Non-blocking cabin door of airplane

Abstract

The utility model belongs to the technical field of airplane non-blocking type cabin door structural design, and particularly relates to an airplane non-blocking type cabin door. The roof side rail is connected to the inner side of the skin and located at the top of the skin; the lower edge beam is connected to the inner side of the skin and located at the bottom of the skin; a web; the two edge strips are integrally formed on the edges of the two sides of the web, and one edge strip is connected to the inner side of the skin; 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 upper end plate is integrally formed and connected to the upper end of the web, the inner side of the side wall is connected to the ends of the two edge strips, and the outer side of the side wall is connected to the inner side of the side wall of the roof side rail; the lower end plate is integrally formed and connected to the lower end of the web, and the inner side of the side wall is connected to the ends of the two edge strips; and the cabin door mechanism mounting seat is integrally formed on the outer side of the side wall of the lower end plate and is provided with two opposite side walls, and the two side walls are provided with a plurality of supporting holes and are connected to the inner side of the side wall of the lower edge beam.

Description

Technical Field

[0001] This application belongs to the technical field of the design of non-blocking aircraft cabin doors, and particularly relates to a non-blocking aircraft cabin door. Background Art

[0002] The non-blocking aircraft cabin door uses a circumferentially arranged load-bearing frame as the main load-bearing structure. Currently, the load-bearing frame mostly adopts a combined structure of profiles and webs. The combined assembly requires a large number of fasteners and special tooling, resulting in poor economy, and is prone to large assembly errors. When installing on the cabin door, it is necessary to use special tooling to position with the reinforcing beam, and the process is cumbersome. In addition, a cabin door mechanism mounting seat is separately provided on the non-blocking aircraft cabin door, which is mainly used to support the rotating shaft of the cabin door mechanism. Installing it separately on the cabin door is time-consuming and laborious.

[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 a non-blocking aircraft cabin door to overcome or mitigate at least one aspect of the known technical defects.

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

[0006] A non-blocking aircraft cabin door, comprising:

[0007] Skin;

[0008] Upper side beam, connected to the inner side of the skin and located at the top of the skin;

[0009] Lower side beam, connected to the inner side of the skin and located at the bottom of the skin;

[0010] Web;

[0011] Two flanges, integrally formed on both side edges of the web. One of the flanges is connected to the inner side of the skin;

[0012] Multiple pairs of reinforcing ribs, each pair of reinforcing ribs integrally formed on both side walls of the web and connected to the inner sides of the two flanges at both ends;

[0013] Upper end plate, integrally formed and connected to the upper end of the web. The inner side of the side wall is connected to the ends of the two flanges, and the outer side of the side wall is connected to the inner side of the side wall of the upper side beam;

[0014] Lower end plate, integrally formed and connected to the lower end of the web. The inner side of the side wall is connected to the ends of the two flanges;

[0015] Cabin door mechanism mounting seat, integrally formed on the outer side of the side wall of the lower end plate, having two opposite side walls with multiple support holes on the two side walls, and connected to the inner side of the side wall of the lower side beam.

[0016] According to at least one embodiment of the present application, in the above non-blocking aircraft door, the two side edges of the upper side beam are bent inwards to form notches;

[0017] On both sides of the upper end of the web and its flange, there are stepped structures that are stuck in the notches;

[0018] On the two side walls of the door mechanism mounting seat, there are inclined surfaces and stepped structures adjacent to the inclined surfaces;

[0019] The side wall of the lower side beam is bent and abutted against the two inclined surfaces on the door mechanism mounting seat, and is stuck to the two stepped structures on the door mechanism mounting seat.

[0020] According to at least one embodiment of the present application, in the above non-blocking aircraft door, it further includes:

[0021] Two support gussets, which are connected between the inner side of the skin and the outer side of the side wall of the lower side beam.

[0022] According to at least one embodiment of the present application, in the above non-blocking aircraft door, it further includes:

[0023] Multiple pairs of reinforcing beams, which are connected to the inner side of the skin, and one end of each pair is connected to each pair of reinforcing ribs.

[0024] According to at least one embodiment of the present application, in the above non-blocking aircraft door, the web and its flange, reinforcing ribs, upper end plate, lower end plate, and door mechanism mounting seat are integrally machined from aluminum alloy materials.

[0025] The present application has at least the following beneficial technical effects:

[0026] A non-blocking aircraft door is provided, in which the load-bearing frame composed of the main web, flange, reinforcing ribs, upper end plate, lower end plate, etc. is integrally formed, without the need for a large number of fasteners and special tooling for assembly, and the door mechanism mounting seat is integrally formed on the lower end plate, which can be conveniently installed on the skin and the door mechanism can be assembled. In addition, the upper end plate and the door mechanism mounting seat are designed to be connected to the upper side beam and the lower side beam arranged on the inner side of the skin, and the overall structure is firmly connected. The load-bearing frame can efficiently bear the load and participate in the circumferential load transfer of the fuselage, giving full play to the load-bearing role. Description of the Drawings

[0027] Figure 1 is a schematic diagram of the non-blocking aircraft door provided by the embodiment of the present application;

[0028] Figure 2 is a schematic diagram of the integration of the load-bearing frame and the door mechanism mounting seat provided by the embodiment of the present application;

[0029] Among them:

[0030] 1 - Skin; 2 - Upper side beam; 3 - Lower side beam; 4 - Web; 5 - Flange; 6 - Reinforcing rib; 7 - Upper end plate; 8 - Lower end plate; 9 - Installation seat for hatch mechanism; 10 - Support gusset plate; 11 - Reinforcing beam.

[0031] 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 should not be construed as a limitation to this application. Detailed implementation manners

[0032] To make the technical solutions and their advantages of this application clearer, the technical solutions of this application will be further described clearly and completely below with reference to the 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 and not to 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.

[0033] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the ordinary meanings understood by those of ordinary skill in the field to which this application belongs. The terms indicating directions used in the description of this application are only used to indicate 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.

[0034] In addition, it should be noted that, unless otherwise clearly specified and limited, the 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.

[0035] An aircraft non-blocking hatch, as Figure 1 shown, includes:

[0036] Skin 1;

[0037] Upper side beam 2, connected to the inner side of the skin 1 and located at the top of the skin 1;

[0038] Lower side beam 3, connected to the inner side of the skin 1 and located at the bottom of the skin 1;

[0039] Web 4;

[0040] Two flange strips 5 are integrally formed on both side edges of the web 4. Among them, one flange strip 5 is connected to the inner side of the skin 1;

[0041] Multiple pairs of stiffeners 6 are integrally formed on the side walls on both sides of the web 4, and both ends are connected to the inner sides of the two flange strips 5 to improve the stability of the web 4 and improve the processing performance of the web 4;

[0042] The upper end plate 7 is integrally formed at the upper end of the web 4 connected. The inner side of the side wall is connected to the ends of the two flange strips 5, and the outer side of the side wall is connected to the inner side of the side wall of the upper side beam 2;

[0043] The lower end plate 8 is integrally formed at the lower end of the web 4 connected. The inner side of the side wall is connected to the ends of the two flange strips 5;

[0044] The hatch mechanism mounting seat 9 is integrally formed on the outer side of the side wall of the lower end plate 8 and has two opposite side walls. There are multiple support holes on the two side walls and it is connected to the inner side of the side wall of the lower side beam 3. Among them, the position and quantity of the support holes can be specifically designed according to the support requirements of the hatch mechanism rotating shaft.

[0045] For the non-blocking hatch of the aircraft disclosed in the above embodiments, the load-bearing frame designed to be composed of the main web 4, flange strips 5, stiffeners 6, upper end plate 7, lower end plate 8, etc. is integrally formed, and does not require a large number of fasteners and special tooling for assembly. And the hatch mechanism mounting seat 9 is integrally formed on the lower end plate 8, which can facilitate the installation and assembly of the hatch mechanism on the skin. In addition, the upper end plate 7 and the hatch mechanism mounting seat 9 are designed to be connected to the upper side beam 2 and the lower side beam 3 arranged on the inner side of the skin 1. The overall structure is firmly connected, the load-bearing frame can carry efficiently, and participates in the circumferential load transfer of the fuselage, giving full play to the load-bearing role.

[0046] In some alternative embodiments, in the above non-blocking hatch of the aircraft, the two side edges of the upper side beam 2 are bent inwards to form a notch;

[0047] The two side edges of the upper end of the web 4 and its flange strips 5 have a stepped structure and are stuck in the notch;

[0048] The two side walls of the hatch mechanism mounting seat 9 have inclined surfaces and stepped structures adjacent to the inclined surfaces;

[0049] The side wall of the lower side beam 3 is bent and abuts against the two inclined surfaces on the hatch mechanism mounting seat 9, and is stuck to the two stepped structures on the hatch mechanism mounting seat 9, so that the connection and cooperation between the overall structures are tight.

[0050] In some alternative embodiments, in the above non-blocking hatch of the aircraft, it further includes:

[0051] Two support gussets 10 are connected between the inner side of the skin 1 and the outer side of the side beam 3 to support the side beam 3.

[0052] In some alternative embodiments, the non-blocking aircraft door described above further includes:

[0053] Multiple pairs of reinforcing beams 11 are connected to the inner side of the skin 1, and one end of each pair is connected to each pair of reinforcing ribs 6 to enable efficient load bearing. When installed on the door, the reinforcing ribs 6 can be used as the positioning reference for the reinforcing beams 11, and no special tooling is required for positioning.

[0054] In some alternative embodiments, in the non-blocking aircraft door described above, the web 4, its flange 5, the reinforcing ribs 6, the upper end plate 7, the lower end plate 8, and the door mechanism mounting seat 9 are integrally machined from aluminum alloy material, which can have relatively high machining accuracy.

[0055] 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 and the technical features in the embodiments in the present application can be combined with each other to obtain new embodiments.

[0056] So far, the technical solution of the present application has 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 all fall within the protection scope of the present application.

Claims

1. An aircraft non-blocking hatch, characterized in that, Comprising: Skin (1); Upper side beam (2), connected to the inner side of the skin (1) and located at the top of the skin (1); Lower side beam (3), connected to the inner side of the skin (1) and located at the bottom of the skin (1); Web (4); Two flange strips (5), integrally formed on both side edges of the web (4). Among them, one flange strip (5) is connected to the inner side of the skin (1); Multiple pairs of stiffening ribs (6), each pair of stiffening ribs (6) integrally formed on both side walls of the web (4) and connected to the inner sides of the two flange strips (5) at both ends; Upper end plate (7), integrally formed and connected to the upper end of the web (4). The inner side of the side wall is connected to the ends of the two flange strips (5), and the outer side of the side wall is connected to the inner side of the side wall of the upper side beam (2); Lower end plate (8), integrally formed and connected to the lower end of the web (4). The inner side of the side wall is connected to the ends of the two flange strips (5); Hatch mechanism mounting seat (9), integrally formed on the outer side of the side wall of the lower end plate (8), having two opposite side walls with multiple support holes on the two side walls and connected to the inner side of the side wall of the lower side beam (3).

2. The non-blocking hatch of an aircraft according to claim 1, wherein: The two side edges of the upper side beam (2) are bent inwards to form notches; Step structures are provided on both side edges at the upper end of the web (4) and its flange strips (5) and are stuck in the notches; The two side walls of the hatch mechanism mounting seat (9) have inclined surfaces and step structures adjacent to the inclined surfaces; The side wall of the lower side beam (3) is bent and abuts against the two inclined surfaces on the hatch mechanism mounting seat (9) and is stuck to the two sets of step structures on the hatch mechanism mounting seat (9).

3. The non-blocking aircraft hatch according to claim 1, characterized in that Further comprising: Two support gussets (10), connected between the inner side of the skin (1) and the outer side of the side wall of the lower side beam (3).

4. The non-blocking aircraft hatch according to claim 1, wherein, Further comprising: Multiple pairs of strengthening beams (11), connected to the inner side of the skin (1), and one end of each pair of strengthening beams is connected to each pair of stiffening ribs (6).

5. The non-blocking aircraft hatch according to claim 1, characterized in that, The web (4) and its flange strips (5), stiffening ribs (6), upper end plate (7), lower end plate (8), and hatch mechanism mounting seat (9) are integrally machined from aluminum alloy material.

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