Landing gear cabin sealing structure

Abstract

The utility model belongs to the technical field of aviation, and particularly relates to an undercarriage cabin sealing structure which is located behind a central wing and below a cabin and used for containing an undercarriage. The undercarriage cabin sealing structure is used for sealing a cabin and an undercarriage cabin, the undercarriage cabin sealing structure comprises a combined longitudinal beam forming a cabin floor and the top of the undercarriage cabin, and the combined longitudinal beam comprises an upper edge plate, a lower edge plate and a web plate; the undercarriage cabin airtight top plate is fixedly connected with the lower edge plate of the combined longitudinal beam through a bolt; the transverse sheet metal part is bent to form two mounting surfaces with an included angle, and the two mounting surfaces are fixedly mounted on the undercarriage cabin airtight top plate and the central wing upper wall plate respectively; and the transverse machining part is provided with a horizontal mounting surface and a vertical mounting surface which are fixedly mounted on the airtight top plate of the undercarriage cabin and the combined reinforcing frame at the rear end of the undercarriage cabin respectively. An upper edge plate of the combined longitudinal beam is provided with an installation notch, and the installation notch is in butt joint with a transverse piece perpendicular to the combined longitudinal beam.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of aviation technology, and particularly relates to a landing gear cabin sealing structure. BACKGROUND

[0002] The structure that the wing, the fuselage and the landing gear are connected is common in civil aircraft or lower single-wing aircraft. The main landing gear is connected to the fuselage, the landing gear cabin is located at the rear of the central wing, the air-tight line is complex, the upper surface of the central wing, the wing front beam frame, the landing gear cabin top plate and the landing gear cabin rear end frame are the air-tight line, especially the landing gear cabin top plate is subjected to the air-tight load and the inconsistent deformation of the central wing, the stress is complex, and fatigue cracks and air leakage are easily generated. How to reduce the cracks of the landing gear cabin top plate, the arrangement of the air-tight plate has certain particularity, the air-tight plate is flexibly connected with the wing, the deformation is coordinated, and the light weight structure satisfies the transmission of the air-tight load. SUMMARY

[0003] In order to solve the above problems, the application provides a landing gear cabin sealing structure, the landing gear cabin is located at the rear of the central wing and below the cabin and is used for accommodating the landing gear; the landing gear cabin sealing structure is used for sealing the cabin and the landing gear cabin, and the landing gear cabin sealing structure comprises:

[0004] A combined longitudinal beam forming the cabin floor and the landing gear cabin top part, the combined longitudinal beam comprising an upper edge plate, a lower edge plate and a web plate;

[0005] An air-tight top plate of the landing gear cabin, which is fixedly connected with the lower edge plate of the combined longitudinal beam through bolts;

[0006] A transverse sheet metal part, which has two installation surfaces with an included angle and is fixedly installed on the air-tight top plate of the landing gear cabin and the upper wall plate of the central wing respectively;

[0007] A transverse machined part, which has two installation surfaces of horizontal and vertical and is fixedly installed on the air-tight top plate of the landing gear cabin and the combined reinforcing frame at the rear end of the landing gear cabin respectively.

[0008] Preferably, the upper edge plate of the combined longitudinal beam has an installation notch, and the installation notch is connected and installed perpendicularly to the transverse part of the combined longitudinal beam.

[0009] Preferably, a plurality of transverse reinforcing parts are arranged longitudinally on the air-tight top plate of the landing gear cabin.

[0010] Preferably, the fastener is connected together through the transverse reinforcing part, the air-tight top plate of the landing gear cabin and the combined longitudinal beam.

[0011] Preferably, the transverse sheet metal part is made of titanium alloy parts and is used for bearing the inconsistent deformation between the upper wall plate of the central wing and the air-tight top plate of the landing gear cabin.

[0012] The advantages of this application include: when the sealed top plate is subjected to airtight load, the deformation of the sheet metal parts connecting the central wing rear beam is coordinated and consistent, avoiding tearing. It can both ensure airtight sealing and coordinate with the deformation of the wing. Attached Figure Description

[0013] Figure 1 This is a diagram showing the positional relationship of the landing gear bays according to a preferred embodiment of this application.

[0014] Figure 2 yes Figure 1 Partial schematic diagram at point A. Detailed Implementation

[0015] 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. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0016] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral 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; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0017] like Figure 1 As shown, a landing gear bay sealing structure is provided. The landing gear bay is located behind the center wing 9 and below the fuselage, and is used to accommodate the landing gear. The landing gear bay sealing structure is used to seal the fuselage and the landing gear bay. The landing gear bay sealing structure includes:

[0018] A combined longitudinal beam 1 forms the cabin floor and the top of the landing gear bay. The combined longitudinal beam 1 includes an upper edge plate, a lower edge plate, and a web plate.

[0019] The airtight top plate 4 of the landing gear bay is fixedly connected to the lower edge plate of the combined longitudinal beam 1 by bolts;

[0020] The transverse sheet metal part 6 is formed by bending the sheet metal to create two mounting surfaces with an angle, which are respectively fixedly installed on the airtight top plate 4 of the landing gear bay and the upper wall plate 12 of the central wing.

[0021] The transverse metal part 3 has two installation surfaces, horizontal and vertical, which are fixed on the airtight top plate 4 of the landing gear cabin and the combined reinforcing frame 2 at the rear end of the landing gear cabin, respectively.

[0022] Preferably, the upper edge plate of the combined longitudinal beam 1 has an installation notch, which is used to install the transverse part 11 perpendicular to the combined longitudinal beam 1, forming a longitudinal-transverse part, and the honeycomb floor is connected to the longitudinal-transverse part framework. The longitudinal-transverse part can bear the airtight load, and the sealant is used to seal the gap and riveting and screwing positions to prevent air leakage.

[0023] Preferably, a plurality of transverse reinforcing parts 5 are arranged longitudinally on the airtight top plate 4 of the landing gear cabin.

[0024] Preferably, the fastener is connected through the transverse reinforcing part 5, the airtight top plate 4 of the landing gear cabin and the combined longitudinal beam 1.

[0025] Preferably, the transverse metal part 6 is made of titanium alloy, which is used to bear the inconsistent deformation between the upper wall plate 12 of the central wing and the airtight top plate 4 of the landing gear cabin.

[0026] The advantages of the present application include that the airtight top plate deforms in coordination with the connecting metal part of the central wing rear beam when bearing the airtight load, avoiding tearing, so that it can ensure sealing without air leakage and coordinate with the deformation of the wing.

[0027] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited to this. Any changes or replacements that can be easily thought of by those skilled in the art within the technical scope disclosed in the present application should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A landing gear bay seal structure, characterized by, The landing gear cabin is located at the rear of the central wing (9) and below the cabin for accommodating the landing gear; The landing gear cabin sealing structure is used for sealing the cabin and the landing gear cabin, and comprises: A combined stringer (1) forming the cabin floor and the landing gear cabin roof, the combined stringer (1) comprising an upper edge plate, a lower edge plate and a web plate; A landing gear cabin air-tight roof (4) fixedly connected with the lower edge plate of the combined stringer (1) through bolts; A transverse sheet metal part (6) having two installation surfaces with an included angle formed by sheet bending and fixedly installed on the landing gear cabin air-tight roof (4) and the central wing upper wall plate (12) respectively; A transverse machined part (3) having horizontal and vertical installation surfaces and fixedly installed on the landing gear cabin air-tight roof (4) and the combined reinforcement frame (2) located at the rear end of the landing gear cabin respectively.

2. The landing gear bay seal structure of claim 1, wherein The upper edge plate of the combined stringer (1) has an installation notch, and the installation notch is butted to install the transverse part (11) perpendicular to the combined stringer (1).

3. The landing gear bay seal structure of Claim 1, wherein A plurality of transverse reinforcement parts (5) are longitudinally arranged on the landing gear cabin air-tight roof (4).

4. The landing gear bay seal structure of Claim 1, wherein Fasteners are connected through the transverse reinforcement part (5), the landing gear cabin air-tight roof (4) and the combined stringer (1).

5. The landing gear bay seal structure of claim 1, wherein The transverse sheet metal part (6) is made of titanium alloy and is used for bearing the inconsistent deformation between the central wing upper wall plate (12) and the landing gear cabin air-tight roof (4).

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