Airplane hydraulic oil tank pressure detection device

Abstract

The invention discloses an aircraft hydraulic oil tank pressure detection device, and belongs to the technical field of aviation equipment detection. 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, the other end of the bottom rod is welded with an inclined rod, and the other end of the inclined rod is welded with a core 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 internal pressure detection efficiency 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] The invention belongs to the technical field of aviation equipment detection, and relates to an aircraft hydraulic oil tank pressure detection device. Background Art

[0002] The hydraulic oil tank of a certain aircraft requires a pressure of 0.2 MPa or less when filling with hydraulic oil. To ensure the tank's tightness, the port is a ф3 one-way sealing valve. This means that the closed port of the ф3 one-way sealing valve must be opened and a pressure gauge connected to test the internal pressure of the hydraulic oil tank. The measured value must be cross-checked with the pressure gauge on the aircraft, and the pressure value and related parameters must be recorded to confirm the hydraulic oil filling amount and thus ensure the aircraft's overall mileage. Due to the difficulty of removing the instrumentation on certain aircraft, the hydraulic oil tank's hydraulic oil pressure must be tested frequently before takeoff. Existing technologies often use direct readings from the flight control system. Without a dedicated hydraulic oil tank detection device, cross-references cannot be made, and conventional detection methods are difficult. Summary of the Invention

[0003] To address the gaps in testing the pressure and leak tightness of hydraulic oil tanks on certain aircraft, this invention provides an aircraft hydraulic oil tank pressure detection device. This device can quickly, accurately, and effectively detect the oil pressure and leak tightness of certain aircraft hydraulic oil tanks. The device is portable, offers accurate measurement with a low error rate, and includes a separate pressure gauge, requiring only semi-annual calibration.

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

[0005] A device for detecting pressure of an aircraft hydraulic oil tank comprises a first plugging cap 1, a core rod 2, a tightening nut 3, an inclined rod 4, a bottom rod 5, a second plugging cap 6, a vertical rod 7, a flat nozzle 8, a washer 9, an adapter 10, and a pressure gauge 11.

[0006] The middle part of the bottom rod 5 is welded to and communicated with the vertical rod 7, and one end thereof is welded to and communicated with the oblique rod 4, forming an angle of 135° between the two. The other end of the bottom rod 5 is detachably installed with a second blocking cap 6, and the other end of the oblique rod 4 is welded to and communicated with the core rod 2. The core rod 2 is used to open the one-way sealing valve of the aircraft hydraulic oil tank to form an internal passage between the inside of the hydraulic oil tank and the detection device. The end face of the oblique rod 4 at the junction with the core rod 2 is an inwardly inclined annular cone.

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

[0008] The first blocking cap 1 is detachably mounted on the end of the core rod 2 , and is removed when the detection device is in use and installed when the detection device is idle, thereby protecting the core rod 2 .

[0009] The flat nozzle 8, gasket 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 to form a local sealed space for direct reading of the pressure gauge 11.

[0010] When in use, remove the first plugging 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 to connect it with the hydraulic oil tank thread, use the conical surface at the junction of the inclined rod 4 and the core rod 2 to seal the hydraulic oil tank port with a rubber gasket end face, perform an intuitive sealing pressure test and read the pressure gauge 11.

[0011] The beneficial effects of the present invention are as follows: the structure of the present invention is simple and practical, and compared with the existing technology, it has high practicality, speed, accuracy and safety. It can improve the internal pressure detection efficiency of the aircraft hydraulic oil tank, and reduce the difficulties such as substandard sealing performance (end face rubber gasket sealing), 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. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 This is the overall structural diagram of the present invention.

[0013] Figure 2 Schematic diagram of the first blocking cap structure, where (a) is the main view and (b) is the side view.

[0014] Figure 3 It is a diagram of the core rod structure, where (a) is the main view and (b) is the side view.

[0015] Figure 4 This is a structural diagram of the tightening nut, where (a) is the main view and (b) is the side view.

[0016] Figure 5 It is a structural diagram of the inclined rod, where (a) is a top view and (b) is a main view.

[0017] Figure 6 It is a structural diagram of the bottom rod, where (a) is the main view, (b) is the side view, and (c) is the top view.

[0018] Figure 7 This is the second blocking cap structure diagram.

[0019] Figure 8 This is the vertical pole structure diagram.

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

[0021] Figure 10 The diagram shows the structure of the gasket.

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

[0023] Among them, 1 first plugging cap, 2 core rod, 3 tightening nut, 4 inclined rod, 5 bottom rod, 6 second plugging cap, 7 vertical rod, 8 flat nozzle, 9 washer, 10 adapter, 11 pressure gauge. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical solutions and advantages of the present invention more clear, the specific implementation methods of the present invention will be described in detail below based on the technical solutions.

[0025] A device for detecting pressure of an aircraft hydraulic oil tank, comprising a first plugging cap 1, a core rod 2, a tightening nut 3, an inclined rod 4, a bottom rod 5, a second plugging cap 6, a vertical rod 7, a flat nozzle 8, a washer 9, an adapter 10, and a pressure gauge 11. Figure 1 .

[0026] like Figure 6 The bottom rod 5 is a hollow tubular structure, wherein the hole in the middle is connected to the vertical rod 7 (such as Figure 8 ) are welded and connected, and are connected to the inclined rod 4 (such as Figure 5 ) are welded and connected, with an angle of 135° between the two. The other end of the bottom rod 5 is connected with a second blocking cap 6 (such as Figure 7 ); one end of the diagonal rod 4 is welded to the bottom rod 5, and the other end is welded to the core rod 2 (such as Figure 3 ) are welded and connected, and the end face of the oblique rod 4 at the junction with the core rod 2 is made into an inwardly inclined annular cone surface; the outer diameter of the core rod 2 is matched with the inner diameter of the oblique rod 4, one end of the core rod 2 is welded to the oblique rod 4, and the other end 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.

[0027] like Figure 4 The tightening nut 3 is sleeved on the core rod 2 and is used 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 end face.

[0028] like Figure 2 The first blocking cap 1 is detachably mounted on the end of the core rod 2. It is removed when the detection device is in use and installed when the detection device is idle to protect the core rod 2.

[0029] Described flat nozzle 8 (as Figure 9 ), gasket 9 (such as Figure 10 ), adapter 10 (such as Figure 11) are connected in sequence at the ends of the vertical rod 7 and fastened with threads to connect the pressure gauge 11 to form a local sealed space for direct reading of the pressure gauge 11, wherein the pressure gauge 11 is a seismic-resistant pressure gauge.

[0030] When in use, remove the first plugging 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 to connect it with the hydraulic oil tank thread, use the conical surface at the junction of the inclined rod 4 and the core rod 2 to seal the hydraulic oil tank port with a rubber gasket end face, perform an intuitive sealing pressure test and read the pressure gauge 11.

[0031] In summary, the above are only preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. An aircraft hydraulic oil tank pressure detection device, characterized in that: The detection device comprises a core rod (2), a tightening nut (3), an inclined rod (4), a bottom rod (5), a second blocking cap (6), a vertical rod (7), and a pressure gauge (11); The middle part of the bottom rod (5) is welded to and communicated with the vertical rod (7), the end of the vertical rod (7) is sealed and connected to a pressure gauge (11), one end of the bottom rod (5) is welded to and communicated with the inclined rod (4), the other end of the bottom rod (5) is detachably mounted with a second blocking cap (6), the other end of the inclined rod (4) is welded to and communicated with the core rod (2), and the core rod (2) is used to open a one-way sealing valve of an aircraft hydraulic oil tank; The tightening nut (3) is sleeved on the core rod (2) and is used to form a threaded connection with the thread of the aircraft hydraulic oil tank, and the inclined rod (4) is used to perform end face sealing on the hydraulic oil tank port.

2. The aircraft hydraulic oil tank pressure detection device according to claim 1, characterized in that: The bottom rod (5) and the oblique rod (4) form an angle of 135 degrees.

3. The aircraft hydraulic oil tank pressure detection device according to claim 1, characterized in that: The end face where the inclined rod (4) and the core rod (2) meet is formed into an inwardly inclined annular conical face, and the inclined rod (4) utilizes the conical face to perform a rubber pad end face seal on the hydraulic oil tank port.

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 mounted with a first blocking cap (1), which is removed when the detection device is in use and mounted when the detection device is idle, thereby protecting the core rod (2).

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

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