Bracket linkage structure for split cabin door of cabin below fuselage

Abstract

The invention belongs to the technical field of aircraft structure design, and particularly relates to a bracket linkage structure for a split cabin door of a cabin below an aircraft fuselage, a bracket and the split cabin door are integrally designed, and the bracket linkage structure comprises the split cabin door, a hinge arm, a bracket, a connecting rod, a support arm and a support; the two groups of hinge arms are connected to the two cabin doors of the split cabin door and hinged to the cabin door frame; the bracket is arranged in a cabin below the fuselage; the two connecting rods are hinged to the support and one hinge arm connected with the two cabin doors. The two supporting arms are connected to the support and located on the two sides of the support. The two supports are connected to the two supporting arms and hinged to the interior of a cabin below the fuselage through pin shafts. When the split cabin door is opened outwards, the hinge arm drives the support to turn over outwards through the connecting rod and is lowered out of the cabin below the fuselage, so that people can conveniently enter the cabin below the fuselage; when the split cabin doors are closed inwards, the hinge arms drive the supports to turn inwards through the connecting rods and retract into the cabin below the fuselage.

Description

Technical Field

[0001] This application belongs to the field of aircraft structural design technology, specifically relating to a linkage structure for the support bracket of the split-opening cabin door under the fuselage of an aircraft. Background Technology

[0002] The cabin below the fuselage of an aircraft is usually equipped with outward-opening double doors. When it is necessary to enter the cabin below the fuselage, the double doors are opened outward. However, the area below the fuselage of large aircraft is usually high above the ground, and personnel need to use additional supports to enter the cabin below the fuselage, which is very inconvenient. Therefore, this application is made. Summary of the Invention

[0003] The purpose of this application is to provide a linkage structure for the support bracket of the aircraft's under-fuselage cabin doors, which allows personnel to enter the cabin below the fuselage when the doors are opened outwards, making it convenient and easy.

[0004] The technical solution of this application is: A linkage structure for a double-opening cabin door support under the fuselage of an aircraft includes: a double-opening cabin door, a hinge arm, a bracket, a connecting rod, a support arm, and a support. There are two sets of hinge arms, which are connected to the two hatches of the double hatch and hinged to the hatch frame. The support structure is located inside the fuselage below the fuselage. There are two connecting rods, which are hinged to the bracket and a hinge arm that connects the two hatches. There are two support arms, connected to the bracket and located on both sides of the bracket; There are two supports, which are connected to two support arms and hinged to the fuselage under the fuselage via pins; When the hatches open outwards, the hinged arm drives the bracket to flip outwards via a connecting rod and lower it to the outside of the cabin under the fuselage. When the hatches close inward, the hinged arm drives the support to flip inward via a linkage and retract into the cabin below the fuselage.

[0005] According to at least one embodiment of this application, in the above-described linkage structure of the aircraft fuselage under-fuselage cabin door support, each set of hinge arms has two arms.

[0006] According to at least one embodiment of this application, in the above-mentioned linkage structure of the aircraft fuselage under-fuselage cabin door support, the hinge arm is connected to the drive mechanism, and the drive mechanism can drive the two sets of hinge arms to rotate, thereby causing the cabin door to open outward and close inward.

[0007] According to at least one embodiment of this application, in the above-described linkage structure for the aircraft fuselage under-fuselage cabin door support, the drive mechanism includes two drive shafts and two drive motors, wherein... Two drive shafts are supported and connected to the door frame, as well as to two sets of hinge arms; Two drive motors are fixedly connected to the hatch frame and to two drive shafts, which can drive the two drive shafts to rotate, causing the two sets of hinge arms to swing, so that the double hatches open outward and close inward.

[0008] According to at least one embodiment of this application, in the above-described linkage structure of the aircraft fuselage under-fuselage cabin door support, the support is composed of multiple segments, and the segments can extend and retract relative to each other.

[0009] According to at least one embodiment of this application, in the above-described linkage structure of the aircraft fuselage under-fuselage cabin door support, the sections of the support are connected by slide rails.

[0010] According to at least one embodiment of this application, in the above-described linkage structure of the aircraft fuselage under-fuselage cabin door support, the sections of the support are extended and retracted by telescopic rods or lead screws.

[0011] According to at least one embodiment of this application, in the above-described linkage structure of the aircraft fuselage under-fuselage cabin door support, the connecting rod is a telescopic rod.

[0012] According to at least one embodiment of this application, in the above-described linkage structure of the aircraft fuselage under-fuselage cabin door support, two connecting rods are hinged to the middle of the rear end of the support and to the hinge arms behind the two doors. Two support arms are connected to the two sides of the rear end of the bracket.

[0013] According to at least one embodiment of this application, in the above-described linkage structure of the aircraft fuselage under-fuselage cabin door support, a roller is provided at the front end of the support.

[0014] This application has at least the following beneficial technical effects: A linkage structure for the support bracket of the aircraft's under-fuselage cabin is provided, wherein the support bracket is integrated with the under-fuselage cabin door. When the under-fuselage cabin door is opened outward, the hinge arm drives the support bracket to flip outward through the connecting rod and lower it to the outside of the cabin under the fuselage, thereby facilitating personnel to enter the cabin under the fuselage. When the under-fuselage cabin door is closed inward, the hinge arm drives the support bracket to flip inward through the connecting rod and retract it into the cabin under the fuselage. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the linkage structure of the aircraft fuselage under-fuselage cabin door support provided in the embodiments of this application; Figure 2 This is a schematic diagram of the linkage structure of the aircraft fuselage under-fuselage cabin door support when the cabin door is opened outward, provided in the embodiments of this application. Figure 3This is another schematic diagram of the linkage structure of the aircraft fuselage under-fuselage cabin door support when the cabin door is opened outward, as provided in the embodiments of this application; in: 1-Double-opening hatch; 2-Hinged arm; 3-Bracket; 4-Linkage; 5-Outrigger; 6-Support.

[0016] To better illustrate this embodiment, some content in the accompanying drawings may be omitted, enlarged, or reduced. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0017] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0018] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The word "comprising" as used in this application description indicates that the concept preceding the word encompasses the concepts listed following the word and their equivalents, without excluding other related concepts.

[0019] Furthermore, the terms indicating location used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0020] A linkage structure for the support brackets of the aircraft fuselage's double-opening cabin doors, such as... Figure 1 As shown, it includes a split hatch 1, a hinge arm 2, a bracket 3, a connecting rod 4, a support arm 5, and a support 6.

[0021] There are two sets of hinge arms 2, which are connected to the two doors of the double-leaf hatch 1 and hinged to the hatch frame. They are connected to the drive mechanism, which can drive the two sets of hinge arms 2 to rotate, causing the double-leaf hatch 1 to open outward and close inward.

[0022] There are two hinge arms in each group.

[0023] The drive mechanism includes two drive shafts and two drive motors. The two drive shafts are supported and connected to the hatch frame and connected to two sets of hinge arms 2. The two drive motors are fixedly connected to the hatch frame and connected to the two drive shafts, which can drive the two drive shafts to rotate, thereby causing the two sets of hinge arms 2 to swing, so that the double hatch 1 opens outward and closes inward.

[0024] The bracket 3 is installed in the cabin below the fuselage. The bracket 3 can be designed to consist of multiple sections, and each section can extend and retract relative to the others. Specifically, the sections can be connected by slide rails and extended and retracted by telescopic rods or lead screws.

[0025] There are two connecting rods 4, which are hinged to the bracket 3 and a hinge arm 2 that connects the two hatches. The connecting rods 4 can be designed as telescopic rods.

[0026] There are two support arms 5, which are connected to the bracket 3 and are located on both sides of the bracket 3.

[0027] There are two supports 6, which are connected to the two support arms 5 and are hinged to the fuselage below the cabin by pins.

[0028] Two connecting rods 4 can be designed to be hinged to the middle of the rear end of the bracket 3, and hinged to the hinge arms 2 behind the two hatches. Two support arms 5 can be designed to be connected to the two sides of the rear end of the bracket 3, and rollers can be set at the front end of the bracket 3.

[0029] When the double-door 1 opens outward, the hinge arm 2, through the connecting rod 4, drives the bracket 3 to flip outward and lower itself outside the cabin below the fuselage. Figures 2-3 As shown, this facilitates personnel access to the cabin below the fuselage. When the double-opening door 1 closes inward, the hinge arm 2 drives the bracket 3 to flip inward via the connecting rod 4 and retract into the cabin below the fuselage.

[0030] After the hatch 1 is opened outward, the support 3 can be extended between its sections to form a stable support by touching the ground. The support 3 is in contact with the ground through rollers, and the tilt angle of the support 3 can be adjusted by the extension and retraction of the connecting rod 4.

[0031] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this 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 scope of protection of this application.

Claims

1. A linkage structure for the support bracket of a double-opening cabin door under the fuselage of an aircraft, characterized in that, include: Double-opening hatch (1), hinge arm (2), bracket (3), connecting rod (4), support arm (5), support (6); The hinge arm (2) has two sets, which are connected to the two doors of the double hatch (1) and hinged to the door frame; The bracket (3) is installed in the cabin below the fuselage; There are two connecting rods (4), which are hinged to the bracket (3) and a hinge arm (2) connecting the two hatches; There are two support arms (5), which are connected to the bracket (3) and located on both sides of the bracket (3); There are two supports (6), which are connected to two support arms (5) and are hinged to the fuselage below the cabin by a pin. When the double-door (1) opens outward, the hinge arm (2) drives the bracket (3) to flip outward through the connecting rod (4) and lower it to the outside of the cabin below the fuselage; When the split hatch (1) closes inward, the hinge arm (2) drives the bracket (3) to flip inward through the connecting rod (4) and retract into the cabin below the fuselage.

2. The linkage structure for the aircraft fuselage under-fuselage cabin door support as described in claim 1, characterized in that, Each set of hinge arms (2) has two.

3. The linkage structure for the aircraft fuselage under-fuselage cabin door support as described in claim 2, characterized in that, The hinge arm (2) is connected to the drive mechanism, which can drive the two sets of hinge arms (2) to rotate, thereby causing the split hatch (1) to open outward and close inward.

4. The linkage structure for the aircraft fuselage under-fuselage cabin door support as described in claim 3, characterized in that, The drive mechanism includes two drive shafts and two drive motors, wherein, Two drive shafts are supported and connected to the door frame and to two sets of hinge arms (2); Two drive motors are fixedly connected to the hatch frame and to two drive shafts, which can drive the two drive shafts to rotate, causing the two sets of hinge arms (2) to swing, so that the double hatch (1) opens outward and closes inward.

5. The linkage structure for the aircraft fuselage under-fuselage cabin door support as described in claim 4, characterized in that, The support (3) is composed of multiple segments, which can stretch and contract relative to each other.

6. The linkage structure for the aircraft fuselage under-fuselage cabin door support as described in claim 5, characterized in that, The bracket (3) is connected to each other by slide rails.

7. The linkage structure for the aircraft fuselage under-fuselage cabin door support as described in claim 6, characterized in that, The bracket (3) is extended and retracted between its sections by means of telescopic rods or lead screws.

8. The linkage structure for the aircraft fuselage under-fuselage cabin door support according to claim 7, characterized in that, Link (4) is a telescopic rod.

9. The linkage structure for the aircraft fuselage under-fuselage split-door support as described in claim 8, characterized in that, Two connecting rods (4) are hinged to the middle of the rear end of the support (3) and to the hinge arms (2) behind the two hatches; Two arms (5) are connected to the two sides of the rear end of the bracket (3).

10. The linkage structure for the aircraft fuselage under-fuselage cabin door support according to claim 9, characterized in that, The bracket (3) has a roller at the front end.

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