Aircraft hydraulic system pressure sensor mounting device

Abstract

The utility model discloses a mounting device for a pressure sensor of an airplane hydraulic system. The mounting device comprises a mounting base, a first mechanical port and a second mechanical port are formed in the two opposite faces of the mounting base correspondingly, the first mechanical port and the second mechanical port are communicated, the first mechanical port and the second mechanical port are both provided with external threads, a mounting support is arranged at the top of the mounting base, a third mechanical port is formed in the top of the mounting support, and the third mechanical port is communicated with the first mechanical port. The top of the third mechanical port is provided with an external thread, the third mechanical port is connected with an internal thread of the pressure sensor through the external thread, the third mechanical port is communicated with the first mechanical port and the second mechanical port, and a pressure sensing part of the pressure sensor penetrates through the mounting support and is arranged in a communicating pipeline of the first mechanical port and the second mechanical port. The pressure sensor can be installed on the premise that a hydraulic pipeline is not damaged.

Description

Technical Field

[0001] The utility model belongs to the aviation field and relates to a pressure sensor installation device for an aircraft hydraulic system. Background Art

[0002] Currently, only mature pressure sensors are available on the market, but there is no corresponding device to connect and fix the sensor to the hydraulic pipeline. In actual applications, engineers will weld the mounting bracket of the pressure sensor into the hydraulic system pipeline, which will cause problems such as damage to the system pipeline. In addition, the mounting bracket welded by this method cannot be disassembled, which increases the weight of the aircraft. Utility Model Content

[0003] The purpose of the utility model is to overcome the shortcomings of the prior art and provide a pressure sensor installation device for an aircraft hydraulic system, which can install the pressure sensor without damaging the hydraulic pipeline.

[0004] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0005] An aircraft hydraulic system pressure sensor mounting device includes a mounting base;

[0006] A first mechanical port and a second mechanical port are respectively arranged on two facing surfaces of the mounting base, the first mechanical port and the second mechanical port are connected, and both the first mechanical port and the second mechanical port are provided with external threads. A mounting support is arranged on the top of the mounting base, and a third mechanical port is arranged on the top of the mounting support. The top of the third mechanical port is provided with an external thread, which is connected to the internal thread of the pressure sensor through the external thread. The third mechanical port is connected to the first mechanical port and the second mechanical port, and the pressure sensing part of the pressure sensor passes through the mounting support and is placed in the connecting pipeline between the first mechanical port and the second mechanical port.

[0007] Preferably, the first mechanical port is an English non-flared port with a No. 6 English external thread.

[0008] Preferably, the second mechanical port is an English non-flared port with a No. 8 English external thread.

[0009] Preferably, a sealing gasket is provided between the pressure sensor and the third mechanical port.

[0010] Preferably, thread glue is provided between the pressure sensor and the thread of the third mechanical port.

[0011] Preferably, the pressure sensing portion of the pressure sensor is flush with the oil in the connecting pipeline between the first mechanical port and the second mechanical port.

[0012] Preferably, the mounting base and the mounting support are connected by welding, and the weld is a third-level weld.

[0013] Furthermore, the weld fillet height of the weld is 4 mm.

[0014] Preferably, the mounting base and the mounting support are both made of 06Cr19Ni10.

[0015] Compared with the prior art, the utility model has the following beneficial effects:

[0016] The utility model installs a first mechanical port and a second mechanical port on the base to be connected, and is used to connect the hydraulic hard pipe. The base is provided with a mounting support for fixing the pressure sensor. The pressure sensing part of the pressure sensor can be placed in the connecting pipeline of the two connecting interfaces. The oil is sent into the first mechanical port and out of the second mechanical port through the hydraulic pipeline. The pressure sensor continuously collects the pressure index of the hydraulic system. The pressure sensor is mechanically connected to the hydraulic system pipeline through the mounting base and the mounting support, which will not cause damage to the system pipeline and is convenient for disassembly, replacement and maintenance. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A schematic diagram of a pressure sensor installation device for an aircraft hydraulic system

[0018] Figure 2 A schematic diagram of the use of an aircraft hydraulic system pressure sensor installation device

[0019] Figure 3 A schematic diagram of the mechanical interface of a pressure sensor installation device for an aircraft hydraulic system

[0020] Among them, there are main view, left view and top view.

[0021] Explanation of numbers in the figure: 1 mounting base, 2 mounting support, 3 pressure sensor, 4 first mechanical port, 5 second mechanical port, 6 third mechanical port, 7 sealing gasket. DETAILED DESCRIPTION

[0022] The technical solutions in the embodiments of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all of the embodiments; based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the utility model.

[0023] It should be noted that the words "front", "rear", "left", "right", "up" and "down" used in the following description refer to directions in the drawings, and the words "inside" and "outside" refer to directions toward or away from the geometric center of a specific component, respectively.

[0024] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by those skilled in the art in the technical field of the present invention. The terms used herein in the specification of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention. The term "and / or" used herein includes any and all combinations of one or more related listed items.

[0025] like Figure 1 , Figure 2 and Figure 3 As shown, a pressure sensor installation device for an aircraft hydraulic system includes a mounting base 1. Connection interfaces are arranged on two facing surfaces of the mounting base 1, which are a first mechanical port 4 and a second mechanical port 5. The two connection interfaces are connected. A mounting support 2 is arranged on the top of the mounting base 1. A third mechanical port 6 is arranged on the top of the mounting support 2. The third mechanical port 6 is used to fix the pressure sensor 3. The third mechanical port 6 is connected with the first mechanical port 4 and the second mechanical port 5. The pressure sensing part of the pressure sensor 3 can pass through the mounting support 2 and be placed in the connecting pipeline of the two connection interfaces. The two mechanical interfaces are respectively connected to the outer sleeve nuts of the hydraulic hard pipe.

[0026] The first mechanical port 4 is processed according to the AS33514 standard, is an imperial non-flared port, has a No. 6 imperial external thread, and the external thread is executed according to the UNJF-3A standard, which can be matched with the internal thread of the outer nut of the hydraulic conduit.

[0027] The second mechanical port 5 is processed according to the AS33514 standard, is an imperial non-flared port, has an 8th imperial external thread, and the external thread is executed according to the UNJF-3A standard, which can be matched with the internal thread of the outer nut of the hydraulic conduit.

[0028] The third mechanical port 6 is a metric external thread, which can be connected to the internal thread of the pressure sensor 3 and tightened. Before installation, thread glue needs to be applied to prevent the thread from biting. In addition, the thread glue can play a role in preventing loosening after curing. In order to prevent the occurrence of hydraulic oil leakage, a sealing gasket 7 is installed at the docking point.

[0029] The mounting base 1 and the mounting support 2 are both machined parts. Finally, they are welded to form a whole. The weld is a grade 3 weld of GB12469-1990. The weld angle height is 4mm, the weld is smooth, without bubbles or slag inclusions.

[0030] The pressure sensing part of the pressure sensor 3 is flush with the oil in the hydraulic pipeline. After the pressure sensor 3 is installed, the sealing test is completed together with the sealing test of the hydraulic pipeline.

[0031] The hydraulic oil is fed into the second mechanical port 5 through the hydraulic pipeline and discharged from the first mechanical port 4. The pressure sensor continuously collects the pressure index of the hydraulic system.

[0032] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0033] It should be understood that the above description is for illustration and not for limitation. Many embodiments and many applications beyond the examples provided will be apparent to those skilled in the art upon reading the above description. Therefore, the scope of the present teachings should not be determined with reference to the above description, but rather with reference to the foregoing claims and the full scope of equivalents to which such claims are entitled. For the purpose of comprehensiveness, all articles and references, including disclosures of patent applications and publications, are incorporated herein by reference. The omission of any aspect of the subject matter disclosed herein in the foregoing claims is not intended to be a waiver of the subject matter, nor should it be considered that the applicant has not considered the subject matter as part of the disclosed utility model subject matter.

Claims

1. An aircraft hydraulic system pressure sensor installation device, characterized in that: including a mounting base (1); A first mechanical port (4) and a second mechanical port (5) are respectively arranged on two facing surfaces of the mounting base (1), the first mechanical port (4) and the second mechanical port (5) are connected, and both the first mechanical port (4) and the second mechanical port (5) are provided with external threads. A mounting support (2) is arranged on the top of the mounting base (1), and a third mechanical port (6) is arranged on the top of the mounting support (2). The top of the third mechanical port (6) is provided with external threads and is connected to the internal threads of the pressure sensor (3) via the external threads. The third mechanical port (6) is connected to the first mechanical port (4) and the second mechanical port (5), and the pressure sensing portion of the pressure sensor (3) passes through the mounting support (2) and is placed in a connecting pipeline between the first mechanical port (4) and the second mechanical port (5); The first mechanical port (4) is an English non-flared port with a No. 6 English external thread; The second mechanical port (5) is an English non-flared port with a No. 8 English external thread; A sealing gasket (7) is provided between the pressure sensor (3) and the third mechanical port (6).

2. The aircraft hydraulic system pressure sensor installation device according to claim 1, characterized in that: Thread glue is provided between the threads of the pressure sensor (3) and the third mechanical port (6).

3. The aircraft hydraulic system pressure sensor installation device according to claim 1, characterized in that: The pressure sensing portion of the pressure sensor (3) is flush with the oil in the connecting pipeline of the first mechanical port (4) and the second mechanical port (5).

4. The aircraft hydraulic system pressure sensor installation device according to claim 1, characterized in that: The mounting base (1) and the mounting support (2) are connected by welding, and the weld is a third-level weld.

5. The aircraft hydraulic system pressure sensor installation device according to claim 4, characterized in that: The weld fillet height is 4 mm.

6. The aircraft hydraulic system pressure sensor installation device according to claim 1, characterized in that: The mounting base (1) and the mounting support (2) are both made of 06Cr19Ni10.

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