Structure for aircraft equipment installation

Abstract

The invention discloses a structure for aircraft equipment installation, which comprises an aircraft body installation joint, an equipment installation joint, an equipment installation bolt, a special nut and an anti-drop assembly, the aircraft body installation joint is in a right-angle plate shape, a placing groove is arranged at the right-angle position, the special nut is placed in the placing groove, and the anti-drop assembly is arranged in the placing groove. One end of the equipment mounting joint is fixedly connected with the aircraft body mounting joint through equipment mounting bolts penetrating through aircraft skin, the other end of the equipment mounting joint is used for mounting aircraft external equipment, the aircraft body mounting joint is arranged in an aircraft structure, and the anti-falling assembly is fixed to the groove wall of the placing groove and used for preventing the special nut from falling off; the special nut has the advantages that the special nut does not need to be detached from the placing groove, when an external equipment mounting bolt is disassembled and assembled, the special nut does not need to be stopped by a tool, a force-bearing maintenance covering cap does not need to be formed on the belly skin, and the structural integrity is guaranteed.

Description

Technical Field The invention belongs to the field of aviation structure design, and specifically relates to a structure for installing aircraft equipment. Background Art

[0002] In order to expand the use capability and purpose of the aircraft, the aircraft needs to be equipped with various functional equipment on the outside, such as pods, auxiliary fuel tanks, smoke extractors, etc. Therefore, it is necessary to arrange external equipment installation joints inside the aircraft. When the aircraft performs a mission, it is necessary to quickly replace the corresponding external equipment. Since the internal space of the aircraft is very limited, and the external equipment needs to be replaced quickly, the structure also needs to ensure sufficient strength. In order to ensure the integrity of the structural belly skin, it is not appropriate to arrange a load-bearing maintenance cover near the installation of external equipment on the belly. For this reason, we designed a special structural form for external equipment installation, which can quickly replace external equipment and ensure sufficient structural strength. Summary of the invention

[0003] In view of the above-mentioned prior art, the purpose of the present invention is to overcome the deficiencies in the prior art and adapt to actual needs, thereby providing a structure for aircraft equipment installation that can quickly replace equipment and ensure sufficient structural strength.

[0004] In order to achieve the above-mentioned purpose, the technical solution adopted by the present invention is: a structure for installing aircraft equipment, including a body mounting joint, an equipment mounting joint, an equipment mounting bolt, a special nut and an anti-dropping assembly. The body mounting joint is in the shape of a right-angled plate, and a placement groove is provided at the right angle. The special nut is placed in the placement groove. One end of the equipment mounting joint is fixedly connected to the body mounting joint through the equipment mounting bolt passing through the aircraft skin, and the other end is used to install aircraft external equipment. The body mounting joint is arranged inside the aircraft structure, and the anti-dropping assembly is fixed to the wall of the placement groove and is used to prevent the special nut from falling off.

[0005] Furthermore, two vertical ribs parallel to each other are provided along the length direction of the right-angled plate of the body mounting joint, a transverse rib is provided between the two vertical ribs, the two vertical ribs and one transverse rib are combined at the right angle of the right-angled plate to form a placement groove, and the anti-slip assembly is fixed on the middle part of the transverse rib of the placement groove and is located at the upper end of the special nut.

[0006] Furthermore, it also includes an anti-wear gasket, which is installed in the mounting groove and located between the mounting groove and the special nut. When the equipment mounting bolt is being tightened or disassembled, the mounting groove and the anti-wear gasket can stop the special nut at the same time.

[0007] Furthermore, the anti-wear gasket is a U-shaped structure with a flat bottom, and the left and right ends and the bottom of the U-shaped structure are respectively attached to the left and right inner walls and the bottom of the placement groove.

[0008] Furthermore, the anti-slip assembly is an anti-slip bolt and a nut, the anti-slip bolt passes through the middle part of the transverse rib of the mounting groove and is fixed to the mounting groove by fastening with the nut, and the distance between the anti-slip bolt and the nut and the left and right side walls of the mounting groove is smaller than the total length of the special nut, and the width between the end of the anti-slip bolt and the nut and the front end side wall of the mounting groove is smaller than the total width of the special nut.

[0009] Furthermore, the special nut includes a square block, and a hexagonal nut structure and a bolt structure extend outward from the middle of the front and rear ends of the square block respectively. The hexagonal nut structure and the bolt structure at the front and rear ends of the square block are coaxially arranged, and a threaded through hole is provided in the middle of the special nut, and the threaded through hole passes through the middle of the hexagonal nut structure, the middle of the bolt structure and the middle of the square block.

[0010] Furthermore, the square block of the special nut is placed in the U-shaped opening of the anti-wear gasket, and the special nut is fixedly connected to the equipment mounting bolt through the threaded through hole in the middle. The anti-falling component is located at the upper end of the hexagonal nut structure of the special nut to prevent the special nut from falling off.

[0011] Furthermore, the equipment mounting bolt is a bolt with a conical head structure at the end. The equipment mounting bolt passes through one end of the equipment mounting joint, the skin, the opposite side of the transverse rib of the body mounting joint, the threaded through hole in the middle of the special nut and the middle of the transverse rib of the body mounting joint in sequence through the conical head structure to fix the equipment mounting joint and the body mounting joint to the skin.

[0012] Furthermore, the placement groove is a square groove.

[0013] Furthermore, the outer diameter of the equipment mounting bolt matches the diameter of the threaded through hole in the middle of the special nut, the total length of the square block in the middle of the special nut is smaller than the total width of the U-shaped opening of the anti-wear gasket, and the connecting line of the two diagonals of the square block in the middle of the special nut is larger than the total width of the U-shaped opening of the anti-wear gasket.

[0014] In the present invention, a placement groove for a special nut is arranged on the fuselage mounting joint, and the special nut can be normally disassembled and installed without using any tools. The fuselage mounting joint is arranged in the fuselage structure, which can be on a frame or a beam, and its appearance structure is designed together with the aircraft. The equipment mounting joint is an installation joint on the equipment, which belongs to a joint on the equipment, and its appearance structure is designed together with the equipment. The equipment mounting joint is installed outside the aircraft, and the special nut can be pre-buried in the aircraft structure through the fuselage mounting joint, and can be removed from the outside of the aircraft without using a wrench. The skin is the skin on the outer surface of the aircraft corresponding to the equipment installation position.

[0015] The beneficial effects of the present invention are as follows: (1) the special nut does not need to be removed from the mounting groove; (2) when disassembling and installing the external equipment mounting bolts, the special nut does not need to be stopped by tools; (3) there is no need to open a load-bearing maintenance cover on the belly skin, thereby ensuring the integrity of the structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the assembly of the present invention; Figure 2 It is a cross-sectional schematic diagram of the present invention; Figure 3 It is a schematic diagram of the decomposition of the present invention; Figure 4 The three-dimensional nut specially made for the present invention Figure 1 ; Figure 5 The three-dimensional nut specially made for the present invention Figure 2 .

[0017] In the figure: 1 - body mounting joint; 2 - skin; 3 - equipment mounting joint; 4 - equipment mounting bolt; 5 - special nut; 6 - anti-wear gasket; 7 - anti-drop bolt; 8 - nut; 9 - mounting groove; 10 - square block; 11 - hexagonal nut structure; 12 - bolt structure; 13 - threaded through hole; 14 - conical head structure. DETAILED DESCRIPTION

[0018] The specific implementation of the present invention is described in detail below in conjunction with the accompanying drawings. It should be understood that the specific implementation described here is only used to illustrate and explain the present invention, and is not used to limit the present invention.

[0019] In the description of the present application, it should be noted that the terms "center / portion", "up", "down", "left", "right", "front", "back", "vertical", "lateral", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0020] In addition, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "provided with", "placed on", etc. should be understood in a broad sense, for example, it 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 it can be indirectly connected 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 this application can be understood according to specific circumstances.

[0021] It is also necessary to understand that the terms "include / comprise", "consist of..." or any other variation thereof are intended to cover non-exclusive inclusion, so that a product, device, process or method including a series of elements includes not only those elements, but also other elements not explicitly listed when necessary, or also includes elements inherent to such product, device, process or method. In the absence of further restrictions, the elements defined by the sentence "include / comprise...", "consist of..." do not exclude the presence of other identical elements in the product, device, process or method including the elements. Example

[0022] like Figures 1 to 5 As shown, the present invention provides a structure for aircraft equipment installation, including a fuselage installation joint 1, a skin 2, an equipment installation joint 3, an equipment installation bolt 4, a special nut 5, an anti-wear gasket 6, an anti-slip bolt 7 and a nut 8.

[0023] The body mounting joint 1 is in the shape of a right-angled plate, and is provided with a placement groove 9 at a right angle, and a special nut 5 is placed in the placement groove 9. Two vertical ribs parallel to each other are provided on the right-angled plate of the body mounting joint 1 along the length direction, and a transverse rib is provided between the two vertical ribs, and the left ends and bottoms of the two vertical ribs are respectively fitted with the two right-angled sides of the right-angled plate, and the top and right ends are respectively flush with the top and right ends of the right-angled plate, and the two vertical ribs and one transverse rib are enclosed at the right angle of the right-angled plate to form a placement groove 9, and also include an anti-wear gasket 6, which is a U-shaped structure with a flat bottom, and the left and right ends and the bottom of the U-shaped structure are respectively fitted on the left and right inner walls and the bottom of the placement groove 9, and the bottom of the anti-wear gasket 6 The part is fixed in the mounting groove 9 by rivets, and the anti-wear gasket 6 is located between the mounting groove 9 and the special nut 5. When the equipment mounting bolt 4 is in the process of tightening or disassembling, the mounting groove 9 and the anti-wear gasket 6 can stop the special nut 5 at the same time, and the anti-dropping bolt 7 and the nut 8 constitute an anti-dropping assembly. The anti-dropping bolt 7 passes through the middle part of the transverse rib of the mounting groove 9 and is fixed on the mounting groove 9 by the nut 8, and the distance between the anti-dropping bolt 7 and the nut 8 and the left and right side walls of the mounting groove 9 is less than the total length of the special nut 5, and the distance between the end of the anti-dropping bolt 7 and the nut 8 and the front end side wall of the mounting groove 9 is less than the total width of the special nut 5, so that the anti-dropping bolt 7 and the nut 8 can prevent the special nut 5 from falling off, and the anti-dropping bolt 7 and the nut 8 are located at the hexagonal nut structure of the special nut 5. The special nut 5 includes a square block 10, and a hexagonal nut structure 11 and a bolt structure 12 are respectively extended outward from the middle of the front and rear ends of the square block 10. The hexagonal nut structure 11 and the bolt structure 12 at the front and rear ends of the square block 10 are coaxially arranged. A threaded through hole 13 is provided in the middle of the special nut 5. The threaded through hole 13 passes through the middle of the hexagonal nut structure 11, the middle of the bolt structure 12 and the middle of the square block 10. The square block 10 of the special nut is placed in the U-shaped opening of the anti-wear gasket 6. The special nut 5 is fixedly connected with the equipment mounting bolt 4 through the threaded through hole 13 in the middle. The anti-slip assembly is located at the upper end of the hexagonal nut structure 11 to prevent the special nut 5 from falling off. One end of the equipment mounting joint 3 passes through the aircraft skin 2 and the fuselage through the equipment mounting bolt 4. The mounting joint 1 is fixedly connected, and the other end is used to install aircraft external equipment. One end of the equipment mounting bolt 4 is a conical head structure 14, and the other end is a bolt structure. The equipment mounting bolt 4 passes through one end of the equipment mounting joint 3, the skin 2, the opposite side of the transverse rib of the fuselage mounting joint 1, the threaded through hole 13 in the middle of the special nut and the middle of the transverse rib of the fuselage mounting joint 1 through the conical head structure 14 in sequence, and the equipment mounting joint 3 and the fuselage mounting joint 1 are fixed to the skin 2. The fuselage mounting joint 1 is arranged inside the aircraft structure, which can be a frame or a beam, and its appearance structure is designed together with the aircraft. The equipment mounting joint 3 is an installation joint on the equipment, which belongs to a joint on the equipment, and its appearance structure is designed together with the equipment. The equipment mounting joint 3 is installed outside the aircraft.The special nut 5 can be pre-buried in the aircraft structure through the fuselage mounting joint 1, and can be removed from the outside of the aircraft without using a wrench. The skin 2 is the skin on the outer surface of the aircraft corresponding to the equipment installation position.

[0024] Preferably, the placement groove 9 is a square groove.

[0025] Preferably, the square block 10 of the special nut 5 is a rectangular structure, and the end of the hexagonal nut structure 11 of the special nut 5 faces the transverse rib of the body mounting joint 1, and the end of the bolt structure 12 is in contact with the opposite side of the transverse rib of the body mounting joint 1.

[0026] Preferably, the outer diameter of the equipment mounting bolt 4 matches the aperture of the threaded through hole 13 in the middle of the special nut 5, the total length of the square block 10 in the middle of the special nut 5 is smaller than the total width of the U-shaped opening of the anti-wear gasket 6, and the diagonal line of the square block 10 in the middle of the special nut 5 is larger than the total width of the U-shaped opening of the anti-wear gasket 6.

[0027] In the present invention, the machine body mounting joint 1 needs to be arranged with two vertical ribs and one horizontal rib, forming a placement groove 9 at the bottom of the corner box, and an anti-wear gasket 6 is installed at the bottom of the placement groove 9. The special nut 5 is a square nut, which is placed in the placement groove 9. Anti-drop bolts 7 and nuts 8 are arranged on the horizontal ribs of the placement groove 9, and the head of the equipment mounting bolt 4 is designed to have a conical head. The design of the equipment mounting bolt 4 as a conical head will facilitate the installation of the equipment mounting bolt 4. The special nut 5 can be stopped by the placement groove 9 and the anti-wear gasket 6 during the tightening and disassembly process of the equipment mounting bolt 4, so the special nut 5 does not need to use a wrench. At the same time, anti-drop bolts 7 and nuts 8 are arranged on the ribs of the placement groove 9 to ensure that the special nut 5 can still stay in the placement groove 9 and does not fall off after the equipment mounting bolt 4 is disassembled.

[0028] The working principle of the present invention is as follows: aircraft equipment is installed on a fuselage mounting joint 1 through an equipment mounting joint 3 and an equipment mounting bolt 4 that passes through a skin 2 on an external structure of the aircraft. The fuselage mounting joint 1 is arranged on a frame or a beam inside the fuselage structure. The equipment mounting bolt 4 is guided by a tapered head structure 14 at the tail to be quickly installed into a special nut 5. The equipment mounting bolt 4 needs to be tightened or disassembled using tools such as a wrench. During the disassembly or installation process of the equipment mounting bolt 4, the square block 10 of the special nut 5 will be directly clamped through the anti-wear gasket 6 after the special nut 5 is rotated, which is convenient for the disassembly or installation of the equipment mounting bolt 4. After the equipment mounting bolt 4 is disassembled, the anti-slip bolt 7 will prevent the special nut 5 from falling off, ensuring that the special nut 5 always remains in the placement groove 9.

[0029] This structure can ensure rapid replacement of equipment while ensuring the integrity of the machine body structure, has low production costs, good practicality, and is easy to promote and apply. It is an innovative design with great value.

[0030] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A structure for installing aircraft equipment, characterized in that: It includes a fuselage mounting joint, an equipment mounting joint, equipment mounting bolts, special nuts and an anti-dropping assembly. The fuselage mounting joint is a right-angled plate and is provided with a mounting groove at the right angle. The special nut is placed in the mounting groove. One end of the equipment mounting joint is fixedly connected to the fuselage mounting joint through the aircraft skin through the equipment mounting bolt, and the other end is used to install aircraft external equipment. The fuselage mounting joint is arranged inside the aircraft structure. The anti-dropping assembly is fixed to the wall of the mounting groove and is used to prevent the special nut from falling off.

2. The structure for installing aircraft equipment according to claim 1, characterized in that: Two vertical ribs parallel to each other are provided along the length direction of the right-angled plate of the body mounting joint, a transverse rib is provided between the two vertical ribs, the two vertical ribs and one transverse rib are combined at the right angle of the right-angled plate to form a placement groove, and the anti-drop assembly is fixed on the middle part of the transverse rib of the placement groove and is located at the upper end of the special nut.

3. The structure for installing aircraft equipment according to claim 2, characterized in that: It also includes an anti-wear gasket, which is installed in the mounting groove and located between the mounting groove and the special nut. When the equipment mounting bolt is being tightened or disassembled, the mounting groove and the anti-wear gasket can stop the special nut at the same time.

4. The structure for installing aircraft equipment according to claim 3, characterized in that: The anti-wear gasket is a U-shaped structure with a flat bottom. The left and right ends and the bottom of the U-shaped structure are respectively attached to the left and right inner walls and the bottom of the placement groove.

5. The structure for installing aircraft equipment according to claim 2, characterized in that: The anti-slip assembly consists of an anti-slip bolt and a nut. The anti-slip bolt passes through the middle of the transverse rib of the mounting groove and is fixed to the mounting groove by fastening with the nut. The distance between the anti-slip bolt and the nut and the left and right side walls of the mounting groove is less than the total length of the special nut. The width between the ends of the anti-slip bolt and the nut and the front end side wall of the mounting groove is less than the total width of the special nut.

6. The structure for installing aircraft equipment according to claim 4, characterized in that: The special nut includes a square block, and a hexagonal nut structure and a bolt structure extend outward from the middle of the front and rear ends of the square block respectively. The hexagonal nut structure and the bolt structure at the front and rear ends of the square block are coaxially arranged. A threaded through hole is provided in the middle of the special nut, and the threaded through hole passes through the middle of the hexagonal nut structure, the middle of the bolt structure and the middle of the square block.

7. The structure for installing aircraft equipment according to claim 6, characterized in that: The square block of the special nut is placed in the U-shaped opening of the anti-wear gasket. The special nut is fixedly connected to the equipment mounting bolt through the threaded through hole in the middle. The anti-dropping component is located at the upper end of the hexagonal nut structure of the special nut.

8. The structure for installing aircraft equipment according to claim 6, characterized in that: The equipment mounting bolt is a bolt with a conical head structure at the end. The equipment mounting bolt passes through one end of the equipment mounting joint, the skin, the opposite side of the transverse rib of the fuselage mounting joint, the threaded through hole in the middle of the special nut and the middle of the transverse rib of the fuselage mounting joint through the conical head structure in sequence to fix the equipment mounting joint and the fuselage mounting joint to the skin.

9. The structure for installing aircraft equipment according to claim 1, characterized in that: The placement slot is a square slot.

10. The structure for installing aircraft equipment according to claim 8, characterized in that: The outer diameter of the equipment mounting bolt matches the diameter of the threaded through hole in the middle of the special nut, the total length of the square block in the middle of the special nut is smaller than the total width of the U-shaped opening of the anti-wear gasket, and the connecting line of the two diagonals of the square block in the middle of the special nut is larger than the total width of the U-shaped opening of the anti-wear gasket.

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