CN108458142B - One-way pressure relief valve suitable for spacecraft cabin pressure control - Google Patents
One-way pressure relief valve suitable for spacecraft cabin pressure control Download PDFInfo
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- CN108458142B CN108458142B CN201711405854.8A CN201711405854A CN108458142B CN 108458142 B CN108458142 B CN 108458142B CN 201711405854 A CN201711405854 A CN 201711405854A CN 108458142 B CN108458142 B CN 108458142B
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- piston
- valve body
- pressure relief
- pressure
- adjusting nut
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K17/00—Safety valves; Equalising valves, e.g. pressure relief valves
- F16K17/02—Safety valves; Equalising valves, e.g. pressure relief valves opening on surplus pressure on one side; closing on insufficient pressure on one side
- F16K17/04—Safety valves; Equalising valves, e.g. pressure relief valves opening on surplus pressure on one side; closing on insufficient pressure on one side spring-loaded
- F16K17/06—Safety valves; Equalising valves, e.g. pressure relief valves opening on surplus pressure on one side; closing on insufficient pressure on one side spring-loaded with special arrangements for adjusting the opening pressure
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K15/00—Check valves
- F16K15/02—Check valves with guided rigid valve members
- F16K15/025—Check valves with guided rigid valve members the valve being loaded by a spring
- F16K15/026—Check valves with guided rigid valve members the valve being loaded by a spring the valve member being a movable body around which the medium flows when the valve is open
- F16K15/028—Check valves with guided rigid valve members the valve being loaded by a spring the valve member being a movable body around which the medium flows when the valve is open the valve member consisting only of a predominantly disc-shaped flat element
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K17/00—Safety valves; Equalising valves, e.g. pressure relief valves
- F16K17/02—Safety valves; Equalising valves, e.g. pressure relief valves opening on surplus pressure on one side; closing on insufficient pressure on one side
- F16K17/04—Safety valves; Equalising valves, e.g. pressure relief valves opening on surplus pressure on one side; closing on insufficient pressure on one side spring-loaded
- F16K17/08—Safety valves; Equalising valves, e.g. pressure relief valves opening on surplus pressure on one side; closing on insufficient pressure on one side spring-loaded with special arrangements for providing a large discharge passage
- F16K17/082—Safety valves; Equalising valves, e.g. pressure relief valves opening on surplus pressure on one side; closing on insufficient pressure on one side spring-loaded with special arrangements for providing a large discharge passage with piston
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Safety Valves (AREA)
Abstract
The invention discloses a one-way pressure release valve suitable for spacecraft cabin pressure control, which comprises a valve body, a sealing gasket, a piston, a spring, a transition flange, a compression nut and an adjusting nut. The invention realizes automatic pressure relief and closing by sensing the pressure difference of the internal environment and the external environment of the reentry capsule through the pressure sensing element, and has the functions of closing and heat protection, small weight of the spacecraft, less resource consumption and simple pressure control mode.
Description
Technical Field
The invention relates to the technical field of spacecraft environment control, in particular to a one-way pressure release valve suitable for spacecraft cabin pressure control.
Background
The spacecraft reentry capsule can be used for manned detection, lunar detection and space science tests. In the rocket launching stage, the atmospheric density and the atmospheric pressure outside the returning capsule are rapidly reduced along with the increase of the flying height, and in order to ensure that the structure of the returning capsule body is not damaged, a one-way pressure relief valve is required to reduce the pressure in the returning capsule to be within a specified pressure value range. In the reentry stage of the return cabin, the valve has the function of closing and heat protection, and instrument and equipment in the return cabin are guaranteed not to be damaged.
At present, an electric control valve in the aerospace one-way valve is common. The electric control valve is used for sensing the environmental pressure by a sensor, and the valve is closed in an electric control mode, so that the defects of large size, heavy weight and consumption of electric resources of a spacecraft for operation are overcome.
Disclosure of Invention
In view of the above, the invention provides a one-way pressure release valve suitable for spacecraft cabin pressure control, which can realize automatic pressure release and closing, has a closing and heat-proof function, and is small in weight of a spacecraft, low in resource consumption and simple in pressure control mode.
The specific embodiment of the invention is as follows:
a one-way pressure relief valve suitable for spacecraft cabin pressure control comprises a valve body, a sealing gasket, a piston, a spring, a transition flange, a compression nut and an adjusting nut;
the bottom of the valve body is provided with a pressure relief opening, and the top of the valve body is fixedly connected with a transition flange; the piston comprises a piston body and a piston rod, the piston body is matched with the valve body, the spring is sleeved on the piston rod and is in contact with the adjusting nut, the adjusting nut is fixedly connected with the valve body, and under the action of the adjusting nut, the spring is compressed to enable the end face of the piston body to seal the base of the valve body through the sealing gasket to seal the pressure relief opening; the compression nut is fixedly connected with the valve body and compresses the end face of the adjusting nut; when the pressure relief valve is opened, the pressure relief opening, the end face of the piston body, the compression nut, the adjusting nut and the transition flange form a passage for transmitting pressure in the cabin together, and the pressure relief value of the one-way pressure relief valve is adjusted by changing the precompression amount of the spring.
Furthermore, the sealing gasket is in contact with a knife edge of the valve body base, and the sealing gasket is installed in a sealing groove of the piston.
Furthermore, the adjusting nut is provided with an extension rod, and the extension rod is in sliding fit with the piston rod.
Furthermore, the piston rod is hollow, and a plurality of through holes are processed on the piston rod.
Has the advantages that:
1. in the stage that the spacecraft ascends along with the rocket, the pressure sensing element senses the pressure difference between the inside and the outside of the reentry module, so that the pressure relief and the closing can be automatically realized; the valve is closed through the pretightening force of the spring and the pressure difference between the inside and the outside of the returning capsule, the heat-proof function is achieved in the reentry stage, the effects of reducing the weight of the spacecraft and reducing the resource consumption are achieved, and the pressure control mode is simple. Secondly, the pretightening force of the pressure sensing element is adjusted by adjusting the mounting height of the nut, and the pressure relief point of the valve is accurately controlled.
2. The sealing gasket of the invention is contacted with the knife edge of the valve body base, the pressure is large, the sealing is tight, the vulcanization process between the sealing gasket and the sealing groove is avoided, and the cost is low.
3. The piston rod is hollow inside, and a plurality of through holes are processed on the piston rod, so that the weight is reduced, the flow area of gas is increased, and the pressure relief and the closing are quickly realized.
Drawings
FIG. 1 is a schematic view of the installation position of the present invention in a return leg;
FIG. 2 is a schematic cross-sectional view of the closed configuration of the present invention;
FIG. 3 is a schematic sectional view of the structure of the present invention at the time of opening;
fig. 4 is a top view of fig. 2.
The valve comprises a valve body 1, a sealing gasket 2, a piston 3, a spring 4, a screw 5, an elastic gasket 6, a flat gasket 7, a transition flange 8, a sealing ring 9, a compression nut 10 and an adjusting nut 11.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention provides a one-way pressure release valve suitable for spacecraft cabin pressure control, which comprises a valve body 1, a sealing gasket 2, a piston 3, a spring 4, a screw 5, a transition flange 8, a compression nut 10 and an adjusting nut 11, as shown in figure 2.
The piston 3 comprises a piston body and a piston rod, a sealing groove for installing the sealing gasket 2 is machined in the end face of the piston body, a through hole for communicating the outside of the valve body 1 with the inside of the piston 3 is machined in the end face of the piston body, and a limiting groove for limiting the position of the spring 4 is machined in the piston body. The piston rod is hollow, and a plurality of through holes are processed on the piston rod.
As shown in fig. 4, the transition flange 8, the compression nut 10 and the adjusting nut 11 are all hollow structures.
The piston body and the inner wall of the lower part of the valve body 1 are in sliding fit, the end face of the piston body is in sealing contact with the base of the valve body 1 through the sealing gasket 2, the sealing gasket 2 is in knife edge contact with the base of the valve body 1, the sealing gasket 2 is installed in a sealing groove of the piston body, and meanwhile, the sealing gasket 2 seals a through hole which communicates the end face of the piston body with the outside of the valve body 1 and the. The adjusting nut 11 is in threaded connection with the inner wall of the upper portion of the valve body 1, meanwhile, an extension rod of the adjusting nut 11 is in sliding fit with the piston rod to play a role in guiding and ensure movement of the piston rod in the vertical direction, the spring 4 is sleeved on the extension rod of the adjusting nut 11 and the piston rod, one end of the spring is limited by a clamping groove of the adjusting nut 11, and the other end of the spring is limited by a limiting groove of the piston body. The compression nut 10 is in threaded connection with the inner wall of the valve body 1, compresses the end face of the adjusting nut 11, and is tightly connected with the adjusting nut 11 through friction force between the compression nut 10 and the adjusting nut 11.
As shown in fig. 1, the valve body 1 is connected to an external device through a transition flange 8, and the transition flange 8 is fixedly mounted on the valve body 1 through a screw 5, an elastic pad 6 and a flat pad 7. The base of the valve body 1 is connected with the inside of the spacecraft cabin, the base of the valve body 1 is opened, and the pressure in the cabin is transmitted out through the base of the valve body 1, the end face of the piston body, the compression nut 10, the adjusting nut 11 and the transition flange 8 to be decompressed.
The piston 2, the spring 4, the adjusting nut 11 and the pressing nut 10 form a pressure sensing element with a limiting function. In the ground stage, the pressure relief value of the one-way pressure relief valve can be adjusted by adjusting the installation heights of the adjusting nut 11 and the compression nut 10 in the valve body 1 and changing the compression amount of the spring 4 to adjust the pre-tightening force of the spring according to the pressure requirement in the spacecraft reentry module.
In the launching stage of the spacecraft reentry capsule along with the rocket, the valve senses the ambient pressure difference inside and outside the capsule through the pressure sensing element to realize automatic pressure relief along with the reduction of the air pressure outside the reentry capsule, and the valve is automatically closed after the air pressure inside the capsule reaches a specified value. In the reentry stage of the spacecraft reentry stage, the valve is closed through the pretightening force of the spring and the pressure difference between the inside and the outside of the reentry stage, so that the heat of the reentry stage of the reentr.
According to the requirement of the spacecraft re-entry capsule structure on the air pressure in the capsule, the pressure relief point, namely the pressure relief value, needs to be set, and the pressure sensing element is obtained by manually debugging the pressure sensing element. The debugging process is as follows: unscrewing and detaching the screw 5, the elastic pad 6 and the flat pad 7, taking the transition flange 8 down, taking the compression nut 10 out by using a tool, adjusting the installation height of the adjusting nut 11 to a designed value by using the tool, wherein the compression amount of the spring 4 is changed, and the pretightening force is correspondingly changed. The compression nut 10 is installed in the valve body 1, the compression nut 10 and the adjusting nut 11 are screwed tightly through a tool, then the transition flange 8 is installed on the valve body 1, and fixation is achieved through the screwing screw 5, the elastic pad 6 and the flat pad 7.
The working process is as follows: the one-way pressure relief valve is installed in the spacecraft return cabin through the valve body 1. In the ground stage, the one-way pressure release valve is in a closed state, and the air pressure in the returning cabin is consistent with the ambient air pressure; in the rocket launching stage, the air pressure outside the returning cabin is reduced, the air pressure in the returning cabin keeps the ground pressure value, the direction of the pressure difference between the inside and the outside of the cabin is opposite to the direction of the pretightening force of the spring 4 and is gradually offset, when the pretightening force of the spring 4 is overcome, the atmospheric pressure outside the returning cabin reaches a pressure relief point at the moment, the air pressure in the cabin drives the piston 3 to move, the valve is opened to relieve the pressure, as shown in figure 3, the air pressure in the returning cabin is reduced, the pressure difference between the inside and the outside of the cabin is gradually reduced, and when the air pressure in the returning cabin reaches a specified air.
In the reentry stage of the spacecraft, the air pressure in the returning cabin keeps a specified air pressure value, the air pressure outside the returning cabin rises, the pressure difference between the inside and the outside of the returning cabin is consistent with the pretightening force direction of the spring 4 and gradually increases, namely the pressure outside the returning cabin compresses the piston all the time, the valve is ensured to be closed, and the heat is prevented from entering the returning cabin.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (3)
1. A one-way pressure relief valve suitable for spacecraft cabin pressure control is characterized by comprising a valve body, a sealing gasket, a piston, a spring, a transition flange, a compression nut and an adjusting nut;
the bottom of the valve body is provided with a pressure relief opening, and the top of the valve body is fixedly connected with a transition flange; the piston comprises a piston body and a piston rod, the piston body is matched with the valve body, a through hole for communicating the outside of the valve body with the inside of the piston is processed on the end face of the piston body, the spring is sleeved on the piston rod and is in contact with an adjusting nut, the adjusting nut is provided with an extension rod, and the extension rod is in sliding fit with the piston rod; the adjusting nut is in threaded connection with the valve body, under the action of the adjusting nut, the spring is compressed to enable the end face of the piston body to seal the base of the valve body through the sealing gasket to seal the pressure relief opening, and the sealing gasket seals the through hole which communicates the end face of the piston body with the outside of the valve body and the inside of the piston; the compression nut is in threaded connection with the valve body and compresses the end face of the adjusting nut; when the pressure relief valve is opened, the pressure relief opening, the end face of the piston body, the compression nut, the adjusting nut and the transition flange form a passage for transmitting pressure in the cabin together, and the pressure relief value of the one-way pressure relief valve is adjusted by changing the precompression amount of the spring.
2. The pressure relief valve adapted for spacecraft cabin pressure control of claim 1, wherein said gasket is in contact with a knife edge of the valve body base, and said gasket is installed in a seal groove of said piston.
3. The one-way pressure relief valve for spacecraft cabin pressure control of claim 1, wherein said piston rod is hollow and has a plurality of through holes formed therein.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711405854.8A CN108458142B (en) | 2017-12-22 | 2017-12-22 | One-way pressure relief valve suitable for spacecraft cabin pressure control |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711405854.8A CN108458142B (en) | 2017-12-22 | 2017-12-22 | One-way pressure relief valve suitable for spacecraft cabin pressure control |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108458142A CN108458142A (en) | 2018-08-28 |
| CN108458142B true CN108458142B (en) | 2020-03-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711405854.8A Active CN108458142B (en) | 2017-12-22 | 2017-12-22 | One-way pressure relief valve suitable for spacecraft cabin pressure control |
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| Country | Link |
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| CN (1) | CN108458142B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110081211B (en) * | 2019-04-28 | 2020-08-18 | 贵州曼格维流体智能科技有限公司 | One-way valve for satellite attitude and orbit control propellant supply system |
| CN111219513A (en) * | 2020-01-20 | 2020-06-02 | 北京航安特机电技术有限公司 | One-level axial flow pressure reducing valve |
| CN113757420A (en) * | 2021-08-12 | 2021-12-07 | 中国石油天然气股份有限公司 | One-way valve device for oil production well |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5538276A (en) * | 1995-05-23 | 1996-07-23 | Tullis; Jay K. | Tunable air spring |
| US5755254A (en) * | 1994-08-30 | 1998-05-26 | Sherex Industries, Ltd. | Two stage pressure regulator |
| CN2714916Y (en) * | 2004-06-12 | 2005-08-03 | 叶国荣 | Water pressure regulating valve |
| CN201236974Y (en) * | 2008-07-22 | 2009-05-13 | 宁波星箭航天机械厂 | Non-return valve |
| CN202580173U (en) * | 2012-05-16 | 2012-12-05 | 丹阳市飞轮气体阀门有限公司 | Safety valve for low-temperature thermal insulation gas cylinder |
| CN204025800U (en) * | 2014-06-26 | 2014-12-17 | 华中科技大学无锡研究院 | A kind of two damping One-stage Water Hydraulic Relief Valve |
| CN206299851U (en) * | 2016-11-24 | 2017-07-04 | 新乡航空工业(集团)有限公司 | A kind of new type of safe valve locking mechanism |
-
2017
- 2017-12-22 CN CN201711405854.8A patent/CN108458142B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5755254A (en) * | 1994-08-30 | 1998-05-26 | Sherex Industries, Ltd. | Two stage pressure regulator |
| US5538276A (en) * | 1995-05-23 | 1996-07-23 | Tullis; Jay K. | Tunable air spring |
| CN2714916Y (en) * | 2004-06-12 | 2005-08-03 | 叶国荣 | Water pressure regulating valve |
| CN201236974Y (en) * | 2008-07-22 | 2009-05-13 | 宁波星箭航天机械厂 | Non-return valve |
| CN202580173U (en) * | 2012-05-16 | 2012-12-05 | 丹阳市飞轮气体阀门有限公司 | Safety valve for low-temperature thermal insulation gas cylinder |
| CN204025800U (en) * | 2014-06-26 | 2014-12-17 | 华中科技大学无锡研究院 | A kind of two damping One-stage Water Hydraulic Relief Valve |
| CN206299851U (en) * | 2016-11-24 | 2017-07-04 | 新乡航空工业(集团)有限公司 | A kind of new type of safe valve locking mechanism |
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| Publication number | Publication date |
|---|---|
| CN108458142A (en) | 2018-08-28 |
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