plug-type cabin door of an aircraft is provided, including:

[0046] Skin 8;

[0047] Multiple pairs of support ribs 9, connected to the inner side of the skin 8;

[0048] Any one of the above plug-type cabin door load-bearing beams of an aircraft, wherein,

[0049] One flange 2 is connected to the inner side of the skin 8;

[0050] The ends of each pair of stiffeners 3 are connected to the ends of each pair of support ribs 9.

[0051] The main improvement of the plug-type cabin door of an aircraft disclosed in the above embodiments lies in that the description of the plug-type cabin door load-bearing beam of an aircraft disclosed in the above embodiments is relatively simple. For specific relevant parts, reference can be made to the relevant descriptions in the parts disclosed in the above embodiments, and the technical effects can also be referred to the relevant technical effects in the relevant parts disclosed in the above embodiments, which will not be elaborated here.

[0052] The various embodiments in the specification are described in a progressive manner. Each embodiment focuses on the differences from other embodiments. For the same or similar parts among the various embodiments, reference can be made to each other. Without conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0053] So far, the technical solutions of the present application have been described in conjunction with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present application.

Claims

1. An aircraft plug-type cabin door load-bearing beam, characterized in that, Comprising: Web (1); Two flanges (2), integrally formed on both side edges of the web (1); Multiple pairs of stiffeners (3), each pair of stiffeners (3) integrally formed on both side walls of the web (1), with both ends connected to the two flanges (2); Two end plates (4), integrally formed at both ends of the web (1), and the inner side wall of each end plate (4) is connected to the ends of the two flanges (2); Two gusset plates (5), each pair of gusset plates (5) integrally formed on both side walls of the web (1), and connected to the inner side wall of one end plate (4); Two stop joints (6), connected to the outer side walls of the two end plates (4).

2. The aircraft plug-type cabin door load-bearing beam according to claim 1, wherein, Further comprising: Two stop screws (7), threadedly connected to the two stop joints (6).

3. The load-bearing beam of the aircraft plug-type cabin door according to claim 1, wherein The web (1) and its flanges (2), stiffeners (3), end plates (4), and gusset plates (5) are made of aluminum alloy material.

4. The load-bearing beam of the aircraft plug-type cabin door according to claim 1, wherein The web (1) and its flanges (2), stiffeners (3), end plates (4), and gusset plates (5) are integrally machined.

5. A plug-type aircraft door, characterized in that, Comprising: Skin (8); Multiple pairs of support ribs (9), connected to the inner side of the skin (8); The load-bearing beam of the aircraft plug-type cabin door according to claim 1, wherein One flange (2) is connected to the inner side of the skin (8); The ends of each pair of stiffeners (3) are connected to the ends of each pair of support ribs (9).

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