Aircraft clamp-type hydraulic self-sealing shutter

Abstract

The application belongs to the technical field of hydraulic systems, and particularly relates to a plane clamp type hydraulic self-sealing valve, which comprises a valve assembly and a mounting device for mounting the valve assembly on a landing gear; the valve assembly comprises a shell (5) fixed on the mounting device and having a mounting cavity; the self-sealing valve (2) comprises an inner cavity and three interfaces connected to the inner cavity, the interfaces comprising two normally-open interfaces and one self-sealing interface, one hydraulic oil path entering the inner cavity through one normally-open interface and flowing out through the other normally-open interface, and the self-sealing interface being detachably connected to a ground hydraulic pressure gauge. The application can detect the pressure of the brake control system hydraulic pipeline through the direct connection of the ground hydraulic pressure gauge and the self-sealing valve joint, thereby ensuring the double-redundancy measurement of the important parameter of the wheel brake pressure.

Description

Technical Field

[0001] This application belongs to the field of hydraulic system technology, and specifically relates to an aircraft clamp-type hydraulic self-sealing valve. Background Technology

[0002] The aircraft braking control system is the most critical system for ensuring a smooth landing, and it has extremely high requirements for safety and reliability. Wheel brake pressure, as an essential parameter of the braking system, plays a vital role in scientific research flight tests, field troubleshooting, and fault tracing. Currently, connecting a pressure sensor to the hydraulic brake line via a T-junction is a common method for monitoring brake pressure signals. However, the working environment near the main landing gear is usually harsh, leading to frequent pressure sensor failures. Ensuring dual-redundancy detection of brake pressure signals is a problem that urgently needs to be solved.

[0003] In addition, the main landing gear struts are equipped with numerous hydraulic lines. Given the limited number of anchor points and the relatively confined space, effectively increasing the number of anchor points and reducing the mechanical interfaces with the struts to efficiently utilize the existing layout space is an important issue that needs to be considered in the design of aircraft landing gear control systems. Summary of the Invention

[0004] To address the aforementioned problems, this application provides an aircraft clamp-type hydraulic self-sealing valve, comprising:

[0005] A valve assembly and a mounting device for mounting the valve assembly on the landing gear;

[0006] The valve assembly includes:

[0007] The housing is fixed to the mounting device and has a mounting cavity;

[0008] The self-sealing valve includes an inner cavity and three interfaces connecting the inner cavity. The interfaces include two normally open interfaces and one self-sealing interface. A hydraulic oil route enters the inner cavity through one normally open interface and then flows out through the other normally open interface. The self-sealing interface is detachably connected to a ground hydraulic pressure gauge.

[0009] Preferably, the self-sealing interface includes: a cylinder, a base, a spring, and a sealing body;

[0010] The cylinder and the base are connected to form the mounting cavity. The cylinder has a sealing opening with a diameter smaller than that of the mounting cavity. The large-diameter section of the sealing body is fitted into the mounting cavity, and the small-diameter section is fitted into the sealing opening to form a seal. The spring abuts against the base and the large-diameter section, and abuts the large-diameter section against the stop of the sealing opening.

[0011] Preferably, the large-diameter section has a guide groove or guide hole for oil flow.

[0012] Preferably, the hydraulic circuit is located on the base.

[0013] Preferably, the cylinder and the base are connected by threads and sealed with a sealing ring.

[0014] Preferably, the installation device includes a clamp, a threaded seat, and a connecting bolt, with threaded seats installed at both ends of the clamp, and the connecting bolt connecting the threaded seats at both ends.

[0015] Preferably, the self-sealing interface has a dust cover on the front end.

[0016] The advantages of this application include: In the event of a pressure sensor failure or a complete power outage, the pressure of the hydraulic pipeline of the brake control system can be detected by directly connecting the ground hydraulic pressure gauge to the self-sealing valve joint, thus ensuring the dual-redundancy measurement of the important parameter of wheel brake pressure. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of a preferred embodiment of an aircraft clamp-type hydraulic self-sealing valve according to this application;

[0018] Figure 2 This is a cross-sectional view of an aircraft clamp-type hydraulic self-sealing valve. Detailed Implementation

[0019] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0020] like Figures 1-2 As shown, in order to solve the above problems, this application provides an aircraft clamp-type hydraulic self-sealing valve, comprising:

[0021] A valve assembly and a mounting device for mounting the valve assembly on the landing gear;

[0022] The valve assembly includes:

[0023] The housing 5 is fixed on the mounting device and has a mounting cavity;

[0024] The self-sealing valve 2 includes an inner cavity and three interfaces connecting to the inner cavity. The interfaces include two normally open interfaces and one self-sealing interface. A hydraulic oil route enters the inner cavity through one normally open interface and flows out through the other normally open interface. The self-sealing interface is detachably connected to a ground hydraulic pressure gauge. The normally open interface has upper and lower hydraulic nozzles that can be connected to the aircraft's braking system piping. A flange is designed in the middle of the self-sealing valve, which can be fixed to the housing using two hexagonal head bolts (left and right) and a support nut. To facilitate the installation and arrangement of numerous hydraulic brake lines on the main landing gear strut, two bolt holes are provided on each side of the housing. Multi-hole pipe clamps can be used to fix the hydraulic brake lines, improving the space utilization of the main landing gear strut.

[0025] Preferably, the self-sealing interface includes: a cylindrical body 11, a base 14, a spring 13, and a sealing body 11;

[0026] The cylindrical body 11 is connected to the base 14 to form the mounting cavity. The cylindrical body 11 has a sealing opening with a diameter smaller than that of the mounting cavity. The large-diameter section of the sealing body 11 is fitted into the mounting cavity, and the small-diameter section is fitted into the sealing opening to form a seal. The spring 13 abuts against the base 14 and the large-diameter section, and abuts the large-diameter section against the stop of the sealing opening.

[0027] Preferably, the large-diameter section has a guide groove or guide hole for oil flow.

[0028] Preferably, the hydraulic circuit is located on the base 14.

[0029] Preferably, the cylinder 11 and the base 14 are connected by threads and sealed by a sealing ring.

[0030] Preferably, the mounting device includes a clamp 3, a threaded seat 4, and a connecting bolt 5. Threaded seats 4 are installed at both ends of the clamp 3, and the connecting bolt 5 connects the threaded seats 4 at both ends. The clamp and the housing are welded together by six weld points.

[0031] Preferably, the front end of the self-sealing interface is fitted with a dust cover 1.

[0032] Two bolt holes are opened on the left and right sides of the housing welded with the clamp, which can be used to install two multi-hole pipe clamps, making it easy to fix the pipeline on the main lifting support and greatly improving the space utilization of the main lifting support.

[0033] When using a clamp-type self-sealing valve for brake pressure testing, first remove the dust cover at the front of the product. Manually connect the ground hydraulic pressure gauge and the self-sealing valve directly. During the connection process, the self-sealing valve is pushed open, and the two form a new sealing pair, quickly connecting and locking together, creating a hydraulic flow channel inside. Then, input the hydraulic medium pressure to test the brake pressure. When separation is required, remove the ground hydraulic pressure gauge, and the two will disengage. The self-sealing valve will return to its original position and close under the action of its internal spring, achieving self-sealing without affecting the continued use of the product on the machine.

[0034] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An aircraft clamp-type hydraulic self-sealing valve, characterized in that, include: A valve assembly and a mounting device for mounting the valve assembly on the landing gear; The valve assembly includes: The housing (5) is fixed on the mounting device and has a mounting cavity; The self-sealing valve (2) includes an inner cavity and three interfaces connected to the inner cavity. The interfaces include two normally open interfaces and one self-sealing interface. A hydraulic oil route enters the inner cavity through one normally open interface and then flows out through the other normally open interface. The self-sealing interface is detachably connected to the ground hydraulic pressure gauge.

2. The aircraft clamp-type hydraulic self-sealing valve as described in claim 1, characterized in that, The self-sealing interface includes: a cylinder (11), a base (14), a spring (13), and a sealing body (11). The cylindrical body (11) is connected to the base (14) to form the mounting cavity. The cylindrical body (11) has a sealing opening with a diameter smaller than that of the mounting cavity. The large-diameter section of the sealing body (11) is fitted into the mounting cavity, and the small-diameter section is fitted into the sealing opening to form a seal. The spring (13) abuts against the base (14) and the large-diameter section, and abuts the large-diameter section against the stop of the sealing opening.

3. An aircraft clamp-type hydraulic self-sealing shutter as claimed in claim 2, characterized in that, The large-diameter section has guide grooves or guide holes for oil flow.

4. The aircraft clamp-type hydraulic self-sealing shutter of claim 2 wherein, The hydraulic circuit is located on the base (14).

5. The aircraft clamp-type hydraulic self-sealing shutter as defined in claim 2 wherein, The cylinder (11) and the base (14) are connected by threads and sealed by a sealing ring.

6. The aircraft clamp-type hydraulic self-sealing shutter of claim 1 wherein, The mounting device includes a clamp (3), a threaded seat (4), and a connecting bolt (5). The threaded seats (4) are installed at both ends of the clamp (3), and the connecting bolt (5) connects the threaded seats (4) at both ends.

7. The aircraft clamp-type hydraulic self-sealing shutter of claim 2 wherein, The self-sealing interface is fitted with a dust cover at the front end (1).

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