Hydraulic oil liquid sampling device of airplane hydraulic system

Abstract

The utility model relates to the technical field of hydraulic oil liquid sampling, in particular to a hydraulic oil liquid sampling device of an airplane hydraulic system. Comprising a fixed shell, a collection adapter port formed in the left end of the fixed shell, a storage box arranged at the top of the fixed shell, a self-priming water pump, a flow regulating valve and a transmission pipe which are arranged in the fixed shell, and a power supply arranged at the right end of the fixed shell, and the left end of the self-priming water pump is connected with a collection pipe; an inner threaded pipe is arranged on the outer ring of the left end of the collecting pipe, a soft catheter is stored in the storage box, a connecting assembly is arranged at a port of one side of the soft catheter, and the connecting assembly comprises an outer threaded sleeve fixedly connected with the port of one side of the soft catheter and a rotating ring connected with the lateral end face of the outer threaded sleeve. According to the utility model, the external thread sleeve is in threaded connection with the internal thread pipe at the left end of the collecting pipe through the connecting assembly, so that the soft catheter can be quickly communicated with the collecting pipe, and the collecting stability is improved.

Description

Technical Field

[0001] This utility model relates to the field of hydraulic fluid sampling technology, specifically a hydraulic fluid sampling device for an aircraft hydraulic system. Background Technology

[0002] The aircraft hydraulic system refers to the entire set of devices on an aircraft that uses oil as the working medium and relies on oil pressure to drive actuators to complete specific control actions. In order to ensure the safety and reliability of the pressure supply, modern aircraft generally have several independent hydraulic source systems, specifically consisting of a main hydraulic system, an auxiliary hydraulic system, a ground service system, and a hydraulic indication system. During the use of the aircraft, maintenance personnel need to perform regular maintenance on the aircraft, which includes the step of testing the quality of the hydraulic system oil. Regarding the testing process of the hydraulic system oil, each hydraulic system needs to be started in sequence before obtaining the hydraulic oil. Then, the oil is sampled from the ground maintenance panel and sent to the quality inspection department for testing.

[0003] A search revealed that CN218566991U discloses a hydraulic oil sampling device for an aircraft hydraulic system. The user first connects the sampling container to the concave spiral at the bottom of the sampling connection post via a convex spiral thread. After connection, the conduit is removed by pulling out the tank cover at the top of the conduit tank. One end of the conduit is inserted into the left side of the sampling tube inside the sampling adapter port, and the other end is placed inside the aircraft hydraulic oil tank. With the hydraulic oil being sampled, the sampling adapter port contacts the sampling port on the aircraft maintenance panel. Turning on the control switch activates the power supply, which drives the self-priming water pump and flow control valve. The self-priming water pump draws the oil into the container through the conduit and sampling tube, and then transfers the oil to the flow control valve, which controls the flow rate. The oil flows into the sampling container through the inlet. After sampling, the conduit is removed, cleaned, and stored in the conduit tank.

[0004] Although the above-mentioned advantages include stable performance, prevention of oil splashing, controllable oil flow rate, simple operation, and ease of use for users, it has been found in actual use that because the conduit is a flexible tube, it is difficult to insert it into the left end of the collection tube, and the stability is not strong after insertion, thus affecting the collection of oil. Utility Model Content

[0005] To address the aforementioned technical problems, this utility model proposes a hydraulic oil sampling device for an aircraft hydraulic system.

[0006] The technical problem to be solved by this utility model is achieved by the following technical solution:

[0007] A hydraulic fluid sampling device for an aircraft hydraulic system includes a fixed housing, a sampling adapter port located at the left end of the fixed housing, a storage box located at the top of the fixed housing, a connecting pipe communicating with the bottom of the fixed housing, a self-priming water pump, a flow regulating valve, and a transmission pipe located inside the fixed housing, and a power supply located at the right end of the fixed housing. A sampling container is detachably connected to the bottom of the connecting pipe. A handle is connected between the storage box and the connecting pipe. The left end of the self-priming water pump is connected to the sampling pipe, and the left end of the sampling pipe extends into the sampling adapter port. The right end of the water pump is connected to the flow regulating valve via an outlet pipe. The flow regulating valve is connected to the transmission pipe. The bottom of the transmission pipe is located above the sampling container. The power supply is connected to a controller. An internally threaded tube is provided on the outer ring of the left end of the collection tube. A flexible conduit is stored inside the storage box. A connecting assembly is provided at one side port of the flexible conduit. The connecting assembly includes an externally threaded sleeve fixedly connected to one side port of the flexible conduit and a swivel ring connected to the lateral end face of the externally threaded sleeve. The external thread on the externally threaded sleeve is adapted to the internal thread of the internally threaded tube.

[0008] As a further improvement of this utility model, a sealing ring is provided on the inner wall of the external threaded sleeve.

[0009] As a further improvement of this utility model, a number of crossbars are circumferentially connected to the lateral end face of the external threaded sleeve, and a sleeve rod is slidably sleeved on each of the crossbars, with the sleeve rod being fixedly connected to the swivel ring.

[0010] As a further improvement of this utility model, the number of crossbars is four.

[0011] As a further improvement of this utility model, each sleeve is provided with a spring that is connected to the crossbar.

[0012] As a further improvement of this utility model, protrusions are evenly provided on the outer ring surface of the rotating ring.

[0013] As a further improvement of this utility model, the maximum outer diameter of the rotating ring is smaller than the inner diameter of the acquisition adapter port.

[0014] The beneficial effects of this utility model are:

[0015] This utility model provides a hydraulic oil sampling device for an aircraft hydraulic system. Through a connecting component, the external threaded sleeve is threaded to the internal threaded tube at the left end of the sampling tube, allowing for quick connection between the flexible conduit and the sampling tube, improving sampling stability. A rotating ring causes the sleeve rod to rotate, which in turn rotates the external threaded sleeve, facilitating rapid connection between the external threaded sleeve and the internal threaded tube. A spring allows the rotating ring to move to the right via the sleeve rod, so that when the ring contacts the sampling port on the aircraft maintenance panel, it can be squeezed into the sampling adapter port. After sampling, the spring pushes the rotating ring out of the sampling adapter port, allowing for rotation of the ring. Attached Figure Description

[0016] The present invention will be further described below with reference to the accompanying drawings and embodiments:

[0017] Figure 1 This is a schematic diagram of the structure of this utility model;

[0018] Figure 2 This is a partial structural diagram of the internally threaded pipe and the externally threaded sleeve in this utility model.

[0019] Figure 3 for Figure 2 A cross-sectional structural diagram.

[0020] In the diagram: 1. Acquisition adapter port; 2. Fixing shell; 3. Storage box; 4. Spring; 5. Connecting tube; 6. Sampling container; 7. Handle; 8. Self-priming water pump; 9. Flow regulating valve; 10. Power supply; 11. Controller; 12. Acquisition tube; 13. Delivery tube; 14. Transmission tube; 15. Flexible conduit; 16. Internally threaded tube; 17. Externally threaded sleeve; 18. Sealing ring; 19. Crossbar; 20. Sleeve rod; 21. Rotary ring; 22. Protrusion. Detailed Implementation

[0021] To make the technical means, creative features, objectives and effects of this utility model easier to understand, the utility model will be further described below in conjunction with the accompanying drawings and embodiments.

[0022] like Figures 1 to 3As shown, a hydraulic fluid sampling device for an aircraft hydraulic system includes a fixed housing 2, a sampling adapter port 1 located at the left end of the fixed housing 2, a storage box 3 located at the top of the fixed housing 2, a connecting pipe 5 connected to the bottom of the fixed housing 2, a self-priming water pump 8 and a flow regulating valve 9 and a transmission pipe 14 located inside the fixed housing 2, and a power supply 10 located at the right end of the fixed housing 2. A sampling container 6 is detachably connected to the bottom of the connecting pipe 5. A handle 7 is connected between the storage box 3 and the connecting pipe 5. A sampling pipe 12 is connected to the left end of the self-priming water pump 8, and the left end of the sampling pipe 12 extends into the sampling adapter port 1. The right end of the self-priming water pump 8 is connected to the flow regulating valve 9 through a delivery pipe 13. The flow regulating valve 9 is connected to the transmission pipe 14, and the bottom of the transmission pipe 14 is located above the sampling container 6. A controller 11 is connected to the power supply 10. The left end of the collection tube 12 has an internally threaded tube 16 on its outer ring. The storage box 3 contains a flexible conduit 15. A connecting assembly is located at one end of the flexible conduit 15. The connecting assembly includes an externally threaded sleeve 17 fixedly connected to one end of the flexible conduit 15 and a swivel ring 21 connected to the lateral end face of the externally threaded sleeve 17. The external thread on the externally threaded sleeve 17 is adapted to the internal thread of the internally threaded tube 16. Furthermore, a sealing ring 18 is provided on the inner wall of the externally threaded sleeve 17. The sealing ring 18 fits snugly against the left end of the collection tube 12, ensuring a sealing effect for easy extraction of hydraulic fluid. Four crossbars 19 are circumferentially connected to the lateral end face of the external threaded sleeve 17. Each of the four crossbars 19 has a sleeve 20 slidably fitted onto it. The sleeve 20 can slide on the crossbars 19 without detaching from them. The sleeve 20 is fixedly connected to the rotating ring 21, so that rotating the rotating ring 21 rotates the sleeve 20, thereby rotating the crossbars 19. Furthermore, each sleeve 20 contains a spring 4 connected to the crossbar 19. The outer circumferential surface of the rotating ring 21 is uniformly provided with protrusions 22 to improve anti-slip capability.

[0023] Working principle and usage process of this utility model:

[0024] In use, remove the flexible conduit 15, align the external threaded sleeve 17 with the internal threaded tube 16, and then rotate the swivel ring 21 located outside the acquisition adapter port 1 so that the external threaded sleeve 17 is threaded and fixed inside the internal threaded tube 16 until the sealing ring 18 is tightly pressed against the left end of the acquisition tube 12. Then, insert the other end of the flexible conduit 15 into the aircraft hydraulic oil tank so that the acquisition adapter port 1 contacts the sampling port of the aircraft maintenance panel in the hydraulic oil acquisition state. This will cause the swivel ring 21 to be squeezed, and the spring 4 to be compressed. In this embodiment, the maximum outer diameter of the swivel ring 21 is required to be smaller than the inner diameter of the acquisition adapter port 1 to ensure that the swivel ring 21 can be stored inside the acquisition adapter port 1. After the acquisition is completed, when the acquisition adapter port 1 no longer contacts the sampling port of the aircraft maintenance panel, the spring 4 pushes the sleeve rod 20 to move, so that the swivel ring 21 extends out of the acquisition adapter port 1, so that the user can rotate the swivel ring 21 and remove the flexible conduit 15 from the acquisition tube 12.

[0025] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely the principles of this utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claims. The scope of protection of this utility model is defined by the appended claims and their equivalents.

Claims

1. A hydraulic fluid sampling device for an aircraft hydraulic system, comprising a fixed housing (2), a sampling adapter port (1) disposed at the left end of the fixed housing (2), a storage box (3) disposed at the top of the fixed housing (2), a connecting pipe (5) communicating with the bottom of the fixed housing (2), a self-priming water pump (8) and a flow regulating valve (9) and a transmission pipe (14) disposed inside the fixed housing (2), and a power supply (10) disposed at the right end of the fixed housing (2), wherein a sampling container (6) is detachably connected to the bottom of the connecting pipe (5), and the storage box (3) is disposed at the top of the fixed housing (2). A handle (7) is connected between the box (3) and the connecting pipe (5). A collection pipe (12) is connected to the left end of the self-priming water pump (8). The left end of the collection pipe (12) extends into the collection adapter port (1). The right end of the self-priming water pump (8) is connected to the flow regulating valve (9) through the delivery pipe (13). The flow regulating valve (9) is connected to the transmission pipe (14). The bottom of the transmission pipe (14) is located above the sampling container (6). The power supply (10) is connected to a controller (11). The feature is that: The left end of the collection tube (12) is provided with an internally threaded tube (16). The storage box (3) contains a soft tube (15). A connecting component is provided at one side port of the soft tube (15). The connecting component includes an externally threaded sleeve (17) fixedly connected to one side port of the soft tube (15) and a swivel (21) connected to the side end face of the externally threaded sleeve (17). The external thread on the externally threaded sleeve (17) is adapted to the internal thread of the internally threaded tube (16).

2. The hydraulic oil sampling device for an aircraft hydraulic system according to claim 1, characterized in that: A sealing ring (18) is provided on the inner wall of the external threaded sleeve (17).

3. The hydraulic oil sampling device for an aircraft hydraulic system according to claim 1, characterized in that: The external threaded sleeve (17) has several crossbars (19) circumferentially connected on its lateral end face. Each of the crossbars (19) has a sleeve rod (20) slidably sleeved on it, and the sleeve rod (20) is fixedly connected to the swivel ring (21).

4. The hydraulic oil sampling device for an aircraft hydraulic system according to claim 3, characterized in that: There are four crossbars (19).

5. The hydraulic oil sampling device for an aircraft hydraulic system according to claim 3, characterized in that: Each sleeve (20) is equipped with a spring (4) that is connected to the crossbar (19).

6. The hydraulic oil sampling device for an aircraft hydraulic system according to claim 1, characterized in that: The outer ring surface of the rotating ring (21) is uniformly provided with protrusions (22).

7. The hydraulic oil sampling device for an aircraft hydraulic system according to claim 1, characterized in that: The maximum outer diameter of the rotating ring (21) is smaller than the inner diameter of the acquisition adapter (1).

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