Large-bearing-capacity butt flange structure

Abstract

The utility model belongs to the technical field of aviation connecting structures, and discloses a large-bearing butt flange structure which comprises a front connecting ring, a rear connecting ring and an inclined web. The front connecting ring is an annular piece with an interface connected with annular equipment, the rear connecting ring is of an annular structure connected with a front airtight end frame of the airplane, and the area, the inner diameter and the outer diameter of the rear connecting ring are larger than those of the front connecting ring; the front connecting ring and the rear connecting ring are connected through an inclined web plate in an inclined cone ring shape, and a reinforcing rib structure is arranged on the inclined web plate. The utility model provides a bearable connecting structure of a photoelectric turret additionally arranged in front of an airtight end frame of an airplane nose, and by adopting the structure, the installation of a long cantilever, heavy weight and an annular connecting interface on the nose can be solved, and meanwhile, the load transmission of large-scale equipment installed on the airplane can be solved.

Description

Technical Field

[0001] The utility model belongs to the technical field of aviation connection structures, and relates to a structure for installing a photoelectric switching tower on an aircraft, in particular to a large-load-bearing butt joint flange structure. Background Art

[0002] In order to meet the requirements of installing equipment on the nose of the aircraft, an equipment mounting bracket structure will be set on the airtight end frame of the nose of the aircraft. The mounting bracket structure is used as a transition between the equipment installation and the airtight end frame, and is usually composed of longitudinal and transverse reinforcement members. However, for the optoelectronic turret structure with a long cantilever, large load, and an annular connection surface, the traditional mounting bracket cannot meet the requirements.

[0003] The optoelectronic turret generates a strong lateral moment, which places high requirements on the moment bearing and connection of the mounting bracket structure. Utility Model Content

[0004] In order to solve the above problems, the utility model provides a large load-bearing docking flange structure, which can meet the installation of equipment with long cantilever, large weight and annular interface on the nose of an aircraft, and solves the connection between the equipment and the front airtight end frame of the aircraft.

[0005] The technical solution of the utility model is as follows:

[0006] A large load-bearing docking flange structure comprises a front connecting ring, a rear connecting ring and an inclined web; the front connecting ring is an annular part with an interface for connecting annular equipment, the rear connecting ring is an annular structure connected to a front airtight end frame of an aircraft, the area and inner and outer diameters of the rear connecting ring are larger than those of the front connecting ring; the front connecting ring and the rear connecting ring are connected by an inclined web in the shape of an inclined cone ring, and a reinforcing rib structure is arranged on the inclined web.

[0007] Furthermore, the reinforcement rib structure includes inner reinforcement ribs and outer reinforcement ribs, the outer reinforcement ribs are arranged on the outer side of the inclined web and supported between the front connecting ring and the rear connecting ring; the inner reinforcement ribs are arranged on the inner side of the inclined web and supported between the front connecting ring and the rear connecting ring.

[0008] Furthermore, the number of the inner reinforcing ribs and the outer reinforcing ribs are the same and their positions are aligned.

[0009] Furthermore, the external reinforcement rib is a T-shaped structure, the wide side of the external reinforcement rib is connected to the front connecting ring, and the narrow side of the front connecting ring is connected to the rear connecting ring.

[0010] Furthermore, the outer reinforcing rib is thickened at the connecting ring after connection and a transition arc surface is added.

[0011] Furthermore, the front connecting ring is provided with a reinforcing boss protruding toward the rear connecting ring between adjacent outer reinforcing rib connections, and the connecting annular device interface is provided on the back side of the reinforcing boss.

[0012] Furthermore, the inner reinforcing rib is a triangular structure composed of two hinge structures, and one side of the triangular structure is arranged on the rear connecting ring.

[0013] Furthermore, it also includes a guide pin, and the front connecting ring is provided with a guide hole that matches the connected annular device, and the guide pin matches the guide hole.

[0014] The beneficial effects of the utility model are as follows:

[0015] The utility model provides a load-bearing connection structure in which a photoelectric turret is installed in front of an airtight end frame of an aircraft nose. The structure can solve the installation of a long cantilever, a heavy weight, and an annular connection interface on the aircraft nose, and can also solve the load transmission of large equipment installed on the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solution of the implementation method of the utility model patent, the following is a brief introduction to the drawings required for use in the implementation method. It should be understood that the following drawings only show certain embodiments of the utility model patent and should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying creative work.

[0017] Figure 1 It is the overall diagram of the docking flange structure;

[0018] Figure 2 This is the front view of the alignment flange structure;

[0019] Figure 3 This is the right view of the docking flange structure;

[0020] Figure 4 It is the detailed drawing of the guide pin of the docking flange structure;

[0021] Among them, 1.1 is the front connecting ring; 1.2 is the rear connecting ring; 1.3 is the inner reinforcing rib; 1.4 is the outer reinforcing rib; 1.5 is the reinforcing boss; 1.6 is the inclined web; 2.1 is the guide pin; 2.2 is the washer; and 2.3 is the nut. DETAILED DESCRIPTION

[0022] This section is an embodiment of the utility model, which is used to explain and illustrate the technical solution of the utility model. In the absence of conflict, the embodiments of the utility model and the features in the embodiments can be combined with each other.

[0023] In the description of the present utility model, it is necessary to understand that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicating directions or positional relationships are based on the orientations or positional relationships of the accompanying drawings, and are only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or case referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present utility model. In addition, the terms "first", "second", etc. are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implying the number of technical features indicated. Thus, features defined as "first", "second", etc. may explicitly or implicitly include more of the features. In the description of the present utility model, unless otherwise specified, "multiple" means two or more.

[0024] In the description of the present utility model, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be interpreted in a broad sense, for example, it can be a fixed connection, a detachable connection or an integrated connection; it can be a mechanical connection or a point connection; it can be a direct connection or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present utility model can be understood by specific circumstances.

[0025] Embodiment 1:

[0026] A large load-bearing butt flange structure comprises a front connecting ring 1.1, a rear connecting ring 1.2 and an inclined web 1.6; the front connecting ring 1.1 is an annular component having an interface for connecting annular equipment, the rear connecting ring 1.2 is an annular structure connected to a front airtight end frame of an aircraft, the area and inner and outer diameters of the rear connecting ring 1.2 are greater than those of the front connecting ring 1.1; the front connecting ring 1.1 and the rear connecting ring 1.2 are connected by an inclined web 1.6 in the shape of an inclined cone ring, and a reinforcing rib structure is provided on the inclined web 1.6.

[0027] The reinforcing rib structure includes inner reinforcing ribs 1.3 and outer reinforcing ribs 1.4. The outer reinforcing ribs 1.4 are arranged on the outer side of the inclined web 1.6 and supported between the front connecting ring 1.1 and the rear connecting ring 1.2; the inner reinforcing ribs 1.3 are arranged on the inner side of the inclined web 1.6 and supported between the front connecting ring 1.1 and the rear connecting ring 1.2.

[0028] The number of the inner reinforcing ribs 1.3 and the outer reinforcing ribs 1.4 are the same and their positions are aligned.

[0029] The outer reinforcing rib 1.4 is a T-shaped structure, the wide side of the outer reinforcing rib 1.4 is connected to the front connecting ring 1.1, and the narrow side of the front connecting ring 1.1 is connected to the rear connecting ring 1.2.

[0030] The outer reinforcing rib 1.4 is thickened and has a transition cambered surface at the rear connecting ring 1.2.

[0031] The front connecting ring 1.1 is provided with a reinforcing boss 1.5 protruding toward the rear connecting ring 1.2 between the connecting parts of the adjacent outer reinforcing ribs 1.4, and the connecting annular device interface is arranged on the back side of the reinforcing boss 1.5.

[0032] The inner reinforcing rib 1.3 is a triangular structure composed of two hinge structures, and one side of the triangular structure is arranged on the rear connecting ring 1.2.

[0033] It also includes a guide pin 2.1. The front connecting ring 1.1 is provided with a guide hole that matches the connected annular device, and the guide pin 2.1 matches the guide hole.

[0034] Embodiment 2:

[0035] The utility model is realized by the following technical scheme: a docking flange structure is designed between the front airtight end frame of the aircraft nose and the photoelectric turret, the docking flange structure is mainly composed of a front docking flange and a guide pin; the docking flange is composed of a front connecting ring, a rear connecting ring, an outer reinforcing rib, an inner reinforcing rib, an inclined web, and a reinforcing boss; the guide pin is composed of a guide pin, a washer and a nut.

[0036] The docking flange mainly transfers the load of the optoelectronic turret equipment to the fuselage structure through bending moment, shear force and torque. The front connecting ring is docked with the docking ring of the equipment; a boss is designed at the bolt connection between the front connecting ring and the equipment docking ring to reduce the stress in the bolt connection area of ​​the front connecting ring; the external reinforcement ribs and the internal reinforcement ribs work together to support the inclined web, and at the same time transfer the load of the front connecting ring to the rear connecting ring of the docking flange; the inclined web mainly transfers the load of the front connecting ring to the rear connecting ring, and at the same time plays a waterproof seal in the docking flange area; the rear connection transfers the load transmitted by the front connecting ring to the fuselage structure, and at the same time satisfies the connection between the docking flange and the front airtight end frame of the aircraft nose.

[0037] The guide pin is mainly used to solve the alignment of the interface of the optoelectronic turret installation. The optoelectronic turret is aligned with the guide pin on the front connecting ring of the docking flange through the guide pin hole on the docking ring to ensure that the optoelectronic turret can be installed in the correct position; the nut is mainly used to fix the guide pin on the front connecting ring of the docking flange; the main function of the washer is to ensure that the nut protects the surface of the front connecting ring during the tightening process, while increasing the force-bearing area of ​​the nut and the front connecting ring and reducing compressive stress.

[0038] The device is mainly composed of a docking flange and a guide assembly. The docking flange is composed of a front connecting ring, a rear connecting ring, an outer reinforcing rib, an inner reinforcing rib, an inclined web and a reinforcing boss; the guide assembly is composed of a guide pin, a washer and a nut.

[0039] The inner diameter of the front connecting ring is φ776mm, the outer diameter is φ866mm, and the thickness is 10mm; there are 18 inner and outer reinforcing ribs along the circumference, arranged equidistantly, the inner reinforcing ribs are aligned with the outer reinforcing ribs, and the thickness is 5mm; the thickness of the inclined web is 5mm; the inner diameter of the rear connecting ring is φ816mm, the outer diameter is φ982mm, and the thickness is 10mm; the thickness of the reinforcing boss at the bolt connection on the front connecting ring is 15mm; the diameter of the guide pin is φ12mm, the guide length is 50mm, the nut is an M12 self-locking nut, and the washer has an inner diameter of φ13mm, an outer diameter of φ18mm, and a thickness of 2mm.

[0040] This docking flange structure solves the problem of installing the optoelectronic turret on the aircraft nose, and can withstand and transmit the bending moment, shear force and torque of the optoelectronic turret.

[0041] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the utility model, but the protection scope of the utility model is not limited thereto. Any technician familiar with the field can easily think of various equivalent modifications or substitutions within the technical scope disclosed in the utility model, and these modifications or substitutions should be included in the protection scope of the utility model.

Claims

1. A large load-bearing butt flange structure, characterized in that: The invention comprises a front connecting ring (1.1), a rear connecting ring (1.2) and an inclined web (1.6); the front connecting ring (1.1) is an annular part having an interface for connecting annular equipment, the rear connecting ring (1.2) is an annular structure connected to the front airtight end frame of the aircraft, and the area and inner and outer diameters of the rear connecting ring (1.2) are both larger than the area and inner and outer diameters of the front connecting ring (1.1); the front connecting ring (1.1) and the rear connecting ring (1.2) are connected by an inclined web (1.6) in the shape of an inclined cone ring, and a reinforcing rib structure is provided on the inclined web (1.6).

2. A large load-bearing butt flange structure according to claim 1, characterized in that: The reinforcing rib structure comprises an inner reinforcing rib (1.3) and an outer reinforcing rib (1.4); the outer reinforcing rib (1.4) is arranged on the outer side of the inclined web (1.6) and supported between the front connecting ring (1.1) and the rear connecting ring (1.2); and the inner reinforcing rib (1.3) is arranged on the inner side of the inclined web (1.6) and supported between the front connecting ring (1.1) and the rear connecting ring (1.2).

3. A large load-bearing butt flange structure according to claim 2, characterized in that: The number of the inner reinforcing ribs (1.3) and the outer reinforcing ribs (1.4) are the same and their positions are aligned.

4. A large load-bearing butt flange structure according to claim 2, characterized in that: The external reinforcing rib (1.4) is a T-shaped structure, the wide side of the external reinforcing rib (1.4) is connected to the front connecting ring (1.1), and the narrow side of the front connecting ring (1.1) is connected to the rear connecting ring (1.2).

5. A large load-bearing butt flange structure according to claim 4, characterized in that: The outer reinforcing rib (1.4) is thickened and has a transitional cambered surface at the connection rear connection ring (1.2).

6. A large load-bearing butt flange structure according to claim 4, characterized in that: The front connecting ring (1.1) is provided with a reinforcing boss (1.5) protruding toward the rear connecting ring (1.2) between the connecting parts of adjacent outer reinforcing ribs (1.4), and the connecting annular device interface is provided on the back side of the reinforcing boss (1.5).

7. A large load-bearing butt flange structure according to claim 2, characterized in that: The inner reinforcing rib (1.3) is a triangular structure composed of two hinge structures, and one side of the triangular structure is arranged on the rear connecting ring (1.2).

8. The large load-bearing butt flange structure according to claim 1, characterized in that: It also includes a guide pin (2.1), and a guide hole matching the connected annular device is provided on the front connecting ring (1.1), and the guide pin (2.1) matches the guide hole.

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