CN112627663A

CN112627663A - Aircraft valve opening mechanism

Info

Publication number: CN112627663A
Application number: CN202011395109.1A
Authority: CN
Inventors: 孟令赛; 孙智孝; 贺集乐; 张健; 许灯顺
Original assignee: Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Current assignee: Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Priority date: 2020-12-03
Filing date: 2020-12-03
Publication date: 2021-04-09

Abstract

The application belongs to the field of aircraft valve structures, and particularly relates to an aircraft valve opening mechanism. The method comprises the following steps: the device comprises a valve (1), a sliding rail (2), a sliding block (3) and a driver (4). The sliding rail (2) comprises a sliding section and a rotating section; the sliding block (3) is arranged in the sliding rail (2), and the sliding block (3) is connected with the valve (1) through a connecting rod; the driver (4) is connected with the connecting rod; the opening position of the valve (1) is controlled by driving the sliding block (3) to slide in the sliding section of the sliding rail (2) through the driver (4), and the opening angle of the valve (1) is controlled by driving the sliding block (3) to rotate in the rotating section of the sliding rail (2) through the driver (4). The utility model provides an aircraft valve opening mechanism can make the valve open according to the position of regulation to the opening that stealthy sawtooth design brought is eliminated and is interfered the problem, and simple structure easily operates.

Description

Aircraft valve opening mechanism

Technical Field

The application belongs to the field of aircraft valve structures, and particularly relates to an aircraft valve opening mechanism.

Background

With the improvement of aviation science and technology, the stealth technology of the airplane is developed unprecedentedly, and the fighting efficiency of the airplane is greatly improved. The valve which needs to be opened on the airplane is huge in damage to the stealth of the airplane, so that a zigzag design is needed, however, the problem of valve opening interference caused by the zigzag design is solved, and special requirements are provided for the opening mode of the valve. Meanwhile, the opening positions of some valves have special requirements, and a special opening mode is also needed to ensure that the valves can be opened according to the specified positions. And the general structure of the valve opening mode in the prior art is more complicated and the cost is high.

Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.

Disclosure of Invention

The application aims to provide an aircraft valve opening mechanism to solve at least one problem existing in the prior art.

The technical scheme of the application is as follows:

an aircraft valve opening mechanism comprising:

a shutter;

the sliding rail comprises a sliding section and a rotating section;

the sliding block is arranged in the sliding rail and is connected with the valve through a connecting rod;

a driver connected with the connecting rod;

the opening position of the valve is controlled by driving the sliding block to slide in the sliding section of the sliding rail through the driver, and the opening angle of the valve is controlled by driving the sliding block to rotate in the rotating section of the sliding rail through the driver.

Optionally, the front end and the rear end of the shutter are both serrated.

Optionally, the slide rail includes left slide rail and right slide rail, the left end of slider is installed in the left slide rail, the right-hand member of slider is installed in the right slide rail.

Optionally, the rotating sections of the left slide rail and the right slide rail are circular, and the front end surface and the rear end surface of the slider are both arc surfaces matched with the rotating sections.

Optionally, an angle limiting block is arranged in each of the rotating sections of the left slide rail and the right slide rail.

Optionally, the actuator is a ram.

The invention has at least the following beneficial technical effects:

the aircraft valve opening mechanism can enable the valve to be opened according to the specified position, eliminates the opening interference problem caused by stealth sawtooth design, is a valve opening mode capable of solving the problem of harsh position requirements, and is simple in structure and easy to operate.

Drawings

FIG. 1 is a schematic view of an aircraft valve opening mechanism in accordance with one embodiment of the present application;

figure 2 is a cross-sectional view of an aircraft shutter opening mechanism according to one embodiment of the present application.

Wherein:

1-a valve; 2-a slide rail; 3-a slide block; 4-a driver; 5-angle limiting block.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. 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 a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.

In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.

The present application is described in further detail below with reference to fig. 1-2.

The application provides an aircraft valve opening mechanism includes: the device comprises a valve 1, a slide rail 2, a slide block 3 and a driver 4.

Specifically, as shown in fig. 1, the sliding rail 2 is designed with a sliding section and a rotating section, which can guide the shutter 1 to slide and rotate, and the rotating section can be arranged at one end of the sliding section; the sliding block 3 is matched with the sliding rail 2, is arranged in the sliding rail 2, can slide in the sliding section of the sliding rail 2 and rotate in the rotating section, and is provided with a connecting rod by welding or integral forming, and the connecting rod is connected with the valve 1; the driver 4 is connected with the connecting rod, and the control of the valve 1 is realized by driving the sliding block 3 connected with the connecting rod to move.

The utility model provides an aircraft valve opening mechanism slides in the sliding section of slide rail 2 through 4 drive sliders 3 of driver, controls the open position of valve 1, and is rotatory in the rotation section of slide rail 2 through 4 drive sliders 3 of driver, controls the opening angle of valve 1.

In one embodiment of the present application, in order to increase the stealth effect, both the front end and the rear end of the shutter 1 are provided in a zigzag shape.

In an embodiment of the present application, the slide rail 2 includes two, left slide rail and right slide rail, and slider 3 is rectangular form, and the left end of slider 3 is installed in left slide rail, and the right-hand member of slider 3 is installed in right slide rail, improves valve driven stability.

In this embodiment, as shown in fig. 2, the sliding section of the left slide rail and the sliding section of the right slide rail of the slide rail 2 are long, the rotating section is circular, the front end face and the rear end face of the slider 3 are circular arc faces matched with the rotating section, when the slider 3 moves to the rotating section, the front end face and the rear end face of the slider are respectively matched with the inner wall face of the rotating section, under the driving of the driver 4, the front end face rotates downwards, the rear end face rotates upwards, the slider 3 rotates in the rotating section, and therefore the opening angle of the valve 1 is driven.

Advantageously, in this embodiment, the angle limiting blocks 5 are respectively disposed on the inner wall surfaces of the rotation sections of the left slide rail and the right slide rail of the slide rail 2, so as to limit the valve 2 when the valve rotates to a predetermined angle, and the opening angle of the wall surface valve 2 is transited.

In one embodiment of the application, the driver 4 may be of any suitable driving form, such as a ram.

The utility model provides an aircraft valve opening mechanism can make the valve open according to the position of regulation to the opening that eliminates stealthy sawtooth design and bring interferes the problem, is one kind and can solves the form that opens to the harsh valve of position requirement. The application has simple structure and easy operation.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. An aircraft valve opening mechanism, comprising:

a shutter (1);

the sliding rail (2) comprises a sliding section and a rotating section;

the sliding block (3) is installed in the sliding rail (2), and the sliding block (3) is connected with the valve (1) through a connecting rod;

a driver (4), the driver (4) being connected with the connecting rod;

the opening position of the valve (1) is controlled by driving the sliding block (3) to slide in the sliding section of the sliding rail (2) through the driver (4), and the opening angle of the valve (1) is controlled by driving the sliding block (3) to rotate in the rotating section of the sliding rail (2) through the driver (4).

2. An aircraft shutter opening mechanism according to claim 1, characterised in that the front and rear ends of the shutter (1) are serrated.

3. An aircraft shutter opening mechanism according to claim 2, characterized in that the slide (2) comprises a left slide in which the left end of the slider (3) is mounted and a right slide in which the right end of the slider (3) is mounted.

4. An aircraft shutter opening mechanism according to claim 3, characterized in that the rotation sections of the left and right slide rails are circular, and the front end face and the rear end face of the slider (3) are both circular arc faces adapted to the rotation sections.

5. An aircraft shutter opening mechanism according to claim 4, characterized in that an angle limiting block (5) is arranged in the rotation section of the left slide rail and the right slide rail.

6. An aircraft shutter opening mechanism according to claim 1, wherein the actuator (4) is a ram.