A docking-assisted aircraft flange connection structure

Abstract

The utility model relates to the technical field of flange plate structure discloses a kind of aircraft flange plate connecting structure of supplementary butt joint, including flange structure ontology one and the flange structure ontology two of being set in flange structure ontology one side, the side fixed connection of flange structure ontology one has placing block, the side fixed connection of flange structure ontology two has connecting box, placing block and connecting box are provided with two groups, the side of connecting box is provided with placing groove, placing groove and placing block sliding fit, the utility model is through the setting of bolt, placing groove, connecting box and placing block, realized the effect that flange structure ontology one and flange structure ontology two can be conveniently butt jointed by staff Installation, improve use effect, solve the existing flange plate connecting structure when butt joint installation, often all through the mode of multiple groups of bolt nut is realized, this kind of connecting installation method greatly reduces the work efficiency of staff, and then influence aircraft use Problem.

Description

Technical Field

[0001] This utility model relates to the field of flange structure technology, specifically to an aircraft flange connection structure that can assist in docking. Background Technology

[0002] Aircraft flange connection structures are important structures used to connect various components of an aircraft, such as engines, wings, and fuselage sections. Common types include bolted flange structures, quick-release flange structures, and plug-in flange structures. The design requirements need to achieve high strength and lightweight characteristics, but existing flange connection structures still have some problems in actual use. For example, patent application number CN202421714491.1 discloses a frame joint and its connection system, including a flange, an inner tube receiving part and an outer tube receiving part. The outer tube receiving part is concentrically arranged outside the inner tube receiving part, and an annular space is formed between the inner tube receiving part and the outer tube receiving part. At least one rib is provided in the annular space to connect the inner tube receiving part and the outer tube receiving part, which has the characteristic of improving the sealing performance during connection. Existing flange connection structures are often achieved by using multiple sets of bolts and nuts during docking and installation. This connection and installation method greatly reduces the work efficiency of the staff, thus affecting the use of the aircraft.

[0003] To address the aforementioned issues, a flange connection structure for aircraft that can assist in docking is proposed. Utility Model Content

[0004] The purpose of this invention is to provide an aircraft flange connection structure that can assist in docking. By using this device, the problem of existing flange connection structures, which are often installed by using multiple sets of bolts and nuts, is solved. This connection and installation method greatly reduces the work efficiency of the staff and thus affects the use of the aircraft.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a flange connection structure for assisted docking of an aircraft, comprising a flange structure body one and a flange structure body two disposed on one side of the flange structure body one. A placement block is fixedly connected to one side of the flange structure body one, and a connection box is fixedly connected to one side of the flange structure body two. Two sets of placement blocks and connection boxes are provided. A placement groove is provided on one side of the connection box, and the placement groove slides with the placement block. The connection box is provided with a fixing mechanism, which fixes the placement block.

[0006] Preferably, the fixing mechanism includes a bolt that passes through the connecting box, and the placement block has a threaded groove that matches the bolt.

[0007] The above-mentioned structural design, through the threaded engagement of the bolts and the threaded groove, can quickly achieve mechanical locking after the placement block slides into the placement groove. Compared with the traditional method of dispersed fixing with multiple sets of bolts, it reduces the number of bolts used and simplifies the docking process. At the same time, the bolts pass through the connection box and act directly on the placement block, which can ensure the connection strength and avoid loosening gaps after docking, thus balancing installation efficiency and connection reliability.

[0008] Preferably, a spring rod is fixedly connected inside the connecting box, a contact block is fixedly connected to one end of the spring rod, and a rotating rod is rotatably connected to one end of the contact block.

[0009] The above-mentioned structural design utilizes the elastic potential energy of the spring rod to drive the contact block, ensuring that the rotating rod always tends to move in the direction of the bolt. The rotational connection between the contact block and the rotating rod can flexibly adapt to the angle adjustment of the rotating rod, providing guidance for the precise fit between the connecting ring and the connecting groove, forming a secondary fixing preload on the bolt, and enhancing structural stability.

[0010] Preferably, a connecting ring is fixedly connected to the inner side of the rotating rod, a connecting groove is provided at one end of the bolt, the connecting groove is slidably engaged with the connecting ring, and the connecting ring is provided with a friction layer.

[0011] With the above-mentioned structural design, the sliding fit between the connecting ring and the connecting groove can achieve circumferential positioning after the bolt is tightened. The friction layer (such as a composite coating of alumina and organic resin) increases the friction of the contact surface, effectively preventing the bolt from loosening due to vibration. The adjustable angle of the connecting ring with the rotating rod can adapt to the bolt position under different tightening degrees, ensuring the versatility and effectiveness of the locking mechanism.

[0012] Preferably, the fixing mechanism includes a pressing block slidably connected to one side of the connecting box, one end of the pressing block being rotatably connected to a rotating rod, and one end of the rotating rod being rotatably connected to a fixing block.

[0013] The above-mentioned structural design uses the linear motion of the pressing block to drive the rotation of the rotating rod, which converts the operating force into the lateral displacement of the fixed block, realizing the convenient switching between "press-unlock" and "release-lock". Compared with bolt connection, docking and fixing can be completed without tools, which is especially suitable for rapid disassembly and assembly scenarios in the confined space of aircraft, greatly improving emergency maintenance efficiency.

[0014] Preferably, the fixing block is slidably connected inside the connecting box, and a spring rod is fixedly connected to one side of the fixing block.

[0015] With the above-mentioned structure, the sliding connection of the fixing block in the connecting box limits its movement trajectory, avoiding locking failure caused by deviation; the elastic reset function of the spring rod can automatically push the fixing block into the fixing groove when the pressing block is released, forming a stable elastic locking structure. This design can maintain the fixed state without continuously applying external force, reducing the impact of human operation error on connection reliability.

[0016] Preferably, one end of the second spring rod is fixedly connected to the inside of the connecting box, and a fixing groove is provided on one side of the placement block, the fixing groove being slidably engaged with the fixing block.

[0017] With the above-mentioned structural design, the fixed connection between the spring rod and the connecting box provides stable support for the elastic locking. The shape matching between the fixing groove and the fixing block can achieve dual radial and axial limiting, preventing the placement block from slipping out of the placement groove under the vibration environment of the aircraft. This purely mechanical structure does not require electric drive, which improves the fault tolerance under extreme working conditions.

[0018] Compared with the prior art, the beneficial effects of this utility model are as follows: 1. This application, through the setting of bolts, placement grooves, connection boxes, and placement blocks, enables workers to easily connect and install flange structure body one and flange structure body two, improving the usage effect and solving the problem that existing flange connection structures often use multiple sets of bolts and nuts for connection and installation, which greatly reduces the work efficiency of workers and thus affects the use of aircraft.

[0019] 2. This application, through the setting of spring rod, connecting groove and connecting ring, effectively prevents the bolt from rotating, thereby improving the efficiency of the device and solving the problem that the bolts in the existing flange connection structure generally lack an effective fixing mechanism and are prone to rotation. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of this utility model; Figure 2 This is a structural diagram of the connecting box and placement slot of this utility model; Figure 3 This is a structural diagram of the bolt and spring rod of this utility model; Figure 4 This is a structural diagram of the pressing block and fixing groove of this utility model; Figure 5 This is a structural diagram of the spring rod and the fixing block of this utility model.

[0021] In the diagram: 1. Flange structure body one; 11. Placement block; 2. Flange structure body two; 21. Connection box; 211. Placement groove; 22. Bolt; 221. Thread groove; 222. Spring rod one; 2221. Contact block; 223. Rotating rod one; 224. Connecting ring; 225. Connecting groove; 23. Pressing block; 231. Rotating rod two; 232. Fixing block; 233. Spring rod two; 234. Fixing groove. Detailed Implementation

[0022] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0023] To further understand the content of this utility model, a detailed description of this utility model will be provided in conjunction with the accompanying drawings.

[0024] Combination Figure 1 and Figure 2 A flange connection structure for assisting docking of an aircraft includes a flange structure body 1 and a flange structure body 2 disposed on one side of the flange structure body 1. A placement block 11 is fixedly connected to one side of the flange structure body 1, and a connection box 21 is fixedly connected to one side of the flange structure body 2. Both the placement block 11 and the connection box 21 are provided in two sets. A placement groove 211 is provided on one side of the connection box 21. The placement groove 211 slides with the placement block 11. The connection box 21 is provided with a fixing mechanism, which fixes the placement block 11.

[0025] The present invention will be further described below with reference to the embodiments.

[0026] Example 1: To address the issue that existing flange connection structures often rely on multiple sets of bolts and nuts for installation, which significantly reduces worker efficiency and consequently impacts aircraft operation, this embodiment discloses the following technical solution, specifically as follows: Figures 1-3As shown, the fixing mechanism includes a bolt 22 that passes through the connecting box 21. The placement block 11 has a threaded groove 221 that matches the bolt 22. A spring rod 222 is fixedly connected inside the connecting box 21. One end of the spring rod 222 is fixedly connected to a contact block 2221. One end of the contact block 2221 is rotatably connected to a rotating rod 223. A connecting ring 224 is fixedly connected to the inner side of the rotating rod 223. One end of the bolt 22 has a connecting groove 225 that slides with the connecting ring 224. The connecting ring 224 has a friction layer. During use, two sets of pipes can be connected to flange structure body 1 and flange structure body 2 respectively. Then, the placement block 11 on one side of flange structure body 1 is aligned with the placement groove 211 of the connecting box 21 on flange structure body 2 and moved, causing the placement block 11 to move into the placement groove 211. By rotating the bolt 22 located on the connecting box 21, one end of the bolt 22 rotates into the threaded groove 221 of the placement block 11, thereby fixing the placement block 11. The operator can also rotate the rotating rod 223 located on the connecting box 21. The rotation of the rotating rod 223 causes the connecting ring 224 to rotate. After the connecting ring 224 is aligned with the connecting groove 225 on the bolt 22, the rotating rod 223 is released. Under the action of the spring rod 222, the connecting ring 224 on the rotating rod 223 automatically enters the interior of the connecting groove 225. Both the interior of the connecting ring 224 and the interior of the connecting groove 225 are coated with a composite coating of alumina and organic resin, which can effectively prevent the bolt 22 from rotating, thereby completing the installation of the placement block 11. This allows the operator to easily connect and install the flange structure body 1 and the flange structure body 2, improving the usage effect.

[0027] Example 2: This embodiment discloses another disassembly method, which differs from Embodiment 1, and facilitates the docking and installation of flange structure body 1 and flange structure body 2 by the operator. For details, please refer to... Figures 4-5The fixing mechanism includes a pressing block 23 slidably connected to one side of the connecting box 21. One end of the pressing block 23 is rotatably connected to a rotating rod 231, and one end of the rotating rod 231 is rotatably connected to a fixing block 232. The fixing block 232 is slidably connected inside the connecting box 21. One side of the fixing block 232 is fixedly connected to a spring rod 233, and one end of the spring rod 233 is fixedly connected inside the connecting box 21. A fixing groove 234 is provided on one side of the placement block 11, and the fixing groove 234 slides with the fixing block 232. When installation is required, the pressing block 232 on the connecting box 21 can be pressed first. Pressing block 23 rotates, causing rotating rod 231 to rotate. Rotating rod 231 moves fixing block 232, allowing placement block 11 to be placed inside placement groove 211. Then, pressing block 23 is released, and under the action of spring rod 233, fixing block 232 moves into fixing groove 234 on placement block 11, thus completing the installation of placement block 11. When disassembly is required, pressing block 23 is pressed down, causing fixing block 232 to come out from inside fixing groove 234, thus separating flange structure body 2 from flange structure body 1.

[0028] It should be noted that the aforementioned electrical components are equipped with power supplies, and their control methods are existing technologies. To avoid redundancy, they will be described here uniformly. Furthermore, this application is primarily for the protection of mechanical equipment, so the control methods and circuit connections will not be explained in detail herein. In this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus.

[0029] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A flange connection structure for assisted docking of an aircraft, comprising a flange structure body one (1) and a flange structure body two (2) disposed on one side of the flange structure body one (1), characterized in that: A placement block (11) is fixedly connected to one side of the flange structure body one (1), and a connection box (21) is fixedly connected to one side of the flange structure body two (2). The placement block (11) and the connection box (21) are provided in two sets. A placement groove (211) is provided on one side of the connection box (21). The placement groove (211) is slidably engaged with the placement block (11). The connection box (21) is provided with a fixing mechanism, which serves to fix the placement block (11).

2. The aircraft flange connection structure for assisted docking according to claim 1, characterized in that: The fixing mechanism includes a bolt (22) that passes through the connecting box (21), and the placement block (11) has a threaded groove (221) that matches the bolt (22).

3. The aircraft flange connection structure for assisted docking according to claim 2, characterized in that: A spring rod (222) is fixedly connected inside the connecting box (21). A contact block (2221) is fixedly connected to one end of the spring rod (222), and a rotating rod (223) is rotatably connected to one end of the contact block (2221).

4. The aircraft flange connection structure for assisted docking according to claim 3, characterized in that: A connecting ring (224) is fixedly connected to the inner side of the rotating rod (223). A connecting groove (225) is provided at one end of the bolt (22). The connecting groove (225) slides with the connecting ring (224). The connecting ring (224) is provided with a friction layer.

5. The aircraft flange connection structure for assisted docking according to claim 1, characterized in that: The fixing mechanism includes a pressing block (23) slidably connected to one side of the connecting box (21), one end of the pressing block (23) is rotatably connected to a rotating rod (231), and one end of the rotating rod (231) is rotatably connected to a fixing block (232).

6. The aircraft flange connection structure for assisted docking according to claim 5, characterized in that: The fixing block (232) is slidably connected inside the connecting box (21), and a spring rod (233) is fixedly connected to one side of the fixing block (232).

7. The aircraft flange connection structure for assisted docking according to claim 6, characterized in that: One end of the second spring rod (233) is fixedly connected to the inside of the connecting box (21), and a fixing groove (234) is provided on one side of the placement block (11), and the fixing groove (234) slides with the fixing block (232).

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