Quick disassembly and assembly structure and method for aircraft control surface hinge bolt

Abstract

The invention belongs to the technical field of aviation structure connection, and discloses a quick bolt disassembly and assembly structure applied to an aircraft hinge joint part, which consists of a bolt, a lug type connecting component, a bushing transition component, a screw, a limiting gasket and a special-shaped nut, the limiting gasket is matched with one cylinder of the special-shaped nut, and the lug type connecting component is matched with the other cylinder of the special-shaped nut; the lug type connecting components are fixedly connected through the screws to form a whole which cannot rotate and cannot be axially separated, and meanwhile the limiting gaskets are fastened to the outer surfaces of the lug type connecting components through the inner hexagon screws to achieve stable limiting. The problem that balance between rapidity and reliability is difficult to consider in traditional bolt connection is solved, and the disassembly and assembly efficiency of bolts in an aircraft hinge structure can be remarkably improved.

Description

Technical Field

[0001] This invention belongs to the field of aerospace structural connection technology, specifically relating to a bolt quick-release and assembly structure and method suitable for aircraft hinged connection parts. Background Technology

[0002] In the structural design and assembly of modern aircraft, articulated structures, as a key method for achieving rotary motion connections, are widely used in critical components such as control systems (e.g., control surface connections), landing gear retraction mechanisms, and engine mounts. These articulated structures typically consist of single / double-ear or multi-double-ear structures combined with bolts and nuts. While maintaining high strength and good maintainability, they also need to possess a certain degree of flexibility and ease of assembly and disassembly, making them one of the key aspects of modern aircraft connection technology. Traditional articulations often use a pin and nut method for fixation. During assembly, the operator needs to insert the bolt into the ear-type connection structure from one side and install the nut at the other end, tightening it to achieve axial clamping and thus form a rigid connection. However, in space-constrained areas such as the aircraft interior, this structure often requires two people to operate or the use of specialized tools, severely reducing on-site assembly efficiency, increasing maintenance workload, and resulting in poor consistency in repeated assembly, affecting quality stability.

[0003] In recent years, although some quick-locking bolt structures have been proposed, most still require simultaneous operation with the nut, or are complex in structure, costly, and have poor applicability. Especially in articulated structures, multiple requirements need to be considered, including rotational function, axial fixation, and repeated assembly and disassembly. Traditional bolt connections struggle to balance speed and reliability. Therefore, there is an urgent need for a new type of quick-release bolt structure suitable for aerospace articulated structures, which can achieve rapid operation while ensuring connection strength and stability, reducing reliance on manual labor, and improving assembly and maintenance efficiency. Summary of the Invention

[0004] The purpose of this invention is to provide a simple, convenient, and efficient structure and method for disassembling and assembling aircraft control surface hinge bolts. This invention addresses the problem of balancing speed and reliability in traditional bolt connections, significantly improving fastening efficiency, reducing assembly and maintenance costs, and enhancing structural connection reliability.

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

[0006] In a first aspect, the present invention provides a quick-release and reassembly structure for aircraft control surface hinge bolts, comprising: Two lug-type connecting members, with a bushing-type transition member provided between the two lug-type connecting members; The bolted connection anti-loosening structure includes a bolt, a limiting washer, and a special-shaped nut. The special-shaped nut is connected to the outside of the lug-type connecting member through the limiting washer. The bolt passes through the lug-type connecting member, the bushing-type transition member, and the limiting washer in sequence before being threadedly connected to the special-shaped nut.

[0007] As a further aspect of the present invention, the ear-type connecting member can be a single ear, a double ear, or a multi-ear type, and any two of these can be combined.

[0008] As a further aspect of the present invention: the bushing-type transition member is respectively installed in the mounting holes of the two lug-type connecting members.

[0009] As a further aspect of the present invention, the bushing-type transition member can be one or more combinations of flange bushing, sliding bushing, and bearing bushing.

[0010] As a further aspect of the present invention: the irregular nut is composed of two cylinders of different diameters connected together, the connection surface of the two is curved, wherein the larger cylinder is provided with a threaded hole to be matched with a bolt, and the smaller cylinder is connected and fixed to a limiting washer by a screw.

[0011] As a further aspect of the present invention: the limiting gasket includes a body and a limiting piece. The body is a plate and its length is greater than that of the irregular nut. One end of the plate is fixedly connected to the outer surface of the ear-type connecting member, and the other end is provided with a through hole adapted to the bolt. The limiting piece and the small cylinder of the irregular nut are connected and fixed by screws.

[0012] As a further aspect of the present invention: the limiting piece adopts a bent structure design, with one end vertically connected to the body and the other end parallel to the body, and the distance between the two is equivalent to the thickness of the irregular nut.

[0013] As a further aspect of the present invention: the body of the limiting gasket is fixed to the outer surface of the ear-type connecting member by means of an internal hexagonal screw and a threaded bushing.

[0014] Secondly, the present invention provides a method for quick assembly and disassembly of aircraft control surface hinge bolts, comprising the following steps: During assembly, first install the bushing-type transition component in the corresponding position of the lug-type connecting component; The irregularly shaped nut is connected to the outside of the lug-type connecting member by means of a limiting washer; The bolt is threaded through the lug-type connecting member, the bushing-type transition member, and the limiting washer in sequence, and then connected to the irregular nut. To disassemble, simply rotate the bolt in the opposite direction and pull it out.

[0015] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. This invention features rapid assembly and disassembly: The irregularly shaped nut and the limiting washer work together to fix the nut to the structure. During installation and disassembly, only the bolt body needs to be rotated relative to the nut, thus achieving assembly and disassembly of the entire structure through unilateral operation. This significantly shortens the assembly and disassembly time and improves the efficiency of aircraft maintenance and repair.

[0016] 2. The present invention provides a stable connection: the cylindrical part of the nut is fixed by a limiting washer, and the limiting washer is fixed to the lug-type connecting component by a hexagonal bolt, forming a stable connection system. This effectively prevents the nut from loosening during use and improves the safety of the overall aircraft structure.

[0017] 3. The present invention has a compact structure and is suitable for installation in confined spaces: by using the mechanical limiting fit between the limiting washer and the irregular nut, it replaces the traditional anti-loosening mechanism. During the disassembly and assembly process, only the bolt body needs to be rotated relative to the nut. It can be quickly assembled and locked in narrow parts such as compartments with limited space and wing hinge areas, which greatly improves the adaptability and integrability of the structure.

[0018] 4. Compared with traditional connection methods, this structure can significantly improve the efficiency of bolt disassembly and assembly in aircraft articulated structures. While ensuring the stability of the connection, it simplifies the disassembly and assembly process, reduces the difficulty and cost of maintenance operations, and meets the needs of efficient maintenance of aircraft structures.

[0019] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0020] Figure 1 This is an assembly isometric view of the bolt quick-release structure of the present invention.

[0021] Figure 2 This is an exploded view of the bolt quick-release and assembly structure of the present invention.

[0022] Figure 3 This is a cross-sectional schematic diagram of the bolt quick-release and assembly structure of the present invention.

[0023] The numbers in the diagram are explained as follows: 1. Ear-type connecting component A; 2. Ear-type connecting component B; 3. Bolt connection anti-loosening structure; 4. Bolt; 5. Limiting washer; 6. Screw; 7. Special-shaped nut; 8. Threaded bushing. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions in the embodiments of this invention will be described in more detail below with reference to the accompanying drawings.

[0025] In the accompanying drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of the present invention.

[0026] The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0027] The following is in conjunction with the appendix Figure 1-3 The embodiments of the present invention will be described in detail below.

[0028] Example 1 This invention provides a quick-release and reassembly structure for aircraft control surface hinge bolts, comprising: Two lug-type connecting members, with a bushing-type transition member provided between the two lug-type connecting members; The bolt connection anti-loosening structure 3 includes a bolt 4, a limiting washer 5, and a special-shaped nut 7. The special-shaped nut 7 is connected to the outside of the ear-type connecting member through the limiting washer 5. The bolt 4 passes through the ear-type connecting member, the bushing-type transition member, and the limiting washer 5 in sequence and is then threadedly connected to the special-shaped nut 7.

[0029] Furthermore, the ear-type connecting component can be single-ear, dual-ear, or multi-ear, and any two of these can be combined.

[0030] Furthermore, the bushing-type transition components are respectively installed in the mounting holes of the two lug-type connecting components.

[0031] Furthermore, the bushing-type transition member can be one or more combinations of flange bushings, sliding bushings, and bearing bushings.

[0032] Furthermore, the irregular nut 7 is composed of two cylinders of different diameters connected together, and the connection surface between the two is curved. The larger cylinder is provided with a threaded hole that is compatible with the bolt 4, and the smaller cylinder is connected and fixed to the limiting washer 5 by a screw 6.

[0033] Furthermore, the limiting gasket 5 includes a body and a limiting piece. The body is a plate and its length is greater than that of the irregular nut 7. One end of the plate is fixedly connected to the outer surface of the ear-type connecting member, and the other end is provided with a through hole adapted to the bolt 4. The limiting piece and the small cylinder of the irregular nut 7 are connected and fixed by screws 6.

[0034] Furthermore, the limiting piece adopts a bent structure design, with one end vertically connected to the body and the other end parallel to the body, and the distance between the two is equivalent to the thickness of the irregular nut 7.

[0035] Furthermore, the body of the limiting gasket 5 is fixed to the outer surface of the ear-type connecting member by means of an internal hex screw 6 and a threaded bushing 8.

[0036] A quick-release bolt structure is disclosed, suitable for articulated connections in aircraft. The core components include a bolt 4, two lug-type connecting members (e.g., single-lug or double-lug), a limiting washer 5, and a shaped nut 7. The bolt 4 passes axially through the lug-type connecting member, the bushing-like transition member, the limiting washer 5, and the shaped nut 7, before being connected to the shaped nut 7 by a screw 6. The shaped nut 7, consisting of two coaxial cylinders of different diameters, is located on one side of the bolt 4. The limiting washer 5 mates with one of the cylinders of the shaped nut 7 and is fixedly connected by a limiting pin, forming a non-rotatable and non-axially detachable unit. Simultaneously, the limiting washer 5 is secured to the outer surface of the double-lug structure by an internal hexagonal screw 6, achieving stable positioning.

[0037] With the above structure, during assembly, it is only necessary to rotate the bolt 4 from one side to tighten it with the irregular nut 7 to complete the connection; during disassembly, simply rotate the bolt 4 in the opposite direction and pull it out, without touching the nut end, which significantly improves space adaptability and operation efficiency.

[0038] This invention provides a method for quick assembly and disassembly of aircraft control surface hinge bolts, comprising the following steps: During assembly, first install the bushing-type transition component in the corresponding position of the lug-type connecting component; The irregular nut 7 is connected to the outside of the lug-type connecting member via the limiting washer 5; Bolt 4 is threaded through the lug-type connecting member, the bushing-type transition member, and the limiting washer 5 in sequence, and then connected to the irregular nut 7 by thread. To disassemble, simply rotate bolt 4 in the opposite direction and pull it out.

[0039] Example 2 This invention provides a quick-release and reassembly structure for aircraft control surface hinge bolts, comprising: At least two ear-type connecting components (such as any combination of single ear, double ear, and multiple ears), and bolt connection anti-loosening structure 3.

[0040] The bolt connection anti-loosening structure 3 includes: bolt 4, bushing-type transition member (such as flange bushing, sliding bushing, bearing bushing or combination thereof) disposed between the lugs, limiting washer 5, screw 6, and special-shaped nut 7. Among them, the bolt 4 passes through the lug-type connection member, bushing-type transition member, and limiting washer 5 in sequence along the axial direction, and is then connected to the special-shaped nut 7 by screw 6.

[0041] Bushing-type transition components are installed in the mounting holes of the two lug-type connecting components, serving as positioning and support functions. This ensures the coaxiality and connection stability of the lug structure while effectively reducing friction and wear between them.

[0042] One side of the bolt 4 is provided with a non-circular nut 7, which is composed of two coaxial cylinders of different diameters connected together. The limiting washer 5 mates with one of the cylinders of the non-circular nut 7. The limiting washer 5 and one of the cylinders of the non-circular nut 7 are fixedly connected by a screw 6 to form a whole that cannot be rotated or axially separated. At the same time, the limiting washer 5 is fastened to the outer surface of the lug structure by an internal hex screw 6 to achieve stable limiting.

[0043] The bolt 4 is assembled or disassembled with the irregular nut 7 by rotation, and the nut is limited in both the axial direction and the rotation direction.

[0044] See the attached diagram, such as Figure 1 As shown, the bolt quick-release structure of this application is suitable for aircraft hinged connection structures. Figure 2 As shown, during assembly, the bushing-type transition component is first installed at the corresponding position of the lug-type connecting component. Then, bolt 4 passes sequentially through lug-type connecting component B2, lug-type connecting component A1, limiting washer 5, and shaped nut 7. The limiting washer 5 mates with one of the cylindrical parts of the shaped nut 7, and is fixedly connected by screw 6. Finally, the limiting washer 5 is fixed to lug-type connecting component B2 by hexagonal screw 6 and threaded bushing 8. At this point, simply rotate bolt 4 from one side to tighten it with the shaped nut 7 to complete the installation; disassembly is achieved by simply rotating bolt 4 in the opposite direction and pulling it out.

[0045] Thus, the objective of this invention has been achieved.

[0046] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A quick-release and assembly structure for aircraft control surface hinge bolts, characterized in that, The application relates to a bolt connection anti-loosening structure. The ear type connecting member can be single-ear, double-ear or multi-ear. The bushing type transition member is installed in the mounting hole of the ear type connecting member.

2. The aircraft control surface hinge bolt quick disconnect structure according to claim 1, wherein, The bushing type transition member can be one or a combination of a flange bushing, a sliding bushing and a bearing bushing.

3. The aircraft control surface hinge bolt quick disconnect structure according to Claim 2, wherein, The special-shaped nut is composed of two cylindrical members with different diameters, and the connecting surfaces of the two cylindrical members are curved surfaces.

4. The aircraft control surface hinge bolt quick disconnect structure according to Claim 3, wherein, The limiting sheet is designed in a bending structure, one end of the limiting sheet is perpendicularly connected to the body, and the other end of the limiting sheet is parallel to the body, and the distance between the two ends is equivalent to the thickness of the special-shaped nut.

5. The aircraft control surface hinge bolt quick disconnect structure according to Claim 1, wherein, The body of the limiting sheet is connected and fixed to the outer surface of the ear type connecting member through an internal hexagonal screw and a threaded bushing.

6. The aircraft control surface hinge bolt quick disconnect structure according to Claim 5, wherein, The following steps are included:

7. The aircraft control surface hinge bolt quick disconnect structure according to Claim 6, wherein, During assembly, the bushing type transition member is first installed at the corresponding position of the ear type connecting member; 8. The aircraft control surface hinge bolt quick disconnect structure as defined in claim 6 or 7 wherein, The special-shaped nut is connected to the outer side of the ear type connecting member through the limiting sheet; 9. A method of quick disconnecting an aircraft control surface hinge bolt, comprising: The bolt is sequentially threaded through the ear type connecting member, the bushing type transition member and the limiting sheet, and is then screwed with the special-shaped nut; During disassembly, the bolt is only needed to be reversely rotated and pulled out. ​ ​ ​

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