Quick connection structure of aviation metal pipe

Abstract

The utility model relates to aviation metal pipe connecting technical field, and disclose a kind of aviation metal pipe quick connection structure, including connecting piece and fastener, connecting piece is hollow sleeve and the sleeve ring located at sleeve outer portion, sleeve ring and sleeve form annular slot, and sealing abutment is equipped in slot;The outer wall of both ends of sleeve is provided with annular groove, and the first rubber airbag ring with built-in natural outer diameter greater than sleeve is arranged.The sealing abutment includes the second rubber airbag ring, and the sliding slot and sliding block are arranged at the corresponding position of sleeve outer wall.The fastener is composed of fixed half ring, movable half ring, U-shaped limiting block, shaft, limiting threaded column and threaded dish cap, and the metal pipe can be driven to contract and lock by half ring to the shaft center.The structure realizes the quick assembly and disassembly of aviation metal pipe, and has excellent double sealing performance, vibration resistance, high and low temperature resistance, and is suitable for aviation harsh environment, reduces maintenance cost and ensures flight safety.

Description

Technical Field

[0001] This utility model relates to the field of aviation metal tube connection technology, specifically to a quick connection structure for aviation metal tubes. Background Technology

[0002] In the aerospace field, titanium alloy tubes and aluminum alloy tubes are widely used as key components for fluid transport and structural support in core applications such as engine hydraulic systems, fuselage fuel lines, and cooling circulation systems. The reliability and efficiency of their connections directly affect aircraft assembly progress, maintenance convenience, and flight safety. Therefore, the connection structure must simultaneously meet the requirements of high strength, vibration resistance, resistance to high and low temperatures, and resistance to corrosion from complex media, as well as the demands for convenient and rapid connection in aerospace scenarios.

[0003] However, the current mainstream connection methods for aerospace metal tubes have significant technical limitations, making it difficult to balance reliability and the need for rapid connection. Specific problems include: 1. Threaded connections are inefficient and costly to maintain. Currently, most titanium alloy and aluminum alloy pipes use threaded connections with sealant, requiring pre-designed thread structures and strict control of tightening torque to ensure sealing and strength. This method involves cumbersome assembly steps, hindering batch assembly and emergency maintenance efficiency. Furthermore, the high hardness of titanium alloy pipes makes thread processing difficult and costly. After long-term service, threads are prone to loosening due to vibration, requiring periodic disassembly, inspection, and tightening, further increasing maintenance costs and downtime.

[0004] 2. Welded connections suffer from poor adaptability and maintenance difficulties. For high-pressure pipelines, existing technologies often employ fixed connection methods such as argon arc welding and laser welding. While these methods ensure strength and sealing, they require professional operation and are subject to harsh environmental conditions, making them unsuitable for field maintenance or emergency repairs. Furthermore, welding results in non-detachable connections; pipeline damage or component replacement necessitates cutting and re-welding, easily causing secondary damage to the pipe body. Subsequent flaw detection is also required, leading to long maintenance cycles and high costs, making it difficult to meet the need for rapid restoration of service. 3. Existing quick couplings suffer from insufficient sealing performance. Current quick couplings mostly achieve connection through external clamps, resulting in poor sealing performance and failing to meet the sealing requirements of aerospace metal pipes.

[0005] To address these issues, we propose a quick-connect structure for aerospace metal tubes. Utility Model Content

[0006] The purpose of this utility model is to provide a quick connection structure for aerospace metal tubes to solve the problems mentioned in the background art, such as low efficiency and high maintenance cost of threaded connections; poor adaptability and difficult maintenance of welded connections; and insufficient sealing performance of existing quick connectors.

[0007] This utility model provides the following technical solution: A quick-connect structure for aviation metal tubes includes a connector for coaxial quick connection of two metal tubes. The connector includes a hollow sleeve and an integral ring fitted around the outer wall of the middle part of the sleeve. Fasteners for locking the aviation metal tubes are provided on the outer periphery of the ring. The inner walls at both ends of the collar and the corresponding outer walls of the sleeve respectively form annular slots for inserting aviation metal tubes. Each annular slot has a sealing abutment. When the end of the aviation metal tube is coaxially inserted into the annular slot, the outer wall of the sleeve and the inner wall of the aviation metal tube are in close contact, and the inner wall of the collar and the outer wall of the aviation metal tube are in close contact. Annular grooves are respectively formed on the outer walls of the sleeve near both ends. A first rubber airbag ring is embedded and fixed in each annular groove. The natural outer diameter of the first rubber airbag ring is larger than the outer diameter of the sleeve, and the outer peripheral wall of the first rubber airbag ring slides against the inner wall of the aviation metal tube.

[0008] Preferably, the sealing abutment includes a second rubber airbag ring, which is coaxially sleeved on the outer wall of the sleeve and located in the groove of the annular slot; at least two sliding grooves are evenly opened circumferentially on the outer wall of the sleeve on the side of the second rubber airbag ring near the middle of the sleeve, and a slider is slidably embedded in each of the sliding grooves; the outer peripheral wall of the slider is fixedly connected to the inner side wall of the second rubber airbag ring to restrict the second rubber airbag ring from coming out along the axial direction of the sleeve; the top of the slider is flush with the outer wall of the sleeve, and when the aviation metal tube is inserted into the annular slot, the end of the aviation metal tube squeezes the second rubber airbag ring, causing the second rubber airbag ring to expand toward the groove wall of the annular slot and tightly abut against it to form a seal.

[0009] Preferably, the fastener includes a fixed half-ring and a movable half-ring, one end of the fixed half-ring and one end of the movable half-ring are rotatably connected by a rotating shaft; the outer peripheral wall of the collar is fixedly fitted with the inner peripheral wall of the fixed half-ring, and the groove diameter of the annular slot is the same as the inner peripheral diameter of the fixed half-ring; when the aviation metal tube is inserted into the annular slot, the inner peripheral wall of the fixed half-ring and the inner peripheral wall of the movable half-ring together abut against the outer peripheral wall of the aviation metal tube.

[0010] Preferably, both the end of the fixed half-ring away from the rotating shaft and the end of the movable half-ring away from the rotating shaft are integrally formed with U-shaped limiting blocks; inside the U-shaped limiting block on the fixed half-ring, a shaft is rotatably connected by a bearing, and a limiting threaded post that is adapted to and engages with the U-shaped limiting block is fixedly sleeved on the outer periphery of the shaft; The limiting threaded post is threaded with a threaded disc cap for locking the U-shaped limiting block. When the threaded disc cap is tightened, the fixed half ring and the movable half ring can be driven to retract towards the axis.

[0011] Preferably, the sleeve is made of titanium alloy, the collar is made of aerospace-grade aluminum alloy, and the collar and sleeve are fixed by laser welding.

[0012] Preferably, a metal support mesh is embedded inside the second rubber airbag ring. The metal support mesh is made of 304 stainless steel and is used to prevent the second rubber airbag ring from being excessively squeezed and deformed.

[0013] This utility model has the following beneficial effects: 1. This application utilizes a combination structure of sleeve, collar, and fastener. The connection can be completed simply by inserting two aerospace metal tubes coaxially into the annular slot, closing the movable half-ring of the fastener, and tightening the threaded disc cap. The entire process requires no pre-setting of threads, welding, or complex tools, which improves efficiency compared to traditional threaded connections and effectively solves the problem of low efficiency during batch assembly. At the same time, this structure does not require professional welding personnel or precise torque control, and can be operated by ordinary maintenance personnel. It is fully adaptable to scenarios such as temporary field repairs and emergency maintenance, avoiding maintenance delays caused by high operational thresholds.

[0014] 2. Compared with traditional threaded connections that require high-precision thread machining of titanium alloy tubes, this application only requires quick connection of the end of the aerospace metal tube, which greatly reduces the difficulty and cost of tube processing, and is especially suitable for difficult-to-machine aerospace materials such as titanium alloys and high-strength aluminum alloys.

[0015] 3. This application designs a dual sealing system of a first rubber airbag ring and a second rubber airbag ring, which significantly improves sealing reliability compared to ordinary clamp-type quick couplings and fully meets the stringent requirements of the aviation field for fluid transportation sealing. Attached Figure Description

[0016] Figure 1 This is an isometric view of the overall structure of this utility model.

[0017] Figure 2 This is an isometric view of the overall connection structure of the connector and fastener of this utility model.

[0018] Figure 3 This is a schematic diagram of the connection structure between the fixed half-ring and the connector of this utility model.

[0019] Figure 4 This is a side view of the present invention.

[0020] Figure 5 This is a side view of the metal tube and connector of this utility model.

[0021] In the diagram: 1. Metal tube; 2. Connector; 21. Sleeve; 211. Annular groove; 212. First rubber airbag ring; 22. Collar; 23. Annular slot; 231. Slide groove; 232. Slider; 24. Sealing abutment; 241. Second rubber airbag ring; 3. Fastener; 31. Fixed half ring; 32. Movable half ring; 33. U-shaped limit block; 331. Shaft; 332. Limiting threaded post; 333. Threaded disc cap. 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] Please see Figure 1 , Figure 3 - Figure 5 A quick-connect structure for aviation metal tubes includes a connector 2 for coaxial quick connection of two metal tubes 1. The connector 2 includes a hollow sleeve 21 and an integral collar 22 that fits around the outer wall of the middle part of the sleeve 21. The sleeve 21 is made of titanium alloy and has a hollow structure. Titanium alloy has high strength, high corrosion resistance and excellent high and low temperature resistance, which can be adapted to the complex and harsh operating environment in the aviation field and ensure the long-term stability of the connection structure. The hollow design of the sleeve 21 can ensure smooth fluid transport in the metal tube 1 without additional flow resistance. The collar 22 is fixed to the sleeve 21 by laser welding. The inner walls of both ends of the collar 22 and the corresponding outer walls of the sleeve 21 respectively form annular slots 23 for inserting the aviation metal tube 1. The size of the annular slots 23 is adapted to the outer diameter and wall thickness of the metal tube 1 to ensure accurate positioning after the metal tube 1 is inserted and to ensure coaxiality.

[0024] When the end of the aviation metal tube 1 is coaxially inserted into the annular slot 23, the outer wall of the sleeve 21 is in close contact with the inner wall of the aviation metal tube 1, and the inner wall of the collar 22 is in close contact with the outer wall of the aviation metal tube 1. Annular grooves 211 are respectively formed on the outer wall of the sleeve 21 near both ends. A first rubber airbag ring 212 is embedded and fixed in each annular groove 211. The first rubber airbag ring 212 is made of highly elastic, oil-resistant, and high / low temperature resistant rubber material. The natural outer diameter is larger than the outer diameter of the sleeve 21, and the outer peripheral wall of the first rubber airbag ring 212 slides against the inner wall of the aviation metal tube 1. When the end of the metal tube 1 is coaxially inserted into the annular slot 23, the outer peripheral wall of the first rubber airbag ring 212 slides against the inner wall of the metal tube 1. Due to the larger natural outer diameter, the first rubber airbag ring 212 will be squeezed by the inner wall of the metal tube 1 and undergo elastic deformation, tightly fitting the inner wall of the metal tube 1 and the outer wall of the sleeve 21, forming the first sealing defense line.

[0025] Each annular slot 23 is provided with a sealing abutment 24 in its cavity to achieve a seal between the metal tube 1 and the connector 2. The sealing abutment 24 includes a second rubber airbag ring 241, which is made of highly elastic, oil-resistant, and high and low temperature resistant rubber material. A metal support mesh of 304 stainless steel is embedded inside it. The metal support mesh can effectively limit the deformation of the second rubber airbag ring 241 under pressure, prevent it from being permanently deformed or damaged due to excessive compression, extend the service life of the sealing component, and ensure the stability of the sealing performance. The second rubber airbag ring 241 is coaxially sleeved on the outer wall of the sleeve 21 and located in the groove of the annular slot 23. At least two sliding grooves 231 are evenly opened circumferentially on the outer wall of the sleeve 21 on the side of the second rubber airbag ring 241 near the middle of the collar 22. A slider 232 is slidably embedded in each sliding groove 231. The outer peripheral wall of the slider 232 is fixedly connected to the inner side wall of the second rubber airbag ring 241 to restrict the second rubber airbag ring 241 from detaching axially along the sleeve 21. The top of the slider 232 is flush with the outer wall of the sleeve 21 to avoid the slider 232 from obstructing the insertion of the metal tube 1 and to ensure that the metal tube 1 can be smoothly inserted into the annular slot 23. When the aviation metal tube 1 is inserted into the annular slot 23, the end of the aviation metal tube 1 squeezes the second rubber airbag ring 241, causing the second rubber airbag ring 241 to expand towards the groove wall of the annular slot 23 and tightly abut against it to form a seal.

[0026] When the end of the aviation metal tube 1 is coaxially inserted into the annular slot 23, the outer wall of the sleeve 21 abuts tightly against the inner wall of the metal tube 1, and the inner wall of the collar 22 abuts tightly against the outer wall of the metal tube 1, achieving the initial positioning and support of the metal tube 1; at the same time, the end of the metal tube 1 will squeeze the second rubber airbag ring 241, causing the second rubber airbag ring 241 to expand and abut tightly against the groove wall of the annular slot 23 (i.e., the inner wall of the collar 22 and the outer wall of the sleeve 21), forming a second sealing line, which works with the first rubber airbag ring 212 to achieve double sealing and greatly improve the sealing performance.

[0027] Please see Figure 1 - Figure 4 The outer periphery of the collar 22 is provided with a fastener 3 for locking the aviation metal tube 1. This fastener locks the aviation metal tube 1 inserted into the annular slot 23, preventing it from loosening or coming out under vibration or external force. The fastener 3 includes a fixed half-ring 31 and a movable half-ring 32. One end of the fixed half-ring 31 and one end of the movable half-ring 32 are rotatably connected by a pivot. This rotatable connection allows the movable half-ring 32 to open and close, facilitating quick closure and locking after the metal tube 1 is inserted, making operation convenient. The outer periphery of the collar 22 is fixedly fitted with the inner periphery of the fixed half-ring 31. The diameter of the slot of the annular slot 23 is the same as the inner periphery diameter of the fixed half-ring 31. When the aviation metal tube 1 is inserted into the annular slot 23, the inner periphery of the fixed half-ring 31 and the inner periphery of the movable half-ring 32 together abut against the outer periphery of the aviation metal tube 1, achieving uniform clamping of the outer periphery of the metal tube 1.

[0028] Both the fixed half-ring 31 and the movable half-ring 32, which are away from the rotating shaft, are integrally formed with U-shaped limiting blocks 33. Inside the U-shaped limiting block 33 on the fixed half-ring 31, a shaft 331 is rotatably connected via a bearing. The outer periphery of the shaft 331 is fixedly fitted with a limiting threaded post 332 that is adapted to and engages with the U-shaped limiting block 33. A threaded cap 333 for locking the U-shaped limiting block 33 is threaded on the limiting threaded post 332. When the threaded cap 333 is tightened, the fixed half-ring 31 and the movable half-ring 32 can be driven to retract toward the axis.

[0029] After the movable half ring 32 is closed, rotate the limiting threaded post 332 so that it is engaged in the U-shaped limiting block 33 of the movable half ring 32. Then tighten the threaded disc cap 333. The threaded disc cap 333 will apply axial pressure to the U-shaped limiting block 33, driving the fixed half ring 31 and the movable half ring 32 to retract towards the axis, further enhancing the clamping force on the outer periphery of the metal tube 1, ensuring the stability of the metal tube 1 connection, and effectively resisting vibration and impact.

[0030] Working principle: With the movable half-ring 32 in the open state, align the ends of the two metal tubes 1 with the annular slots 23 at both ends of the connector 2, and slowly insert them along the axial direction of the sleeve 21. During the insertion process, the inner wall of the metal tube 1 will contact the first rubber airbag ring 212 on the outer wall of the sleeve 21. Since the outer diameter of the first rubber airbag ring 212 is naturally larger than the outer diameter of the sleeve 21, it will be squeezed by the inner wall of the metal tube 1 to produce elastic deformation, tightly fitting the inner wall of the metal tube 1 and the outer wall of the sleeve 21, initially forming a seal. Continue to insert the metal tube 1 until its end contacts the second rubber airbag ring 241 in the annular slot 23 and is squeezed. The end of the metal tube 1 continuously squeezes the second rubber airbag ring 241, forcing the second rubber airbag ring 241 to expand towards the groove wall of the annular slot 23 (the inner wall of the collar 22 and the outer wall of the sleeve 21) until the second rubber airbag ring 241 tightly fits the groove wall, forming a second seal; at the same time, the slider 232 slides slightly in the groove 231 with the expansion of the second rubber airbag ring 241, restricting its axial disengagement and ensuring the stability of the double sealing structure. Rotate the movable half-ring 32 to close it around the axis. At this time, the inner circumferential walls of both the fixed half-ring 31 and the movable half-ring 32 are in contact with the outer circumferential wall of the metal tube 1. Rotate the shaft 331 inside the U-shaped limiting block 33 on the fixed half-ring 31 to drive the limiting threaded column 332 to rotate, so that it is engaged in the U-shaped limiting block 33 of the movable half-ring 32, thus achieving the initial positioning of the half-ring. Then, use a tool to tighten the threaded disc cap 333. The threaded disc cap 333 applies axial pressure to the U-shaped limiting block 33 through the threaded engagement with the limiting threaded column 332, driving the fixed half-ring 31 and the movable half-ring 32 to contract towards the axis, so that the inner circumferential wall of the half-ring is tightly abutted against the outer circumferential wall of the metal tube 1, generating a uniform clamping force, and firmly locking the metal tube 1 in the annular slot 23 to prevent it from loosening and falling out under vibration or external force.

[0031] The first rubber airbag ring 212 and the second rubber airbag ring 241 of this application can compensate for the slight displacement of the metal tube 1 caused by temperature changes (thermal expansion and contraction) or vibration through their own elastic deformation, and maintain a tight fit with the tube body and groove wall to ensure that the sealing performance does not decrease. The semi-circular contraction structure of the fastener 3 can provide a continuous and stable clamping force to resist vibration and impact, prevent the metal tube 1 from axial or radial displacement, and ensure the overall stability of the connection structure. When disassembly and maintenance are required, simply loosen the threaded disc cap 333, rotate the limiting threaded post 332 to disengage it from the U-shaped limiting block 33 of the movable semi-ring 32, open the movable semi-ring 32, and the metal tube 1 can be pulled out from the annular slot 23. The operation is convenient, greatly shortens the maintenance time, and reduces the maintenance cost.

[0032] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, 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 process, method, article, or apparatus.

[0033] The above description is only a preferred embodiment of the present utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present utility model, and these improvements and modifications should also be considered within the protection scope of the present utility model.

Claims

1. A quick-connect structure for aerospace metal tubes, comprising a connector (2) for coaxial quick connection of two metal tubes (1), characterized in that: The connector (2) includes a hollow sleeve (21) and an integral collar (22) that is fitted around the outer wall of the middle part of the sleeve (21). The outer periphery of the collar (22) is provided with fasteners (3) for locking the aviation metal tube (1). The inner walls of the two ends of the collar (22) and the corresponding outer walls of the sleeve (21) respectively form annular slots (23) for inserting the aviation metal tube (1). Each annular slot (23) is provided with a sealing abutment (24). When the end of the aviation metal tube (1) is coaxially inserted into the annular slot (23), the outer wall of the sleeve (21) is in close contact with the inner wall of the aviation metal tube (1), and the inner wall of the collar (22) is in close contact with the outer wall of the aviation metal tube (1). Annular grooves (211) are respectively opened on the outer walls of the sleeve (21) near both ends. A first rubber airbag ring (212) is embedded and fixed in each annular groove (211). The natural outer diameter of the first rubber airbag ring (212) is larger than the outer diameter of the sleeve (21), and the outer peripheral wall of the first rubber airbag ring (212) slides against the inner wall of the aviation metal tube (1).

2. The quick-connect structure for aerospace metal tubes according to claim 1, characterized in that: The sealing contact (24) includes a second rubber airbag ring (241), which is coaxially sleeved on the outer wall of the sleeve (21) and located in the groove of the annular slot (23); on the outer wall of the sleeve (21) near the middle of the collar (22) of the second rubber airbag ring (241), at least two sliding grooves (231) are evenly opened in the circumferential direction, and a slider (232) is slidably embedded in each of the sliding grooves (231); the slider (232) The outer peripheral wall is fixedly connected to the inner side wall of the second rubber airbag ring (241) to restrict the second rubber airbag ring (241) from detaching along the sleeve (21) axially; the top of the slider (232) is flush with the outer wall of the sleeve (21). When the aviation metal tube (1) is inserted into the annular slot (23), the end of the aviation metal tube (1) squeezes the second rubber airbag ring (241), causing the second rubber airbag ring (241) to expand toward the groove wall of the annular slot (23) and fit tightly to form a seal.

3. The quick-connect structure for aerospace metal tubes according to claim 1, characterized in that: The fastener (3) includes a fixed half-ring (31) and a movable half-ring (32). One end of the fixed half-ring (31) and one end of the movable half-ring (32) are rotatably connected by a rotating shaft. The outer peripheral wall of the collar (22) is fixedly fitted and connected to the inner peripheral wall of the fixed half-ring (31). The groove diameter of the annular slot (23) is consistent with the inner peripheral diameter of the fixed half-ring (31). When the aviation metal tube (1) is inserted into the annular slot (23), the inner peripheral wall of the fixed half-ring (31) and the inner peripheral wall of the movable half-ring (32) are tightly abutted against the outer peripheral wall of the aviation metal tube (1).

4. The quick-connect structure for aerospace metal tubes according to claim 3, characterized in that: The fixed half-ring (31) and the movable half-ring (32) both have U-shaped limiting blocks (33) integrally formed at the ends away from the rotating shaft. Inside the U-shaped limiting blocks (33) on the fixed half-ring (31), a shaft (331) is rotatably connected by a bearing. The outer periphery of the shaft (331) is fixedly fitted with a limiting threaded post (332) that is adapted to and engages with the U-shaped limiting blocks (33). The limiting threaded post (332) is threaded with a threaded disc cap (333) for locking the U-shaped limiting block (33). When the threaded disc cap (333) is tightened, the fixed half ring (31) and the movable half ring (32) can be driven to retract towards the axis.

5. The quick-connect structure for aerospace metal tubes according to claim 1, characterized in that: The sleeve (21) is made of titanium alloy, and the collar (22) is made of aerospace-grade aluminum alloy. The collar (22) and the sleeve (21) are fixed by laser welding.

6. The quick-connect structure for aerospace metal tubes according to claim 2, characterized in that: The second rubber airbag ring (241) is internally embedded with a metal support mesh made of 304 stainless steel, which is used to prevent the second rubber airbag ring (241) from being excessively squeezed and deformed.

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