Connection type spaceflight valve device

Abstract

The utility model relates to the technical field of valve devices, and discloses a connection type spaceflight valve device which comprises a valve body and two valve bodies arranged at the two ends of the valve body, the end, away from the valve body, of one valve body is connected with a flange, and the end, away from the valve body, of the flange is provided with a small isolation flange gasket. The valve body comprises a valve ball, a valve rod, a connecting cover, a low-temperature RPTFE packing combination, a spinning cover and an anti-loosening assembly. The upper end and the lower end of the low-temperature RPTFE filler combination are connected to the interior of the connecting cover by adopting an embedded structure; the rotary pressing cover is rotationally mounted in the connecting cover through threads, and the rotary pressing cover is pressed in the connecting cover through the anti-loosening assembly; the anti-loosening assembly comprises a clamp and a clamp spring gasket. Through the triple sealing structure of the metal sealing ring, the low-temperature RPTFE packing combination and the small isolation flange gasket, the sealing grade is effectively improved, the sealing stability is enhanced, the device is suitable for vacuum, low-temperature and special atmosphere environments, and the high requirement of an aerospace system for the sealing performance is met.

Description

Technical Field

[0001] This utility model relates to the field of valve device technology, specifically to a connecting aerospace valve device. Background Technology

[0002] With the development of aerospace technology and the increase in deep space exploration missions, various spacecraft, exploration devices and extraterrestrial operation platforms have placed higher demands on the sealing performance, reliability and environmental adaptability of fluid transport and control systems. As a key component for controlling the flow of media, the structural stability, sealing effect and resistance to extreme environments of valves are directly related to the operational safety of aerospace systems and the success or failure of missions.

[0003] Existing aerospace valve structures mostly adopt a combination of traditional metal seals and elastic seals. However, in the low-temperature, low-pressure, and high-vibration environments of outer space such as the moon and Mars, the sealing materials are prone to cold contraction, hardening, or fatigue, leading to seal failure and causing problems such as media leakage, electrical short circuits, or component malfunction. In addition, traditional tightening parts are prone to loosening under repeated opening and closing or high-frequency vibration conditions, reducing the service life and stability of the overall sealing assembly.

[0004] On the other hand, the existing threaded assembly structure used for valve clamping is relatively simple and generally lacks self-locking, limiting or anti-loosening functions, making it difficult to meet the reliable connection requirements under complex working conditions. At the same time, in some special application scenarios, such as the interface connection between spacecraft and external energy systems, multiple isolations are required to avoid damage to electrical components caused by conductivity. However, traditional sealing structures can usually only achieve one or two seals, making it difficult to achieve high-level insulation and vacuum isolation effects.

[0005] In view of the above, this application proposes a connecting aerospace valve device to solve the above problems. It has stronger sealing performance, anti-loosening and self-locking function, and is adaptable to extreme low temperature and vacuum environments. This improves the safety, stability and reliability of media control and transmission in aerospace systems and meets the needs of more complex and demanding aerospace missions in the future. Utility Model Content

[0006] To address the shortcomings of existing technologies, this utility model provides a connecting aerospace valve device, which solves the problems mentioned in the background section.

[0007] To achieve the above objectives, this utility model provides the following technical solution:

[0008] A connecting aerospace valve device includes a valve body and two valve bodies disposed at both ends of the valve body. One valve body is connected to a flange at the end away from the valve body. A small isolation flange gasket is provided on the end of the flange away from the valve body. The valve body includes a valve ball, a valve stem, a connecting cover, a cryogenic RPTFE packing assembly, a spin cap, and an anti-loosening component.

[0009] The low-temperature RPTFE packing assembly is connected to the inside of the connecting cover by an embedded structure at both ends; the screw cap is installed inside the connecting cover by screw thread rotation, and the screw cap is pressed into the connecting cover by the anti-loosening component;

[0010] The anti-loosening component includes a clamp and a retaining spring washer.

[0011] Optionally, the valve ball is located inside the valve body.

[0012] Optionally, the connecting cover is disposed on the valve body corresponding to the valve ball.

[0013] Optionally, the valve stem passes through the cryogenic RPTFE packing assembly, the spin cap, and the anti-loosening component to connect with the valve ball.

[0014] Optionally, the spin cap includes a cylindrical body with a large diameter and a connecting post with a small diameter. The connecting post is coaxially disposed at the center of the lower end of the cylindrical body, and the cylindrical body and the connecting post are integrally formed to form a T-shaped structure.

[0015] Optionally, the clamp and the retaining spring washer are connected by elastic engagement, and the clamp achieves a stable assembly of the connecting cover by pressing against the retaining spring washer.

[0016] This utility model provides a connecting aerospace valve device, which has the following advantages:

[0017] 1. The device uses a triple sealing structure consisting of a metal sealing ring, a combination of cryogenic RPTFE packing, and a small isolation flange gasket to effectively improve the sealing level and enhance sealing stability. It is suitable for vacuum, cryogenic, and special atmosphere environments, meeting the high sealing requirements of aerospace systems.

[0018] 2. The elastic engagement structure of the clamp and spring washer can automatically compensate for stress changes caused by external vibration, pressure difference and temperature difference during long-term use, effectively prevent the screw cap from loosening, ensure the long-term stable operation of the system, and improve the reliability and life of the device.

[0019] 3. The embedded structure provides flexible compensation in the radial and axial directions, maintaining good sealing and flexibility even in low-temperature (-100℃) environments, preventing material hardening or failure.

[0020] 4. The introduction of small isolation flange gaskets can effectively prevent damage to components caused by electrical conductivity and enhance the dielectric insulation effect between the valve body and the external body, making it suitable for aerospace mission scenarios with low-pressure environments such as the lunar surface. Attached Figure Description

[0021] Figure 1This is a schematic diagram of the structure of this utility model;

[0022] Figure 2 This is a schematic diagram of the planar structure of this utility model;

[0023] Figure 3 This is a cross-sectional structural diagram of the present invention.

[0024] In the diagram: 1. Valve body; 2. Valve body; 21. Valve ball; 22. Valve stem; 23. Connecting cover; 24. Low-temperature RPTFE packing assembly; 25. Swivel cover; 251. Cylindrical body; 252. Connecting column; 26. Anti-loosening component; 261. Clamp; 262. Snap ring gasket; 3. Flange; 4. Small isolation flange gasket. Detailed Implementation

[0025] In order to make the technical means, creative features, objectives and effects of this utility model easier to understand, the present utility model will be further described below in conjunction with specific embodiments.

[0026] In the description of this utility model, it should be understood that the terms "lateral", "longitudinal", "end", "edge", "sidewall", "upper", "lower", "upper part", "lower part", "directly above", "surface", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "axial", "radial", "circumferential", "end", "head", "tail", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the technical solution of this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0027] This application proposes a connecting aerospace valve device, which mainly consists of a valve body 1, two valve bodies 2 disposed at both ends of the valve body 1, a flange 3 connected to one side of the valve body 2, and a small isolation flange gasket 4 disposed on the flange 3. Through the coordinated arrangement of multiple sets of structures, it achieves a better sealing and isolation effect.

[0028] For reference Figure 1-3 The valve body 1 is connected to two valve bodies 2 at both ends. The connection is a common existing technology and will not be described in detail in this application.

[0029] For reference Figure 1-3A flange 3 is provided on a valve body 2 connected to one end of the valve body 1. A small isolation flange gasket 4 is provided on the end of the flange 3 away from the valve body 2. The small isolation flange gasket 4 adds a sealing structure when the flange 3 is connected to the external body. The existing flange 3 is provided with a metal sealing ring as the first seal, and the low temperature RPTFE packing combination 24 is the second seal. The added small isolation flange gasket 4 is the third seal, which promotes the use of a three-stage vacuum sealing structure to isolate the valve body 2 from the external body equipment, prevent electrical conduction from damaging the electrical components of the body, and at the same time achieve a vacuum effect in the lunar atmosphere.

[0030] For reference Figure 1-3 The valve body 2 includes a valve ball 21, a valve stem 22, a connecting cover 23, a cryogenic RPTFE packing assembly 24, a spin cap 25, and an anti-loosening component 26. The valve ball 21 is located inside the valve body 1, and the connecting cover 23 is mounted on the valve body 1 corresponding to the valve ball 21. The valve stem 22 passes through the cryogenic RPTFE packing assembly 24, the spin cap 25, and the anti-loosening component 26 and is connected to the valve ball 21. The valve ball 21 rotates through the valve stem 22.

[0031] It should be noted that the valve ball 21, valve stem 22, and connecting cover 23 are common structures in existing valve devices and will not be described in detail here.

[0032] Specifically, the low-temperature RPTFE packing assembly 24 is connected to the inside of the connecting cover 23 by an embedded structure at both the upper and lower ends. The embedded structure of the low-temperature RPTFE packing assembly 24 includes an upper groove and a lower flange, which cooperate to form a limit, so that the sealing packing can achieve two-way compensation in the radial and axial directions under pressure, and can play a temperature protection role at a low temperature of -100 degrees.

[0033] The screw cap 25 is installed inside the connecting cap 23 by rotating the screw threads. The screw threads of the screw cap 25 have a trapezoidal thread structure and a self-locking function. It can maintain a stable clamping force after multiple opening and closing operations, so that the internal seal can achieve a strict sealing effect.

[0034] Furthermore, the spin cap 25 includes a large-diameter cylindrical body 251 and a small-diameter connecting post 252. The connecting post 252 is coaxially disposed at the center of the lower end of the cylindrical body 251. The cylindrical body 251 and the connecting post 252 are integrally formed to form a T-shaped structure. The large-diameter cylindrical body 251 in the T-shaped structure can provide a larger contact surface, increase the force-bearing area during the spin process, and enable the spin cap to generate greater axial pressure during the tightening process, thereby enhancing the compression and sealing ability of the sealing packing. The small-diameter connecting post 252 is inserted into the container or sealing cavity as a limiting shaft (or guide post). Its length and diameter can limit the pressing depth of the spin cap, preventing damage to internal components or the low-temperature RPTFE packing assembly 24 due to excessive screwing.

[0035] In view of the above, the spinning cap 25 of the present invention adopts a T-shaped structure, which is formed by coaxially and integrally molding a large-diameter cylindrical body 251 and a small-diameter connecting post 252. The connecting post 252 is located at the center of the lower end of the cylindrical body 251. Through this structure, the pressing effect during spinning and sealing can be effectively enhanced. At the same time, the connecting post 252 realizes the guiding positioning and limiting functions, ensuring the stability and sealing reliability during the spinning process, and reducing assembly errors and manufacturing costs. It has the advantages of compact structure, strong sealing performance, and stable installation.

[0036] For reference Figure 1-3 The screw cap 25 is pressed into the connecting cap 23 by the anti-loosening component 26, wherein the anti-loosening component 26 includes a clamp 261 and a retaining spring washer 262. The clamp 261 and the retaining spring washer 262 are connected by elastic engagement. The clamp 261 achieves a stable assembly of the connecting cap 23 by pressing against the retaining spring washer 262.

[0037] The elastic engagement structure between the clamp 261 and the retaining spring washer 262 provides a continuous reaction force when the cap is subjected to vibration, pressure difference, or temperature difference changes, effectively preventing loosening or rotational displacement of the cap during use and improving the long-term stability of the system seal. This structural design effectively prevents loosening of the cap due to vibration or long-term use, while also providing limiting, self-locking, and vibration-resistant functions. Furthermore, its simple structure, easy assembly, and convenient maintenance enhance the safety and reliability of the overall sealing assembly.

[0038] In this utility model, the assembly steps of the device are as follows:

[0039] Install the valve ball and valve stem:

[0040] Install the valve ball 21 in the middle of the valve body 1; insert the valve stem 22 from the top of the connecting cover 23, pass through the cryogenic RPTFE packing assembly 24, and connect it to the valve ball 21.

[0041] Loading the cryogenic packing assembly:

[0042] The low-temperature RPTFE packing assembly 24 is embedded into the connecting cover 23 in an embedded structure (upper groove and lower flange) to ensure a firm positioning.

[0043] Install the screw cap:

[0044] T-shaped screw cap 25 (including cylindrical body 251 and connecting column 252) is screwed into the internal thread of connecting cap 23 along the thread direction. The trapezoidal thread structure provides a self-locking effect. Tighten to the specified depth to compress the packing assembly.

[0045] Install anti-loosening components:

[0046] Press the retaining spring washer 262 onto the corresponding groove or stop of the connecting cover 23; fit the clamp 261 and connect it to the retaining spring washer 262 through elastic engagement to form a limiting and pressing structure to prevent the screw cap 25 from loosening due to vibration or thermal expansion and contraction.

[0047] Connect the flange structure and complete the three seals: install the valve body 2 with flange 3 to both ends of the valve body 1 and connect it with the external body; install a small isolation flange gasket 4 as the third seal at the end of flange 3 near the external body; at the same time, the metal sealing ring on flange 3 is the first seal, and the low temperature packing combination is the second seal, forming a triple vacuum sealing barrier.

[0048] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments, and various changes and modifications can be made without departing from the spirit and scope of this utility model. All such changes and modifications fall within the scope of protection claimed by this utility model. The scope of protection of this utility model is defined by the appended claims and their equivalents.

Claims

1. A connecting aerospace valve device, characterized in that: It includes a valve body (1) and two valve bodies (2) disposed at both ends of the valve body (1), wherein a flange (3) is connected to the end of one valve body (2) away from the valve body (1), and a small isolation flange gasket (4) is provided on the end of the flange (3) away from the valve body (2). The valve body (2) includes a valve ball (21), a valve stem (22), a connecting cover (23), a low temperature RPTFE packing assembly (24), a spin cap (25), and an anti-loosening component (26). The low-temperature RPTFE packing assembly (24) is connected to the inside of the connecting cover (23) by an embedded structure at both ends; the screw cap (25) is installed in the connecting cover (23) by screw rotation, and the screw cap (25) is pressed in the connecting cover (23) by the anti-loosening component (26); The anti-loosening component (26) includes a clamp (261) and a retaining spring washer (262).

2. The connecting aerospace valve device according to claim 1, characterized in that: The valve ball (21) is located inside the valve body (1).

3. The connecting aerospace valve device according to claim 1, characterized in that: The connecting cover (23) is disposed on the valve body (1) corresponding to the valve ball (21).

4. The connecting aerospace valve device according to claim 1, characterized in that: The valve stem (22) passes through the low-temperature RPTFE packing assembly (24), the swivel cap (25), and the anti-loosening component (26) and is connected to the valve ball (21).

5. The connecting aerospace valve device according to claim 1, characterized in that: The spun cap (25) includes a cylindrical body (251) with a large diameter and a connecting post (252) with a small diameter. The connecting post (252) is coaxially arranged at the center of the lower end of the cylindrical body (251). The cylindrical body (251) and the connecting post (252) are integrally formed and connected to form a T-shaped structure.

6. The connecting aerospace valve device according to claim 1, characterized in that: The clamp (261) and the spring washer (262) are connected by elastic engagement, and the clamp (261) achieves a stable assembly of the connecting cover (23) by pressing against the spring washer (262).

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