A flange plate for an aircraft is provided, which is convenient to connect and install

Abstract

The utility model discloses a flange plate for aircraft convenient to connect and install, including first disc body and boss, the upper end surface integration of first disc body is provided with boss, the middle part of boss and first disc body is equipped with the central hole, the outer edge of first disc body is provided with the connecting assembly, the outer surface welding of first disc body has the reinforcing rib board. This flange plate for aircraft convenient to connect and install positioning boss adopts the circular truncated cone structure and four groups annular distribution, can play good guiding effect by the shape of upper narrow and lower wide when the second disc body installs, realizes quick accurate positioning, the elastic buckle of positioning boss upper end surface, in the installation process, the elastic deformation of extrusion, restores the original shape and is connected after reaching positioning recess, can effectively prevent first disc body and second disc body in the aircraft operation and separate because of the factors such as vibration, greatly enhanced the stability and reliability of the connection of both, guarantee the working performance of flange plate whole and the safe operation of aircraft.

Description

Technical Field

[0001] This utility model relates to the technical field of aircraft connection components, specifically to an aircraft flange that is easy to connect and install. Background Technology

[0002] A flange, often simply called a flange, is a general term that usually refers to a disc-shaped metal body with several holes around its perimeter for connecting other things. It is widely used in machinery. A flange is also called a flange plate or flange. It is a part that connects pipes to each other. It is connected to the pipe end. There are holes on the flange. Bolts are used to tightly connect two flanges. A gasket is used to seal between the flanges. A flange is a disc-shaped part and is most commonly used in pipeline engineering. Flanges are always used in pairs. In the field of aircraft manufacturing, flanges are key connecting components, and their performance directly affects the safe and stable operation of aircraft.

[0003] However, existing aircraft flanges still have certain problems during installation:

[0004] For example, a flange with application number CN201220507298.1 belongs to the flange field, including a flange body, a number of bolt holes for fixing reinforcing ribs on the flange body, a number of protrusions for positioning on one side of the flange body, and a matching groove on the back of the flange body corresponding to the protrusions.

[0005] Traditional flanges are usually fastened with multiple sets of bolts. Workers need to tighten each set of bolts one by one, which is time-consuming and affects installation efficiency. At the same time, the lack of an effective positioning structure when installing two sets of flanges means that when connecting the two sets of flanges, workers need to align the holes on the flanges first and then insert the pins, which reduces the connection accuracy and makes it difficult to meet the stringent requirements of large aircraft.

[0006] In view of this, in-depth research was conducted on the above issues, which led to the creation of this case.

[0007] To address the aforementioned issues, an innovative design was developed based on the existing flanges used in aircraft. Utility Model Content

[0008] The purpose of this utility model is to provide an aircraft flange that is easy to connect and install, in order to solve the problems mentioned in the background art, where flanges are usually fastened by multiple sets of bolts, requiring workers to tighten each set of bolts one by one, which is time-consuming and affects installation efficiency. At the same time, when installing two sets of flanges, there is a lack of effective positioning structure, which means that when connecting two sets of flanges, workers need to align the holes on the flanges first and then insert the pins, which reduces the connection accuracy and makes it difficult to meet the stringent requirements of large aircraft.

[0009] To achieve the above objectives, this utility model provides the following technical solution:

[0010] An aircraft flange for easy connection and installation includes a first disc body and a boss. The boss is integrally formed on the upper end face of the first disc body. A central hole is formed in the middle of the boss and the first disc body. A connecting component is provided at the outer edge of the first disc body. A reinforcing rib is welded to the outer surface of the first disc body. A locking component is provided on the upper end face of the boss. A sealing groove is formed on the outer surface of the boss. A second disc body is provided above the first disc body. An annular groove adapted to the boss is formed in the middle of the second disc body. A connecting protrusion that fits and connects with the central hole is integrally formed in the middle of the second disc body. A second pin hole is formed at the outer edge of the second disc body. A connecting groove corresponding to the reinforcing rib is formed at the bottom of the second disc body. A positioning groove is formed in the middle of the second disc body. A sealing ring corresponding to the sealing groove is placed in the middle of the second disc body.

[0011] By adopting the above technical solution, the initial positioning is achieved through the precise matching of the boss and the annular groove of the second disc, and the connecting protrusion and the center hole. Then, the engagement component and the positioning groove are used to cooperate, and the connecting component and the second pin hole are used to complete the stable connection. At the same time, the sealing ring is embedded in the sealing groove to ensure the sealing of the connection. This makes the flange connection and installation of the aircraft convenient, efficient and accurate, enhances the connection strength and stability, and can also effectively prevent media leakage and ensure the normal operation of the aircraft.

[0012] Preferably, the connecting component includes a first pin hole, the inner wall of which is inlaid with reinforcing ribs.

[0013] The above technical solution involves setting a first pin hole on the first plate body to provide space for the pin to be inserted and fixed, thereby achieving initial connection and positioning between the flange and the corresponding component. A reinforcing rib is embedded in the inner wall of the first pin hole to enhance the structural strength of the pin hole. The first pin hole facilitates quick connection and installation, improving assembly efficiency. The reinforcing rib can prevent the pin hole from deforming and being damaged when the pin is inserted, ensuring connection stability and the service life of the flange.

[0014] Preferably, the first pin hole is provided in eight groups along the outer edge of the first disc body, the reinforcing ribs are in the form of a ring structure and are distributed at intervals along the axial direction of the first pin hole, and the thickness of the reinforcing ribs is designed to increase from top to bottom.

[0015] Using the above technical solution, eight sets of first pin holes are distributed in a ring around the outer edge of the first disc, which can be connected to the corresponding components from multiple directions to form a stable connection layout; the reinforcing ribs are distributed in a ring and axially spaced, and the thickness increases from top to bottom, which can gradually disperse the stress when the pin is inserted. The multiple sets of pin holes increase the number and distribution rationality of connection points and enhance the stability of the connection; the special design of the reinforcing ribs can effectively enhance the structural strength of the pin holes, prevent deformation and cracking, and extend the service life of the flange.

[0016] Preferably, the reinforcing rib has a triangular structure, with one side welded to the boss and the other side extending to the outer edge of the first disc. Eight sets of reinforcing ribs are arranged in a ring along the outer surface of the boss, and the reinforcing ribs are fitted and connected to the connecting grooves in a one-to-one correspondence.

[0017] Using the above technical solution, the triangular reinforcing rib has high stability. One side is connected to the boss, and the other side extends to the outer edge of the disc body, which can effectively transfer and distribute the force of the boss to the disc body. The eight sets of ring-shaped distribution and corresponding to the connecting grooves one by one can accurately position and enhance the overall structural synergy during connection, enhance the overall structural strength and rigidity of the flange, and improve its resistance to deformation and damage. The close connection with the connecting groove can increase the tightness and stability of the connection, ensuring the reliability of the flange connection during the use of the aircraft.

[0018] Preferably, the engaging assembly includes a positioning protrusion fixed to the upper surface of the boss, and an elastic buckle is fixed to the upper surface of the positioning protrusion.

[0019] Using the above technical solution, the positioning protrusion provides a stable installation base for the elastic buckle and determines its precise position on the protrusion; the elastic buckle deforms during the installation of the second disc due to its own elasticity, and returns to its original shape when it reaches the positioning groove to achieve engagement. The positioning protrusion ensures precise engagement and avoids misalignment during installation; the elastic buckle and the positioning groove cooperate to achieve a quick and stable connection between the first and second discs, enhancing the overall reliability of the flange connection.

[0020] Preferably, the positioning protrusion has a frustum-shaped structure, and four sets of positioning protrusions are arranged in a ring on the upper end face of the protrusion, and the elastic buckle extends to the outside of the positioning groove and engages with it.

[0021] Using the above technical solution, the frustum-shaped positioning protrusion utilizes its unique shape to achieve rapid positioning and guidance, and the four sets of ring-shaped distribution can accurately position the second disc from multiple directions; the elastic buckle extends to the outside of the positioning groove, and generates a rebound force by its own elastic deformation, tightly locking the positioning groove to achieve a stable connection. The frustum-shaped positioning protrusion and the four-set layout improve the accuracy and efficiency of installation and positioning; the engaging connection between the elastic buckle and the positioning groove enhances the firmness of the connection between the first disc and the second disc, preventing the flange from loosening during aircraft operation.

[0022] Compared with the prior art, the beneficial effects of this utility model are: the aircraft flange that is easy to connect and install,

[0023] 1. The first disc body and the boss are integrated and have a central hole. The second disc body has a corresponding annular groove and connecting protrusion in the center. During installation, the annular groove and the boss, and the connecting protrusion and the central hole are matched with each other, which can quickly achieve preliminary positioning and lay the foundation for subsequent precise connection. At the same time, eight sets of first pin holes are opened in the annular shape on the outer edge of the first disc body, and second pin holes are opened on the outer edge of the second disc body. The pins can be used to connect and fix the disc body from multiple directions, which further ensures the accuracy and stability of the connection, greatly facilitates the installation operation, and improves the installation efficiency.

[0024] 2. The reinforcing ribs embedded in the inner wall of the first pin hole are in the shape of a ring and are distributed at intervals along the axial direction. The thickness increases from top to bottom. This can effectively disperse the stress generated when the pin is inserted, enhance the structural strength of the pin hole, prevent its deformation and damage, and thus ensure the stability of the connection.

[0025] 3. A sealing groove is opened on the outer surface of the boss, and a corresponding sealing ring is placed in the middle of the second plate. During installation, the sealing ring is embedded in the sealing groove, which can effectively prevent the leakage of the medium and ensure the sealing performance of the flange, providing a reliable guarantee for the safe and stable operation of the aircraft.

[0026] 4. The positioning protrusion adopts a frustum-shaped structure with four sets of rings. When the second plate is installed, its shape, which is narrow at the top and wide at the bottom, can play a good guiding role and achieve rapid and accurate positioning. The elastic buckle on the upper end of the positioning protrusion is elastically deformed under pressure during installation. After reaching the positioning groove, it returns to its original shape and locks in place. This can effectively prevent the first plate and the second plate from loosening and separating due to vibration and other factors during the operation of the aircraft. This greatly enhances the stability and reliability of the connection between the two, and ensures the overall working performance of the flange and the safe operation of the aircraft.

[0027] 5. The reinforcing ribs on the outer surface of the first flange adopt a triangular structure. Utilizing the principle of triangular stability, one side is welded to the boss, and the other side extends to the outer edge of the first flange. Furthermore, eight sets of reinforcing ribs are distributed in a ring along the outer surface of the boss, which can effectively disperse and transfer the stress borne by the boss to the first flange body. This greatly enhances the structural strength and rigidity of the entire flange, making it less prone to deformation or damage when subjected to various complex external forces during aircraft operation, thus ensuring the service life and reliability of the flange. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the external structure of the main body of this utility model;

[0029] Figure 2 This is a schematic diagram of the first disc body structure of this utility model;

[0030] Figure 3 This is a schematic diagram of the corresponding connection structure of the second disc body of this utility model;

[0031] Figure 4 This is a schematic diagram of the structural composition of the connecting component of this utility model;

[0032] Figure 5 This is a schematic diagram of the structural composition of the snap-fit ​​assembly of this utility model.

[0033] In the figure: 1. First disc body; 2. Boss; 3. Center hole; 4. Connecting assembly; 401. First pin hole; 402. Reinforcing rib; 5. Reinforcing rib plate; 6. Engaging assembly; 601. Positioning protrusion; 602. Elastic buckle; 7. Sealing groove; 8. Second disc body; 9. Annular groove; 10. Connecting protrusion; 11. Second pin hole; 12. Connecting groove; 13. Positioning groove; 14. Sealing ring. Detailed Implementation

[0034] 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.

[0035] Example 1

[0036] Please see Figures 1-4 This utility model provides a technical solution:

[0037] An aircraft flange for easy connection and installation includes a first disc body 1 and a boss 2. The boss 2 is integrally formed on the upper end face of the first disc body 1. A central hole 3 is formed in the middle of the boss 2 and the first disc body 1. A connecting component 4 is provided at the outer edge of the first disc body 1. A second disc body 8 is provided above the first disc body 1. An annular groove 9 that matches the boss 2 is formed in the middle of the second disc body 8. A connecting protrusion 10 that fits and connects with the central hole 3 is integrally formed in the middle of the second disc body 8. A second pin hole 11 is formed at the outer edge of the second disc body 8. The connecting component 4 includes a first pin hole 401. A reinforcing rib 402 is embedded in the inner wall of the first pin hole 401. Eight sets of first pin holes 401 are formed annularly along the outer edge of the first disc body 1. The reinforcing ribs 402 are in annular structure and are distributed axially at intervals along the first pin holes 401. The thickness of the reinforcing ribs 402 increases from top to bottom.

[0038] This aircraft flange, designed for easy connection and installation, features an integrated boss 2 on the upper end of the first disc body 1, with a central hole 3 in the middle to provide a channel for fluid and other transmission. Eight sets of first pin holes 401 are arranged in a ring around the outer edge of the first disc body 1, facilitating quick connection with components such as the second disc body 8 from multiple directions via pins, achieving initial positioning and fixation. The inner wall of the first pin holes 401 is inlaid with reinforcing ribs 402 in a ring structure, spaced axially and with increasing thickness from top to bottom, which progressively disperses stress during pin insertion, enhancing the structural strength of the pin holes and preventing deformation and damage. The second disc body 8 has an annular groove 9 that matches the boss 2 and a connecting protrusion 10 that fits the central hole 3 in the middle, achieving precise positioning and tight connection. Second pin holes 11 are opened on the outer edge of the second disc body 8, cooperating with the first pin holes 401 to further reinforce the connection via pins. Overall, this design improves the convenience, stability, and reliability of the flange connection and installation, ensuring the normal operation of the aircraft.

[0039] Example 2

[0040] Please see Figure 2 , Figure 3 This utility model provides a technical solution:

[0041] A reinforcing rib 5 is welded to the outer surface of the first disc 1. A sealing groove 7 is formed on the outer surface of the boss 2. A connecting groove 12 corresponding to the reinforcing rib 5 is formed at the bottom of the second disc 8. A sealing ring 14 corresponding to the sealing groove 7 is placed in the middle of the second disc 8. The reinforcing rib 5 has a triangular structure, with one side welded to the boss 2 and the other side extending to the outer edge of the first disc 1. Eight sets of reinforcing ribs 5 are arranged in a ring along the outer surface of the boss 2, and the reinforcing ribs 5 are fitted and connected to the connecting groove 12 in a one-to-one correspondence.

[0042] This aircraft flange, which is easy to connect and install, features a triangular structure for the reinforcing ribs 5 welded to the outer surface of the first disc body 1. Utilizing the principle of triangular stability, one side is welded to the boss 2, while the other side extends to the outer edge of the first disc body 1. Eight sets of these ribs are distributed in a ring along the outer surface of the boss 2, effectively distributing and transferring the stress on the boss 2 to the first disc body 1, enhancing the overall structural strength and rigidity, and preventing deformation. The sealing groove 7 on the outer surface of the boss 2 corresponds to the sealing ring 14 in the middle of the second disc body 8. During installation, the sealing ring 14 is embedded in the sealing groove 7, effectively preventing media leakage and ensuring sealing. The connecting groove 12 at the bottom of the second disc body 8, corresponding to the reinforcing ribs 5, fits one-to-one with the reinforcing ribs 5 during connection, further enhancing the tightness of the connection and assisting in positioning. This ensures an accurate and stable connection between the first disc body 1 and the second disc body 8, meeting the requirements for aircraft use.

[0043] Example 3

[0044] Please see Figure 1 , Figure 2, Figure 5 This utility model provides a technical solution:

[0045] A locking component 6 is provided on the upper end face of the boss 2. A positioning groove 13 is provided in the middle of the second disc body 8. The locking component 6 includes a positioning protrusion 601 fixed to the upper end face of the boss 2, and an elastic buckle 602 is fixed on the upper end face of the positioning protrusion 601. The positioning protrusion 601 has a frustum-shaped structure, and four sets of positioning protrusions 601 are arranged in a ring on the upper end face of the boss 2. The elastic buckle 602 extends to the outside of the positioning groove 13 and engages with it.

[0046] This aircraft flange, designed for easy connection and installation, features a truncated cone-shaped positioning protrusion 601 within the engagement assembly 6 on the upper surface of the boss 2. The protrusion's narrower-than-wider shape guides the second plate 8 during installation, facilitating rapid positioning. Four sets of positioning protrusions 601 are arranged in a ring on the upper surface of the boss 2, allowing for positioning of the second plate 8 from multiple angles and enhancing connection accuracy. The elastic buckle 602 fixed to the upper surface of the positioning protrusion 601 undergoes elastic deformation under pressure during the installation of the second plate 8. When it reaches the positioning groove 13 in the middle of the second plate 8, the elastic buckle 602 returns to its original shape and extends to engage with the outside of the positioning groove 13, achieving a stable connection between the first plate 1 and the second plate 8. This prevents loosening and separation during aircraft operation, ensuring the reliability of the flange connection.

[0047] Working principle:

[0048] In use, when connecting the first disc 1 and the second disc 8, the annular groove 9 of the second disc 8 is first aligned with the boss 2 of the first disc 1, and the connecting protrusion 10 fits into the center hole 3 to achieve initial positioning. At this time, the four sets of frustum-shaped positioning protrusions 601 on the upper end face of the boss 2 use their narrow upper and wide lower shape to guide the second disc 8 to quickly find the correct position. At the same time, the elastic buckle 602 is deformed by compression and returns to its original shape after reaching the positioning groove 13 to lock in the connection and prevent loosening. Next, the pin is inserted into the eight sets of first pin holes 401 with reinforcing ribs 402 on the outer edge of the first disc 1 and the second pin holes 11 on the outer edge of the second disc 8 for further reinforcement. At the same time, the eight sets of triangular reinforcing ribs 5 on the outer surface of the first disc 1 fit into the connecting groove 12 at the bottom of the second disc 8 to distribute stress and enhance the tightness of the connection. Finally, the sealing ring 14 is embedded in the sealing groove 7 on the outer surface of the boss 2 to prevent media leakage and ensure reliable flange connection and normal operation of the aircraft.

[0049] The contents not described in detail in this specification are existing technologies known to those skilled in the art.

[0050] 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. An aircraft flange that is easy to connect and install, comprising a first flange body (1) and a boss (2), characterized in that: A boss (2) is integrally provided on the upper end face of the first disc body (1). A central hole (3) is provided in the middle of the boss (2) and the first disc body (1). A connecting component (4) is provided at the outer edge of the first disc body (1). A reinforcing rib (5) is welded on the outer surface of the first disc body (1). A locking component (6) is provided on the upper end face of the boss (2). A sealing groove (7) is provided on the outer surface of the boss (2). A second disc body (8) is provided above the first disc body (1). The middle of the second disc body (8) An annular groove (9) adapted to the boss (2) is provided. A connecting protrusion (10) that fits and connects with the central hole (3) is integrally provided in the middle of the second disc (8). A second pin hole (11) is provided at the outer edge of the second disc (8). A connecting groove (12) corresponding to the reinforcing rib (5) is provided at the bottom of the second disc (8). A positioning groove (13) is provided in the middle of the second disc (8). A sealing ring (14) corresponding to the sealing groove (7) is placed in the middle of the second disc (8).

2. The aircraft flange for easy connection and installation according to claim 1, characterized in that: The connecting component (4) includes a first pin hole (401), and the inner wall of the first pin hole (401) is inlaid with a reinforcing rib (402).

3. The aircraft flange for easy connection and installation according to claim 2, characterized in that: The first pin hole (401) is provided with eight sets of rings along the outer edge of the first disc body (1). The reinforcing ribs (402) are in the form of rings and are distributed axially along the first pin hole (401). The thickness of the reinforcing ribs (402) is designed to increase from top to bottom.

4. The aircraft flange for easy connection and installation according to claim 1, characterized in that: The reinforcing rib (5) has a triangular structure, with one side welded to the boss (2) and the other side extending to the outer edge of the first disc (1). The reinforcing rib (5) is arranged in eight sets along the outer surface of the boss (2), and the reinforcing rib (5) and the connecting groove (12) are connected in a one-to-one correspondence.

5. The aircraft flange for easy connection and installation according to claim 1, characterized in that: The engaging assembly (6) includes a positioning protrusion (601) fixed to the upper surface of the boss (2), and an elastic buckle (602) is fixed to the upper surface of the positioning protrusion (601).

6. The aircraft flange for easy connection and installation according to claim 5, characterized in that: The positioning protrusion (601) is a frustum-shaped structure, and four sets of positioning protrusions (601) are arranged in a ring on the upper end face of the protrusion (2), and the elastic buckle (602) extends to the outside of the positioning groove (13) and engages with it.

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