Airplane hydraulic oil tank pressure detection device

Abstract

The utility model discloses a pressure detection device for an airplane hydraulic oil tank, which belongs to the technical field of aviation equipment detection and is characterized in that the middle part of a bottom rod is welded and communicated with a vertical rod, the end part of the vertical rod is hermetically connected with a pressure gauge, one end of the bottom rod is provided with a second plug cap, and the other end of the bottom rod is welded with an inclined rod; the inclined rod is in threaded connection with threads of the airplane hydraulic oil tank, and end face sealing is conducted on a port of the hydraulic oil tank through the inclined rod end face. The device is simple and practical in structure, can improve the detection efficiency of the internal pressure of the airplane hydraulic oil tank, reduces the difficulties that the sealing performance does not reach the standard, the detection is inaccurate, the pressure of the hydraulic oil tank is not clear, and the oil tank is damaged, improves the thermal guarantee work efficiency, and shortens the whole period.

Description

Technical Field

[0001] This utility model belongs to the field of aviation equipment testing technology, and relates to an aircraft hydraulic oil tank pressure testing device. Background Technology

[0002] The hydraulic oil tank of a certain type of aircraft requires a pressure of ≥0.2 MPa when filling with hydraulic fluid. To ensure the tank's airtightness, a ф3 one-way valve is used. This means that after opening the closed port of the ф3 one-way valve, a pressure gauge must be connected to measure the internal pressure of the hydraulic oil tank. The measured value must be cross-checked with the pressure gauge readings on the aircraft, and the pressure value and related parameters must be recorded to confirm the hydraulic oil filling level, thereby ensuring the aircraft's overall mileage. Due to the difficulty in disassembling the instruments of this type of aircraft, the hydraulic oil pressure in the tanks must be tested before takeoff, a process that is frequently performed. Existing technologies mostly use direct readings from the flight control system, lacking a dedicated hydraulic oil tank testing device, making cross-referencing impossible, and conventional testing methods are difficult to implement. Utility Model Content

[0003] To fill the gap in the testing of hydraulic oil tank pressure and sealing performance for a certain type of aircraft, this invention provides a hydraulic oil tank pressure testing device. This device can quickly, accurately, and effectively test the hydraulic oil pressure of a certain type of aircraft and effectively assess its sealing performance. This invention is portable, provides accurate measurements with a low error rate, and features a separate pressure gauge that only requires calibration every six months.

[0004] The present invention adopts the following technical solution:

[0005] An aircraft hydraulic oil tank pressure detection device, the detection device comprising a first plug 1, a core rod 2, a tightening nut 3, a diagonal rod 4, a bottom rod 5, a second plug 6, a vertical rod 7, a flat nozzle 8, a washer 9, an adapter 10, and a pressure gauge 11.

[0006] The bottom rod 5 is welded to and connected to the vertical rod 7 in the middle, and one end of it is welded to and connected to the diagonal rod 4. The two are at a 135° angle. The other end of the bottom rod 5 is detachably fitted with a second cap 6. The other end of the diagonal rod 4 is welded to and connected to the core rod 2. The core rod 2 is used to open the one-way sealing valve of the aircraft hydraulic oil tank, so as to form an internal passage between the inside of the hydraulic oil tank and the detection device. The end face of the diagonal rod 4 where it connects with the core rod 2 is made into an inwardly inclined annular cone surface.

[0007] The tightening nut 3 is fitted onto the core rod 2 to form a threaded connection with the aircraft hydraulic oil tank thread, and the conical surface at the junction of the inclined rod 4 and the core rod 2 is used to seal the hydraulic oil tank port with a rubber gasket.

[0008] The first cap 1 is detachably installed at the end of the core rod 2. It is removed when the detection device is in use and installed when the detection device is not in use to protect the core rod 2.

[0009] The flat nozzle 8, washer 9, and adapter 10 are sequentially connected to the end of the vertical rod 7 and fastened with threads to connect the pressure gauge 11, forming a local sealed space for direct reading of the pressure gauge 11.

[0010] In use, remove the first cap 1, open the one-way sealing valve of the hydraulic oil tank with the core rod 2 and extend it into the hydraulic oil tank. Tighten the nut 3 and connect it to the hydraulic oil tank threadedly. Use the conical surface at the junction of the inclined rod 4 and the core rod 2 to seal the end face of the hydraulic oil tank with a rubber gasket. Perform a visual sealing pressure test and read the pressure through the pressure gauge 11.

[0011] The beneficial effects of this utility model are as follows: This utility model has a simple and practical structure, and compared with the prior art, it has high practicality, speed, accuracy and safety. It can improve the internal pressure detection efficiency of aircraft hydraulic oil tanks and reduce difficulties such as substandard sealing performance (end face rubber gasket seal), inaccurate detection, unclear hydraulic oil tank pressure, and damage to the oil tank, thereby improving the efficiency of thermal protection work and shortening the overall cycle. Attached Figure Description

[0012] Figure 1 This is a structural diagram of the present utility model.

[0013] Figure 2 The diagram shows the structure of the first cap, where (a) is the front view and (b) is the side view.

[0014] Figure 3 The diagram shows the core rod structure, where (a) is the front view and (b) is the side view.

[0015] Figure 4 The diagram shows the structure of the tightening nut, where (a) is the front view and (b) is the side view.

[0016] Figure 5 The diagram shows the structure of the diagonal brace, where (a) is the top view and (b) is the front view.

[0017] Figure 6 The diagram shows the structure of the base rod, where (a) is the front view, (b) is the side view, and (c) is the top view.

[0018] Figure 7 This is a structural diagram of the second cap.

[0019] Figure 8 This is a diagram of the vertical rod structure.

[0020] Figure 9 This is a structural diagram of a flat nozzle.

[0021] Figure 10 This is a structural diagram of a washer.

[0022] Figure 11 The diagram shows the structure of the adapter rod, where (a) is the top view and (b) is the front view.

[0023] The components are: 1. First plug cap; 2. Core rod; 3. Tightening nut; 4. Diagonal rod; 5. Bottom rod; 6. Second plug cap; 7. Vertical rod; 8. Flat nozzle; 9. Washer; 10. Adapter; 11. Pressure gauge. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of this utility model clearer, the specific embodiments of this utility model will be described in detail below.

[0025] An aircraft hydraulic oil tank pressure detection device, comprising a first plug 1, a core rod 2, a tightening nut 3, a diagonal rod 4, a base rod 5, a second plug 6, a vertical rod 7, a flat nozzle 8, a washer 9, an adapter 10, and a pressure gauge 11, as shown. Figure 1 .

[0026] like Figure 6 The bottom rod 5 is a hollow tubular structure, with a hole in its middle connecting to the vertical rod 7 (as shown in the image). Figure 8 ) Welded and connected, it is connected to the diagonal rod 4 (such as Figure 5 The two are welded together and connected, forming a 135° angle. A joint is made at the other end of the bottom rod 5, and a second cap 6 is detachably installed thereon. Figure 7 The inclined rod 4 is welded at one end to the base rod 5, and at the other end to the core rod 2 (e.g., Figure 3 The ends of the inclined rod 4 and the core rod 2 are welded and connected, and the end face of the connection is made into an inwardly inclined annular conical surface; the outer diameter of the core rod 2 matches the inner diameter of the inclined rod 4, one end of which is welded to the inclined rod 4, and the other end is used to open the one-way sealing valve of the aircraft hydraulic oil tank, so as to realize the internal passage between the hydraulic oil tank and the detection device.

[0027] like Figure 4 The tightening nut 3 is fitted onto the core rod 2 to form a threaded connection with the aircraft hydraulic oil tank thread, and the conical surface at the junction of the inclined rod 4 and the core rod 2 is used to seal the hydraulic oil tank port with a rubber gasket.

[0028] like Figure 2 The first cap 1 is detachably fitted onto the end of the core rod 2. It is removed when the detection device is in use and installed when the detection device is not in use to protect the core rod 2.

[0029] The flat nozzle 8 (e.g.) Figure 9 ), Washer 9 (e.g.) Figure 10 ), adapter 10 (e.g.) Figure 11They are sequentially connected to the ends of the vertical rod 7 and fastened with threads to connect to the pressure gauge 11, forming a local sealed space for direct reading of the pressure gauge 11. The pressure gauge 11 is a shock-resistant pressure gauge.

[0030] In use, remove the first cap 1, open the one-way sealing valve of the hydraulic oil tank with the core rod 2 and extend it into the hydraulic oil tank. Tighten the nut 3 and connect it to the hydraulic oil tank threadedly. Use the conical surface at the junction of the inclined rod 4 and the core rod 2 to seal the end face of the hydraulic oil tank with a rubber gasket. Perform a visual sealing pressure test and read the pressure through the pressure gauge 11.

[0031] In summary, the above are merely preferred embodiments of this utility model and are not intended to limit the scope of protection of this utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the scope of protection of this utility model.

Claims

1. A device for detecting the pressure of an aircraft hydraulic oil tank, characterized in that, The detection device includes a core rod (2), a tightening nut (3), a diagonal rod (4), a bottom rod (5), a second plug (6), a vertical rod (7), and a pressure gauge (11); The bottom rod (5) is welded to and connected to the vertical rod (7) in the middle. A pressure gauge (11) is sealed and connected at the end of the vertical rod (7). One end of the bottom rod (5) is welded to and connected to the inclined rod (4). The other end of the bottom rod (5) is detachably fitted with a second plug cap (6). The other end of the inclined rod (4) is welded to and connected to the core rod (2). The core rod (2) is used to open the one-way sealing valve of the aircraft hydraulic oil tank. The tightening nut (3) is fitted onto the core rod (2) to form a threaded connection with the aircraft hydraulic oil tank thread, and the inclined rod (4) is used to seal the end face of the hydraulic oil tank port.

2. The aircraft hydraulic oil tank pressure detection device according to claim 1, characterized in that, The base rod (5) and the diagonal rod (4) form a 135° angle.

3. The aircraft hydraulic oil tank pressure detection device according to claim 1, characterized in that, The end face of the diagonal rod (4) at the junction with the core rod (2) is made into an inwardly inclined annular cone surface, and the diagonal rod (4) uses the cone surface to seal the end face of the hydraulic oil tank port with a rubber gasket.

4. The aircraft hydraulic oil tank pressure detection device according to claim 1, characterized in that, The end of the core rod (2) is detachably fitted with a first cap (1), which is removed when the detection device is in use and installed when the detection device is not in use, to protect the core rod (2).

5. The aircraft hydraulic oil tank pressure detection device according to claim 1, characterized in that, The vertical rod (7) is connected in sequence to a flat nozzle (8), a washer (9), and an adapter (10), and is fastened with threads for sealing connection with the pressure gauge (11).

Images