An aircraft ground liquid cooling connection device

Abstract

The application belongs to the field of aircraft structure design, and particularly relates to an aircraft ground liquid cooling connecting device. The connecting device comprises a receiving cavity arranged in the inside of a butt joint sleeve, the butt joint sleeve comprises a first butt joint section and a second butt joint section, and the first butt joint section is connected with a liquid cooling seat; a connecting body is arranged in the receiving cavity, a sliding block is arranged on the side wall of the connecting body and is slidingly installed in a sliding groove of the connecting body, a fluid passage is arranged in the inside of the connecting body, a first interface and a second interface which are in communication with the fluid passage are respectively arranged at the two ends of the connecting body, and a conversion joint connected with a ground liquid cooling hose is arranged on the second interface; an inner core is arranged in the fluid passage, and the inner core comprises a first inner core section and a second inner core section which are both in T shape. The application is inserted into the sleeve of the liquid cooling seat on the aircraft and is fixed without additional force, the butt joint interface connected with the ground liquid cooling hose is vertically downward, and the hose is not bent; a handle is pushed to establish a flow passage, and is locked in place, thereby saving labor and being reliable.

Description

Technical Field

[0001] This application belongs to the field of aircraft structural design, and specifically relates to an aircraft ground liquid cooling connection device. Background Technology

[0002] Aircraft ground liquid cooling interfaces are crucial connection devices that link ground equipment to the aircraft's liquid cooling mounts. With the increasing demand for aircraft liquid cooling in recent years, the traditional connector-based method is no longer sufficient to meet the needs of aircraft maintenance personnel.

[0003] Currently, the liquid cooling mount installed on the aircraft is the TSA-20Z. Its matching liquid cooling connector is large and has poor ergonomics. In practical applications, it can only be operated with both hands, requiring significant force. The liquid cooling hoses are also frequently bent and coiled, and connection and disconnection are time-consuming.

[0004] Therefore, it is desirable to have a technical solution to overcome or at least mitigate one of the aforementioned defects of the prior art. Summary of the Invention

[0005] The purpose of this application is to provide an aircraft ground liquid cooling connection device to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] An aircraft ground liquid cooling connection device, comprising:

[0008] A docking sleeve, the interior of which is provided with a receiving cavity, the docking sleeve includes a first docking section and a second docking section, the first docking section is connected to a liquid cooling base, the side wall of the second docking section is provided with a connecting body sliding groove, and the bottom of the second docking section is provided with an opening;

[0009] A connector is disposed in the receiving cavity. A sliding block is provided on the side wall of the connector. The sliding block is slidably installed in the sliding groove of the connector. A fluid channel is provided inside the connector. A first interface and a second interface communicating with the fluid channel are respectively opened at both ends of the connector. A conversion connector is installed at the second interface. The conversion connector passes through the opening at the bottom of the second docking section and is connected to the ground liquid cooling hose.

[0010] The inner core is disposed in the fluid channel. The inner core includes a first inner core segment and a second inner core segment, both of which are T-shaped. The first inner core segment includes a first limiting part and a first straight rod part. The second inner core segment includes a second limiting part and a second straight rod part. The second straight rod part is fixedly connected to the connecting body. A cavity is provided inside the second straight rod part. An opening communicating with the cavity is provided on the second limiting part. The first straight rod part passes through the opening on the second limiting part and is nested in the cavity. A spring is sleeved on the first straight rod part. The two ends of the spring abut against the first limiting part and the second limiting part, respectively. The first limiting part is adapted to the inner wall surface of the first interface.

[0011] When the connector slides to the connection position, the bolt passes through the opening on the first mating section and abuts against the connector, thereby limiting the connector to the connection position.

[0012] In at least one embodiment of this application, a single-handed grip is also included, the single-handed grip being connected to the second docking segment.

[0013] In at least one embodiment of this application, a crank-slider mechanism is further included, the crank-slider mechanism comprising a connecting rod, a spring, and a locking pin, wherein...

[0014] The linkage includes a first linkage and a second linkage.

[0015] The first end of the first connecting rod is hinged to the single-hand grip, and the second end of the first connecting rod has two locking slots.

[0016] The second connecting rod is L-shaped, with its first end hinged to the sliding block and its middle part hinged to the second end of the first connecting rod.

[0017] The first end of the spring is fixedly connected to the second end of the second connecting rod;

[0018] The locking pin is fixedly installed at the second end of the spring piece, and the locking pin can be engaged in the upper locking slot.

[0019] In at least one embodiment of this application, the crank-slider mechanism further includes an unlocking button mounted on the second connecting rod. Pressing the unlocking button pushes the spring plate to disengage the locking pin from the locking slot.

[0020] In at least one embodiment of this application, the first mating section of the mating sleeve is provided with an anti-detachment groove for matching with the liquid cooling seat.

[0021] In at least one embodiment of this application, the connecting body is provided with a threaded connection portion inside, the second straight rod portion is provided with an external thread section, and the second straight rod portion is fixed to the threaded connection portion by threads.

[0022] In at least one embodiment of this application, a rubber sealing ring is provided on the side wall of the first limiting part, and the rubber sealing ring is used to cooperate with the inner wall surface of the first interface to achieve a seal.

[0023] In at least one embodiment of this application, two rubber sealing rings are arranged in parallel on the side wall of the first limiting portion.

[0024] In at least one embodiment of this application, a washer is mounted on the end of the first straight rod by a screw.

[0025] The invention has at least the following beneficial technical effects:

[0026] The aircraft ground liquid cooling connection device of this application is inserted and fixed to the on-board liquid cooling base without additional force. The docking interface for connecting to the ground liquid cooling hose is vertically downward and does not bend the hose. The handle is pushed to establish a flow channel and locks in place, which is labor-saving and reliable. Attached Figure Description

[0027] Figure 1 This is an overall schematic diagram of an aircraft ground liquid cooling connection device according to one embodiment of this application;

[0028] Figure 2 This is a cross-sectional view of an aircraft ground liquid cooling connection device according to one embodiment of this application;

[0029] Figure 3 This is a schematic diagram of the operation of an aircraft ground liquid cooling connection device according to one embodiment of this application.

[0030] in:

[0031] 1-Matching sleeve; 2-Connecting rod; 3-Unlock button; 4-One-hand grip; 5-Adapter; 6-Spring; 7-Crank slider mechanism; 8-Locking pin; 9-Locking slot; 10-Connecting body; 11-Inner core; 12-Anti-detachment groove. Detailed Implementation

[0032] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the 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, embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0033] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this application.

[0034] The following is in conjunction with the appendix Figures 1 to 3 This application will be described in further detail.

[0035] This application provides an aircraft ground liquid cooling connection device, including a docking sleeve 1, a connector 10, and an inner core 11.

[0036] Specifically, the mating sleeve 1 has an internal receiving cavity. The mating sleeve 1 includes a first mating section and a second mating section. The radial dimension of the first mating section is larger than that of the second mating section. The first mating section is used to connect with the liquid cooling base. An opening for bolt assembly is formed on the wall of the first mating section. A connecting body sliding groove is formed on the side wall of the second mating section, and an opening is formed at the bottom of the second mating section. It can be understood that the connecting body sliding groove is symmetrically formed on the two opposite side walls of the second mating section.

[0037] The connector 10 is set in the receiving cavity of the docking sleeve 1. Sliding blocks are provided on the two opposite side walls of the connector 10. The two sliding blocks are slidably installed in the corresponding connector sliding groove. A fluid channel is provided inside the connector 10. A first interface and a second interface communicating with the fluid channel are respectively opened at both ends of the connector 10. A conversion connector 5 is installed at the second interface. The conversion connector 5 passes through the opening at the bottom of the second docking section and connects to the ground liquid cooling hose.

[0038] The inner core 11 is disposed in the fluid channel. The inner core 11 includes two parts: a first inner core segment and a second inner core segment. Both the first inner core segment and the second inner core segment are T-shaped. The first inner core segment includes a first limiting part and a first straight rod part. The second inner core segment includes a second limiting part and a second straight rod part. The second straight rod part is fixedly connected to the connecting body 10. A cavity is provided inside the second straight rod part. An opening communicating with the cavity is provided on the second limiting part. The first straight rod part passes through the opening on the second limiting part and is nested in the cavity. A spring is sleeved on the first straight rod part. The two ends of the spring abut against the first limiting part and the second limiting part, respectively. The first limiting part is adapted to the inner wall surface of the first interface.

[0039] The aircraft ground liquid cooling connection device of this application has a connected state and a disconnected state. When the connecting body 10 slides forward to the connected position, the connecting body 10 is abutted by the bolt passing through the opening on the first mating section, thereby limiting the connecting body 10 to the connected position.

[0040] In a preferred embodiment of this application, a single-handed grip 4 is also included, which is connected to the second docking section of the docking sleeve 1 for daily carrying, thereby making the overall device gun-shaped.

[0041] In a preferred embodiment of this application, a crank-slider mechanism 7 is further included, which is used to push the connecting body 10 to the connecting position or pull the connecting body 10 to the separating position. Figure 2 As shown, the crank-slider mechanism 7 includes a connecting rod 2, a spring plate 6, and a locking pin 8. The connecting rod 2 includes a first connecting rod and a second connecting rod. The first end of the first connecting rod is hinged to a single-hand grip 4 (the first end of the first connecting rod can also be hinged to a connecting sleeve 1). The single-hand grip 4 provides a fulcrum for the connecting rod 2. The second end of the first connecting rod has two locking slots 9, corresponding to the connected and disengaged states, respectively. The second connecting rod is L-shaped. The first end of the second connecting rod is hinged to a sliding block, and the middle part of the second connecting rod is hinged to the second end of the first connecting rod. The first end of the spring plate 6 is fixedly connected to the second end of the second connecting rod. The locking pin 8 is fixedly installed on the second end of the spring plate 6 and can be engaged in the locking slots 9. It can be understood that in this embodiment, the connecting rod 2 includes two symmetrically arranged sets, each used to connect to a corresponding sliding block. The two connecting rods 2 are connected together through a connector at the second end of the second connecting rod; the connector can be a bolt.

[0042] Advantageously, in this embodiment, the crank-slider mechanism 7 also includes an unlocking button 3, which is mounted on the second connecting rod. By pressing the unlocking button 3, the spring 6 is pushed to disengage the locking pin 8 from the locking slot 9.

[0043] The aircraft ground liquid cooling connection device of this application preferably has an anti-detachment groove 12 for matching with the liquid cooling seat on the first docking section of the docking sleeve 1.

[0044] In a preferred embodiment of this application, the connecting body 10 is provided with a threaded connection portion inside, and the second straight rod portion is provided with an external thread section. The second straight rod portion is fixed to the threaded connection portion by threads.

[0045] In a preferred embodiment of this application, a rubber sealing ring is provided on the side wall of the first limiting portion. The rubber sealing ring is used to cooperate with the inner wall surface of the first interface to achieve a seal. In this embodiment, preferably, two rubber sealing rings are arranged in parallel on the side wall of the first limiting portion.

[0046] In a preferred embodiment of this application, a washer is installed at the end of the first straight rod by a screw, thereby increasing the connection reliability between the first inner core segment and the second inner core segment.

[0047] In this application, after all parts are installed in place, the docking sleeve 1 is aligned with the aircraft liquid cooling base by holding the handle 4, allowing the cylinder on the liquid cooling base to enter the anti-detachment groove 12. Pressing the unlock button 3 on the crank-slider mechanism 7 and pushing the crank-slider mechanism 7, the connecting body 10 moves to the connection position. The locking pin 8 on the crank-slider mechanism 7 then springs into the locking slot 9 and engages, thus achieving connection locking. At this time, the connecting body 10 is pushed into the liquid cooling base, establishing a reliable connection between the ground equipment and the aircraft liquid cooling base. Pressing the unlock button 3 on the crank-slider mechanism 7 causes the locking pin 8 to pop out of the locking slot 9. Pulling the crank-slider mechanism 7 causes the connecting body 10 to exit the liquid cooling base. After the connecting body 10 reaches the separation position, the locking pin 8 on the crank-slider mechanism 7 springs into another locking slot 9, thus achieving separation locking. The docking sleeve 1 is then separated from the aircraft liquid cooling base by holding the handle 4.

[0048] The aircraft ground liquid cooling connection device of this application uses a crank-slider mechanism 7 to convert the axial movement of the liquid cooling base into the rotation of the crank-slider mechanism 7. Based on the lever principle, the length of the crank-slider mechanism 7 is increased, thereby reducing the push and pull force. When the docking sleeve 1 docks with the liquid cooling base into the groove, there is no spring force, making it easier to dock in place. The automatic locking and unlocking of the spring piece 6 on the crank-slider mechanism 7 makes the connection and separation more reliable and in place. The connection with the external liquid cooling hose is without bending, avoiding bending and coiling. All operations can be performed with one hand, making the entire process convenient and quick.

[0049] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An aircraft ground liquid cooling connection device, characterized in that, include: The docking sleeve (1) has an internal cavity. The docking sleeve (1) includes a first docking section and a second docking section. The first docking section is connected to the liquid cooling base. A connecting body sliding groove is opened on the side wall of the second docking section. An opening is provided at the bottom of the second docking section. A connector (10) is disposed in the receiving cavity. A sliding block is provided on the side wall of the connector (10). The sliding block is slidably installed in the sliding groove of the connector. A fluid channel is provided inside the connector (10). A first interface and a second interface communicating with the fluid channel are respectively opened at both ends of the connector (10). A conversion connector (5) is installed at the second interface. The conversion connector (5) passes through the opening at the bottom of the second docking section and is connected to the ground liquid cooling hose. The inner core (11) is disposed in the fluid channel. The inner core (11) includes a first inner core segment and a second inner core segment, both of which are T-shaped. The first inner core segment includes a first limiting part and a first straight rod part. The second inner core segment includes a second limiting part and a second straight rod part. The second straight rod part is fixedly connected to the connecting body (10). A cavity is provided inside the second straight rod part. An opening communicating with the cavity is provided on the second limiting part. The first straight rod part passes through the opening on the second limiting part and is nested in the cavity. A spring is sleeved on the first straight rod part. The two ends of the spring abut against the first limiting part and the second limiting part respectively. The first limiting part is adapted to the inner wall surface of the first interface. When the connector (10) slides to the connection position, the bolt passes through the opening on the first mating section and abuts against the connector (10), thereby limiting the connector (10) to the connection position.

2. The aircraft ground liquid cooling connection device according to claim 1, characterized in that, It also includes a single-hand grip (4), which is connected to the second docking section.

3. The aircraft ground liquid cooling connection device according to claim 2, characterized in that, It also includes a crank-slider mechanism (7), which includes a connecting rod (2), a spring (6), and a locking pin (8), wherein, The link (2) includes a first link and a second link. The first end of the first link is hinged to the single-hand grip (4), and the second end of the first link has two locking slots (9); The second connecting rod is L-shaped, with its first end hinged to the sliding block and its middle part hinged to the second end of the first connecting rod. The first end of the spring piece (6) is fixedly connected to the second end of the second connecting rod; The locking pin (8) is fixedly installed at the second end of the spring piece (6), and the locking pin (8) can be engaged in the upper locking slot (9).

4. The aircraft ground liquid cooling connection device according to claim 3, characterized in that, The crank-slider mechanism (7) also includes an unlock button (3), which is mounted on the second connecting rod. By pressing the unlock button (3), the spring piece (6) is pushed to disengage the locking pin (8) from the locking slot (9).

5. The aircraft ground liquid cooling connection device according to claim 1, characterized in that, The first docking section of the docking sleeve (1) is provided with an anti-detachment groove (12) for matching with the liquid cooling seat.

6. The aircraft ground liquid cooling connection device according to claim 1, characterized in that, The connecting body (10) has a threaded connection part inside, and the second straight rod part has an external thread section. The second straight rod part is fixed to the threaded connection part by the thread.

7. The aircraft ground liquid cooling connection device according to claim 1, characterized in that, A rubber sealing ring is provided on the side wall of the first limiting part, and the rubber sealing ring is used to cooperate with the inner wall surface of the first interface to achieve a seal.

8. The aircraft ground liquid cooling connection device according to claim 7, characterized in that, Two rubber sealing rings are arranged parallel to each other on the side wall of the first limiting part.

9. The aircraft ground liquid cooling connection device according to claim 1, characterized in that, A washer is installed at the end of the first straight rod by a screw.

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