Straight-through switching structure of aircraft hydraulic system

Abstract

The utility model belongs to the technical field of aviation hydraulic system assembling and manufacturing, and discloses an airplane hydraulic system straight-through switching structure which comprises a body designed to be of a cylindrical structure, a through hole is formed in the body, and a section of internal thread is arranged at one end of the through hole of the body and matched with an air pressure sensor connector; the extension section is designed at the other end of the through hole of the body, the outer diameter of the extension section is smaller than that of the body, and external threads are arranged on the outer surface of the extension section and matched with a hydraulic system pipe joint. According to the utility model, the problem that the barometric sensor cannot be mounted in an onboard hydraulic system is solved, so that the barometric sensor can be fixed on an airplane, the fixation during flight is kept, and the task reliability is improved.

Description

Technical Field

[0001] This utility model belongs to the field of aviation hydraulic system assembly and manufacturing technology, specifically relating to a direct-connection structure for an aircraft hydraulic system. Background Technology

[0002] The thread specifications of the air pressure sensors currently available on the market are different from the standard thread specifications of the standard parts for the machine's hydraulic system. Therefore, there is a difference in thread size, which makes it impossible to install the air pressure sensors in the machine's hydraulic system.

[0003] Therefore, a straight-through adapter structure needs to be designed, with both ends processed according to different standards, to ensure the smooth installation and normal operation of the pressure sensor. Utility Model Content

[0004] The purpose of this invention is to provide a direct-connection structure for an aircraft hydraulic system to overcome the shortcomings of the prior art, enabling the pressure sensor to be fixed on the aircraft, maintaining its position during flight and improving mission reliability.

[0005] The technical solution of this utility model is implemented as follows:

[0006] A straight-through adapter structure for an aircraft hydraulic system, comprising:

[0007] The main body is designed as a cylindrical structure with a through hole inside. One end of the through hole in the main body is provided with an internal thread to match the air pressure sensor connector.

[0008] The extension section is designed at the other end of the through hole of the main body. Its outer diameter is smaller than that of the main body. The outer surface of the extension section is provided with external threads to match the hydraulic system pipe fittings.

[0009] As a further embodiment of this utility model, the main body is provided with an external hexagonal boss.

[0010] As a further embodiment of this utility model, the cross-section of the body is designed to be hexagonal or circular.

[0011] As a further embodiment of this utility model: the extension section is a first mechanical interface, and its external thread is a British No. 6 external thread, which conforms to the standard AS4375E06.

[0012] As a further embodiment of this utility model: one end of the body with internal thread is a second mechanical interface, and its internal thread is a British No. 6 internal thread, which conforms to the standard AS5202-06.

[0013] As a further embodiment of this utility model: a 4×45° recessed groove is provided at the port of the second mechanical interface for placing an O-ring seal.

[0014] As a further embodiment of this utility model: the external hexagonal boss is located on one side of the second mechanical interface, and a plurality of fuse holes are provided thereon.

[0015] As a further embodiment of this utility model: the fuse holes are in three groups, with a diameter of φ1.2mm, and are machined using a φ1 CNC drill bit.

[0016] As a further embodiment of this utility model: the through-connector structure is a machined integrated structure, and the material is 06Cr19Ni10 resistant to phosphate ester-based hydraulic oil.

[0017] The beneficial effects of this application are as follows:

[0018] 1. In this application, the first mechanical interface and the second mechanical interface are connected. The first mechanical interface is connected to the hydraulic pipe joint on the machine, and the second mechanical interface is connected to the air pressure sensor. The pressure sensing part of the air pressure sensor can be placed in the connecting pipe of the two connection interfaces. Air pressure is sent in from the first mechanical interface and sent out from the second mechanical interface. The air pressure sensor continuously collects the gas pressure index of the hydraulic system.

[0019] 2. This application enables the barometric pressure sensor to be fixed on the aircraft, maintaining its position during flight and improving mission reliability.

[0020] 3. The main body of this application is provided with an external hexagonal boss, and a fuse hole is provided on the boss for double-strand safety with the barometric pressure sensor to maintain fixation during flight and improve mission reliability.

[0021] The present application will be further described in detail below with reference to the accompanying drawings of the embodiments. Attached Figure Description

[0022] Figure 1 A schematic diagram of a straight-through adapter structure for an aircraft hydraulic system;

[0023] Figure 2 A schematic diagram illustrating the use of a straight-through adapter structure for an aircraft hydraulic system;

[0024] The numbers in the diagram are explained as follows: 1. First mechanical interface; 2. Second mechanical interface; 3. External thread; 4. Internal thread; 5. 4×45° recessed groove; 6. O-ring seal; 7. Pressure sensor; 8. External hexagonal boss; 9. Fuse hole; 10. Hydraulic system pipe joint. Detailed Implementation

[0025] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions of the embodiments of this utility model 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 utility model. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this utility model, and should not be construed as limiting this utility model. All other embodiments obtained by those skilled in the art based on the embodiments of this utility model without creative effort are within the scope of protection of this utility model.

[0026] The following is in conjunction with the appendix Figure 1-2 The embodiments of this utility model will be described in detail below.

[0027] Example 1

[0028] A straight-through adapter structure for an aircraft hydraulic system, comprising:

[0029] The main body is designed as a cylindrical structure with a through hole inside. One end of the through hole in the main body is provided with an internal thread 4, which matches the air pressure sensor 7 connector.

[0030] The extension section is designed at the other end of the through hole of the main body. Its outer diameter is smaller than that of the main body. An external thread 3 is provided on the outer surface of the extension section to match the hydraulic system pipe joint 10.

[0031] The main body is provided with an external hexagonal boss 8, the external hexagonal boss 8 having a size of 1in×δ8mm.

[0032] The cross-section of the body is designed to be hexagonal or circular.

[0033] The extension section is the first mechanical interface 1, and its external thread 3 is a British 6-gauge external thread 3, which conforms to the standard AS4375E06.

[0034] One end of the body with internal thread 4 is a second mechanical interface 2. Its internal thread 4 is a British No. 6 internal thread 4, and the standard is AS5202-06.

[0035] A 4×45° recessed groove 5 is machined at the port of the second mechanical interface 2, and the O-ring 6 is placed exactly in the 4×45° recessed groove 5 for sealing.

[0036] The external hexagonal boss 8 is located on one side of the second mechanical interface 2, and has several fuse holes 9.

[0037] The fuse holes 9 consist of 3 sets, each with a diameter of φ1.2mm, and are machined using a φ1 CNC drill bit. Any one of the 3 sets of fuse holes 9 can be selected to form a double fuse with the fuse hole 9 built into the pressure sensor 7, thus disregarding the installation angle of the pressure sensor 7.

[0038] The through-connector structure is a machined integrated structure, and the material is 06Cr19Ni10, which is resistant to phosphate ester-based hydraulic oil.

[0039] Example 2

[0040] This utility model provides a direct-connector structure for an aircraft hydraulic system. A first mechanical interface 1 and a second mechanical interface 2 are respectively provided on two opposing surfaces, communicating to form a hydraulic oil passage. The first mechanical interface 1 has an external thread 3, and the second mechanical interface 2 has an internal thread 4. The second mechanical interface 2 has a 4×45° recessed groove 5 for accommodating an O-ring seal 6, ensuring a seal when mated with the external thread 3 of a pressure sensor 7. The direct-connector structure body has an external hexagonal boss 8, with a fuse hole 9 on the boss for double-strand safety with the pressure sensor 7.

[0041] During implementation, manually pre-tighten the first mechanical interface 1 to the hydraulic system pipe connector 10, and manually pre-tighten the second mechanical interface 2 to the pressure sensor 7. When tightening, ensure the O-ring 6 does not lift up. Use two open-end wrenches, one to hold the external hexagonal boss 8 of the straight-through adapter structure and the other to hold the hydraulic system pipe connector 10, to tighten the straight-through adapter structure. Use two open-end wrenches, one to hold the external hexagonal boss 8 of the straight-through adapter structure and the other to hold the pressure sensor 7, to tighten the pressure sensor 7.

[0042] Pass the fuse through fuse hole 9 to provide double-strand protection for the straight-through adapter structure and the pressure sensor 7.

[0043] Thus, the objective of this utility model has been achieved.

[0044] The above are merely preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. An aircraft hydraulic system pass-through switching arrangement, characterized by, The utility model relates to a straight-through adapter structure for a gas pressure sensor and a hydraulic system pipe joint, comprising: a body designed as a cylindrical structure with a through hole in the inside, an inner thread at one end of the through hole of the body matched with a gas pressure sensor joint; an extension section designed at the other end of the through hole of the body with an outer diameter smaller than that of the body, an outer thread on the outer surface of the extension section matched with a hydraulic system pipe joint.

2. The aircraft hydraulic system pass-through switching architecture of claim 1, wherein, An outer hexagonal boss is arranged on the body.

3. The aircraft hydraulic system pass-through switching architecture of Claim 2, wherein, The cross section of the body is designed as a hexagonal shape or a circular shape.

4. The aircraft hydraulic system pass-through switching architecture of Claim 3, wherein, The extension section is a first mechanical interface, the outer thread is a British No. 6 outer thread, and the execution standard is AS4375E06.

5. The aircraft hydraulic system pass-through switching architecture of Claim 4, wherein, The end of the body with the inner thread is a second mechanical interface, the inner thread is a British No. 6 inner thread, and the execution standard is AS5202-06.

6. The aircraft hydraulic system pass-through switching architecture of Claim 5, wherein, A 4×45° recessed groove is arranged at the port of the second mechanical interface for placing an O-shaped sealing ring.

7. The aircraft hydraulic system pass-through switching architecture of claim 6, wherein, The outer hexagonal boss is located at one side of the second mechanical interface, and a plurality of fuse holes are arranged on the outer hexagonal boss.

8. The aircraft hydraulic system pass-through switching architecture of Claim 7, wherein, The fuse holes are 3 groups, the hole diameter is φ1.2 mm, and the holes are processed by a φ1 numerical control drill.

9. The aircraft hydraulic system pass-through switching architecture of claim 8, wherein, The straight-through adapter structure is a machining integrated structure, and the material is 06Cr19Ni10 resistant to phosphate-based hydraulic oil.

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