CN114352800A - Pilot pneumatic valve applied to rocket power system - Google Patents
Pilot pneumatic valve applied to rocket power system Download PDFInfo
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- CN114352800A CN114352800A CN202111502640.9A CN202111502640A CN114352800A CN 114352800 A CN114352800 A CN 114352800A CN 202111502640 A CN202111502640 A CN 202111502640A CN 114352800 A CN114352800 A CN 114352800A
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- ejector rod
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- 239000007788 liquid Substances 0.000 claims abstract description 132
- 238000007789 sealing Methods 0.000 claims description 23
- 239000002184 metal Substances 0.000 claims description 7
- 230000004044 response Effects 0.000 abstract description 16
- 230000000694 effects Effects 0.000 description 7
- 230000009471 action Effects 0.000 description 3
- 238000001816 cooling Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000005855 radiation Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
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Abstract
The invention provides a pilot pneumatic valve applied to a rocket power system, wherein the outer part of the pilot pneumatic valve is a shell, the end parts of the left end and the right end of the shell are sealed by a liquid path plug, the lower end of the shell is sealed by a gas path plug, the upper part of the shell is provided with an armature, the inner part of the shell is sleeved with a guide sleeve, the inner part of the guide sleeve is sleeved with a gas valve core guide sleeve along the axial direction of the guide sleeve, the outer side of the guide sleeve is provided with a liquid valve core guide sleeve between the guide sleeve and the liquid path plug along the radial direction of the guide sleeve, the gas valve core guide sleeve and the guide sleeve are provided with through holes at the axial extension line of the liquid valve core guide sleeve, a gas valve core is arranged in the gas valve core guide sleeve, a gas ejector rod is abutted against the gas valve core, a spring is arranged between the gas valve core and the gas path plug, a liquid valve core is arranged in the liquid valve core guide sleeve, and the liquid ejector rod is abutted against the liquid valve core and the spring arranged between the liquid path plug. The invention has compact structure, effectively cools the liquid path, prolongs the service life of the valve core and improves the response speed.
Description
Technical Field
The invention belongs to the technical field of electromagnetic valves in the aerospace category, and particularly relates to a pilot pneumatic valve applied to a rocket power system.
Background
When the pilot-operated electromagnetic valve is electrified, the armature drives the valve rod by means of electromagnetic force, the lower valve core of the gas circuit is opened, the upper valve core of the gas circuit is closed, gas enters the gas cavity from the lower valve core of the gas circuit, high pressure is formed in the gas cavity, pressure difference of high gas and low liquid is formed at the sealing position of the push rod of the liquid circuit, and the gas pressure pushes the main valve core of the liquid circuit to move to open the main valve port under the action of the pressure difference; when the power is off, the electromagnetic force disappears, the lower valve core of the gas circuit is closed under the action of the spring force, the upper valve core of the gas circuit is opened, the gas is communicated with the atmosphere from the upper valve core of the gas circuit, the pressure is released in the gas cavity, and the main valve core of the liquid circuit is closed and sealed under the action of the hydraulic force and the spring force. However, the existing pilot valve of a certain rocket power system generally has the following problems that firstly, the service life of the valve core is shortened due to overhigh liquid temperature in the existing scheme, and secondly, the pilot valve has the advantages of quicker opening response time and slower closing response time.
Disclosure of Invention
The technical problem solved by the invention is to provide a pilot pneumatic valve applied to a rocket power system, which can better solve the problem that the temperature of liquid in the valve is too high, the pilot pneumatic valve is applied under the working condition that continuous pulse is required during use, and a liquid medium has a working condition with higher temperature when entering a valve body, so that heat conduction can be generated among gas, a guide sleeve and the liquid due to temperature difference, the guide sleeve made of metal has good heat conductivity, the heat of the liquid is absorbed and transferred to the gas, but the heat conductivity of the gas is relatively poor, a small amount of heat conduction is generated between the gas and the metal, and meanwhile, the guide sleeve transfers energy to the gas path direction through heat radiation; meanwhile, due to the continuous pulse working condition, high-low pressure alternation can be continuously generated in the boundary direction of the air path of the guide sleeve, so that energy exchange is carried out between the air and the guide sleeve through thermal convection, partial heat of the guide sleeve and the liquid is taken away, and a certain air cooling effect is achieved. For the problems of relatively short opening response time and relatively short closing response time of the traditional pilot-operated pneumatic valve applied to a certain power system of a rocket during test, the pilot-operated pneumatic valve provided by the invention shortens the distance between an inlet and an outlet of a gas path and a liquid path and reduces the overall response time under the condition of ensuring that the opening response time is still within an index range; meanwhile, the range of the gap of the air cavity is enlarged, so that heat exchange is generated between the air and the liquid, the temperature of the air is increased by heat transfer of a liquid path medium, and the air pressure in the air cavity is slightly increased, so that the response time of the valve during closing is shortened. For the pneumatic valve, the gas path and the liquid path are separated by a longer distance, the pilot pneumatic valve integrates internal parts, shortens the distance between the gas path and the liquid path, shortens the distance between the liquid outlet and the liquid inlet, ensures that gas can reach the outer side of the liquid path cavity through the guide sleeve, participates in heat conduction, and improves the response speed.
The technical scheme adopted by the invention is as follows: a pilot pneumatic valve applied to a rocket power system is provided, the outer part is a shell, the end parts of the left end and the right end of the shell are sealed by a liquid path plug, the lower end of the shell is sealed by a gas path plug, the upper part of the shell is provided with an armature, the inner part of the shell is sleeved with a guide sleeve, the inner part of the guide sleeve is sleeved with a gas valve core guide sleeve along the axial direction of the guide sleeve, the outer side of the guide sleeve is provided with a liquid valve core guide sleeve between the guide sleeve and the liquid path plug along the radial direction of the guide sleeve, through holes are processed on the axial extension line positions of the gas valve core guide sleeve and the liquid valve core guide sleeve to form a cross-shaped through cavity inside the valve body, the gas valve core is arranged in the gas valve core guide sleeve, the gas ejector rod is propped against the gas valve core, a spring is arranged between the gas valve core and the gas circuit plug, the liquid valve core is installed in the liquid valve core guide sleeve, the liquid ejector rod is abutted to the liquid valve core, and the spring is installed between the liquid valve core and the liquid path plug.
Preferably, the gas valve core is formed by assembling an inlet gas valve core at the lower part, a push rod and an outlet gas valve core at the upper part, the gas ejector rod is divided into an upper ejector rod and a lower ejector rod, the lower ejector rod is abutted between the inlet gas valve core and the outlet gas valve core, the upper ejector rod is abutted between the outlet gas valve core and the armature, the upper ejector rod, the outlet gas valve core, the lower ejector rod, the inlet gas valve core and the spring are in linear connection.
Preferably, the air valve core consists of a valve core and a framework, a sealing block is arranged between the valve core and the framework, and the end face of the sealing block is aligned with the cutting edge of the guide sleeve of the air valve core.
Preferably, the end surface of the liquid ejector rod is abutted to the through hole of the guide sleeve, and the end surface of the liquid ejector rod is larger than the aperture of the through hole of the guide sleeve.
The effect is as follows: the gas valve core is used for sealing gas path media, and gas enters from the lower part and is discharged from the upper part. When the electromagnetic valve is closed, the lower inlet air valve core is stressed by spring force to make the sealing block be pressed against the cutting edge of the air valve core guide sleeve to implement sealing, and the upper outlet air valve core is stressed by thrust of the lower push rod to form a gap with the air valve core guide sleeve, and is connected with atmosphere. When the electromagnetic valve is opened, the armature at the upper end is subjected to electromagnetic force, the force is transmitted to the outlet gas valve core at the upper part through the upper ejector rod, so that the outlet gas valve core moves downwards, the sealing block of the outlet gas valve core and the cutting edge of the gas valve core guide sleeve form sealing, and meanwhile, the lower ejector rod and the inlet gas valve core at the lower end are pushed, so that high-pressure gas below the lower ejector rod enters the gas cavity in the middle. After the gas enters the gas cavity, the liquid ejector rod is pushed through the through hole of the guide sleeve, and the liquid ejector rod pushes the liquid valve core open by overcoming the spring force of the spring, so that the liquid in the liquid inlet flows into the liquid outlet.
Preferably, the liquid valve core is provided with a liquid inlet, the liquid ejector rod is provided with a liquid outlet, and the distance between the liquid inlet and the liquid outlet is 12-15 mm.
The effect is as follows: the distance between the liquid inlet and the liquid outlet is shortened, and the response speed is improved.
Preferably, the lower part of the inlet gas valve core is provided with a gas inlet, and the upper ejector rod is provided with a gas outlet.
Preferably, at least one sealing ring is respectively arranged between the guide sleeve and the shell, between the gas valve core guide sleeve and the guide sleeve, between the liquid valve core guide sleeve and the shell, between the shell and the gas path plug and between the shell and the liquid path plug.
The effect is as follows: the whole sealing performance of the pneumatic valve is enhanced, so that gas can flow according to a designed path, and the cooling effect of the gas is exerted.
Preferably, the gas valve core guide sleeve, the guide sleeve and the liquid valve core guide sleeve are made of metal.
The effect is as follows: the metal material has good thermal conductivity, and absorbs and transfers the heat of the liquid to the gas.
The invention has the beneficial effects that: the invention is suitable for continuous pulse, and the liquid medium has a working condition of higher temperature when entering the valve body, has good heat conductivity, absorbs and transfers the heat of the liquid to the gas for heat conduction, and simultaneously, because of the continuous pulse working condition, the high-low pressure alternation can be continuously generated in the boundary direction of the gas path of the guide sleeve, so that the energy exchange is carried out between the gas and the guide sleeve through the heat convection, the heat conduction efficiency is accelerated, the local temperature of the liquid path is reduced by about 5-10 percent, and the service life of the valve core is prolonged; the internal structure of the valve body is integrated, and the closing response time of the pneumatic valve is shortened.
Drawings
FIG. 1 is a schematic diagram of a pilot pneumatic valve for a rocket power system;
fig. 2 is a partial enlarged structural schematic diagram of a pilot pneumatic valve core part in an opening state of the solenoid valve.
Reference numerals: 1-gas valve core, 2-gas ejector rod, 3-gas valve core guide sleeve, 4-guide sleeve, 5-liquid valve core guide sleeve, 6-liquid ejector rod, 7-liquid valve core, 8-spring, 9-armature, 10-shell, 11-liquid path plug, 12-gas path plug, I-gas inlet, 101-valve core, 102-framework, 103-sealing block, 201-upper ejector rod, 202-lower ejector rod, 301-cutting edge, I-gas inlet, II-liquid outlet, III-liquid inlet and IV-gas outlet.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to the following embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The main working principle of the invention is as follows:
the working condition that the pilot pneumatic valve is applied is that continuous pulse is needed when the pilot pneumatic valve is used, and a liquid medium has a working condition with higher temperature when entering the valve body, so that heat conduction can be generated among gas, the guide sleeve and the liquid due to temperature difference, the guide sleeve made of metal has good heat conductivity, the heat of the liquid is absorbed and transferred to the gas, but the heat conductivity of the gas is relatively poor, only a small amount of heat conduction is generated between the gas and the metal, and meanwhile, the guide sleeve transfers energy to the gas path direction through heat radiation; meanwhile, due to the continuous pulse working condition, high-low pressure alternation can be continuously generated in the boundary direction of the air path of the guide sleeve, so that energy exchange is carried out between the air and the guide sleeve through thermal convection, partial heat of the guide sleeve and the liquid is taken away, and a certain air cooling effect is achieved. In addition, during operation, gas and liquid generate heat exchange at the liquid valve core guide sleeve 5, so that the temperature of the gas is increased, the pressure is increased, the force of the gas acting on the upper end outlet gas valve core when the electromagnetic valve is closed is increased, and the function of shortening the closing response time is realized. Moreover, the overall structure of the pneumatic valve is optimized, the distance between the air path and the liquid path is shortened, the distance between the liquid outlet and the liquid inlet is shortened, and the gas can reach the outer side of the liquid path cavity through the guide sleeve, participate in heat conduction and improve the response speed. The distance between the inlet and the outlet of the liquid path is shortened, and the overall response time is reduced; meanwhile, the range of the gap of the air cavity is enlarged, so that heat exchange is generated between the air and the liquid, the temperature of the air is increased by heat transfer of a liquid path medium, and the air pressure in the air cavity is increased along with the temperature of the air, so that the response time of closing the valve is shortened.
As shown in figures 1 and 2, a pilot pneumatic valve applied to a rocket power system is provided, the outer part is a shell 10, the end parts of the left end and the right end of the shell 10 are sealed by a liquid path plug 11, the lower end of the shell 10 is sealed by a gas path plug 12, the upper part of the shell 10 is provided with an armature 9, the upper part of the armature 9 is provided with a solenoid valve coil, the shell 10 is internally sheathed with a guide sleeve 4, the guide sleeve 4 is internally sheathed with a gas valve core guide sleeve 3 along the axial direction of the guide sleeve 4, the outer side of the guide sleeve 4 is provided with a liquid valve core guide sleeve 5 between the guide sleeve 4 and the liquid path plug 11 along the radial direction of the guide sleeve 4, the gas valve core guide sleeve 3 and the guide sleeve 4 are provided with through holes at the positions of the axial extension lines of the liquid valve core guide sleeve 5, a cross cavity is formed in the valve body, a gas valve core 1 is installed in the gas valve core guide sleeve 3, a gas ejector rod 2 is propped against the gas valve core 1, and the gas valve core 1 consists of an inlet gas valve core at the lower part, The gas ejector rod 2 is divided into an upper ejector rod 201 and a lower ejector rod 202, the lower ejector rod 202 is abutted between the inlet gas valve core and the outlet gas valve core, the upper ejector rod 201 is abutted between the outlet gas valve core and the armature 9, the upper ejector rod 201, the outlet gas valve core, the lower ejector rod 202, the inlet gas valve core and the spring 8 are in linear connection. And a spring 8 is arranged between the inlet gas valve core and the gas path plug 12. The inlet air valve core and the outlet air valve core are both composed of a valve core 101 and a framework 102, a sealing block 103 is arranged between the valve core 101 and the framework 102, and the end surface of the sealing block 103 is aligned with the cutting edge 301 of the air valve core guide sleeve 3.
A liquid valve core 7 is arranged in the liquid valve core guide sleeve 5, a liquid ejector rod 6 is abutted to the liquid valve core, and a spring 8 is arranged between the liquid valve core 7 and a liquid path plug 11. The end surface of the liquid ejector rod 6 is abutted to the through hole of the guide sleeve 4, the end surface of the liquid ejector rod 6 is larger than the aperture of the through hole of the guide sleeve 4, and when the liquid ejector rod is not under gas pressure, the spring 8 enables the end surface of the liquid ejector rod 6 to be abutted to the through hole of the guide sleeve 4 through spring force for sealing. When the air pressure is increased, the pressure of the air acting on the through hole of the guide sleeve 4 is increased to exceed the spring force, and the liquid valve core 7 is pushed to the liquid path plug 11. A liquid inlet III is formed in the position of the liquid valve core 7, a liquid outlet II is formed in the position of the liquid ejector rod 6, and the distance between the liquid inlet III and the liquid outlet II ranges from 12 mm to 15 mm. Effectively shorten the interval between liquid entry III and the liquid export II, improved response speed.
As shown in fig. 1, a gas inlet I is provided at the lower part of the inlet gas valve core, and a gas outlet IV is provided at the upper ejector rod 201. At least one sealing ring is respectively arranged between the guide sleeve 4 and the shell 10, between the gas valve core guide sleeve 3 and the guide sleeve 4, between the liquid valve core guide sleeve 5 and the shell 10, between the shell 10 and the gas path plug 12 and between the shell 10 and the liquid path plug 11.
The gas valve core guide sleeve 3, the guide sleeve 4 and the liquid valve core guide sleeve 5 are made of metal.
When the gas valve core 1 is used for sealing gas circuit media, gas enters from a gas inlet I at the lower part and is discharged from a gas outlet IV at the upper part. In the closed state of the electromagnetic valve, as shown in fig. 1, the lower inlet air valve core is subjected to spring force to enable the sealing block 103 to abut against the cutting edge 301 of the air valve core guide sleeve 3 to realize sealing, and the upper outlet air valve core is subjected to thrust of the lower ejector rod 202 to form a gap with the air valve core guide sleeve 3 and be connected with the atmosphere. When the solenoid valve is opened, as shown in fig. 2, the armature 9 at the upper end is subjected to electromagnetic force, and the force is transmitted to the outlet air valve core at the upper part through the upper ejector rod 201, so that the outlet air valve core moves downwards, the sealing block 103 of the outlet air valve core forms sealing with the cutting edge 301 of the air valve core guide sleeve 3, and meanwhile, the lower ejector rod 202 and the inlet air valve core at the lower end are pushed, so that high-pressure air below enters the air cavity in the middle. After the gas enters the gas cavity, the liquid ejector rod 6 is pushed through the through hole of the guide sleeve 4, the liquid ejector rod 6 pushes the liquid valve core 7 open against the spring force of the spring 8, and therefore the liquid in the liquid inlet III flows into the liquid outlet II.
The above description is the specific embodiment of the present invention and the technical principle applied, and any modification and equivalent transformation based on the technical solution of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. The pilot pneumatic valve applied to the rocket power system is characterized in that: the valve body is characterized in that a shell is arranged outside the valve body, the end parts of the left end and the right end of the shell are sealed through a liquid path plug, the lower end of the shell is sealed through a gas path plug, an armature is arranged on the upper portion of the shell, a guide sleeve is sleeved inside the shell, a gas valve core guide sleeve is sleeved inside the guide sleeve along the axial direction of the guide sleeve, a liquid valve core guide sleeve is arranged between the guide sleeve and the liquid path plug on the outer side of the guide sleeve along the radial direction of the guide sleeve, through holes are formed in the axial extension line of the liquid valve core guide sleeve by the gas valve core guide sleeve and the guide sleeve, a cross-shaped through cavity is formed inside the valve body, a gas valve core is arranged in the gas valve core guide sleeve, a gas ejector rod is abutted against the gas valve core, a spring is arranged between the gas valve core and the gas path plug, a liquid valve core is arranged in the liquid valve core guide sleeve, and a spring is arranged between the liquid valve core and the liquid path plug.
2. A pilot pneumatic valve for a rocket power system as recited in claim 1, further comprising: the gas valve core is formed by assembling an inlet gas valve core at the lower part, a push rod and an outlet gas valve core at the upper part, the gas ejector rod is divided into an upper ejector rod and a lower ejector rod, the lower ejector rod is abutted between the inlet gas valve core and the outlet gas valve core, the upper ejector rod is abutted between the outlet gas valve core and the armature, the upper ejector rod, the outlet gas valve core, the lower ejector rod, the inlet gas valve core and the spring are in linear connection.
3. A pilot pneumatic valve for a rocket power system as recited in claim 1, further comprising: the gas valve core consists of a valve core and a framework, a sealing block is arranged between the valve core and the framework, and the end face of the sealing block is aligned with the cutting edge of the gas valve core guide sleeve.
4. A pilot pneumatic valve for a rocket power system as recited in claim 1, further comprising: the end surface of the liquid ejector rod is abutted to the through hole of the guide sleeve, and the end surface of the liquid ejector rod is larger than the aperture of the through hole of the guide sleeve.
5. A pilot pneumatic valve for a rocket power system as recited in claim 1, further comprising: the liquid valve core is provided with a liquid inlet, the liquid ejector rod is provided with a liquid outlet, and the distance between the liquid inlet and the liquid outlet is 12-15 mm.
6. A pilot pneumatic valve for a rocket power system as recited in claim 2, further comprising: the lower part of the inlet gas valve core is provided with a gas inlet, and the upper ejector rod is provided with a gas outlet.
7. The pilot pneumatic valve applied to the rocket power system as recited in any one of claims 1 to 6, wherein: at least one sealing ring is respectively arranged between the guide sleeve and the shell, between the gas valve core guide sleeve and the guide sleeve, between the liquid valve core guide sleeve and the shell, between the shell and the gas path plug and between the shell and the liquid path plug.
8. The pilot pneumatic valve applied to the rocket power system as recited in any one of claims 1 to 6, wherein: the gas valve core guide sleeve, the guide sleeve and the liquid valve core guide sleeve are made of metal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111502640.9A CN114352800A (en) | 2021-12-09 | 2021-12-09 | Pilot pneumatic valve applied to rocket power system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111502640.9A CN114352800A (en) | 2021-12-09 | 2021-12-09 | Pilot pneumatic valve applied to rocket power system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114352800A true CN114352800A (en) | 2022-04-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111502640.9A Pending CN114352800A (en) | 2021-12-09 | 2021-12-09 | Pilot pneumatic valve applied to rocket power system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114352800A (en) |
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| CN203906964U (en) * | 2014-06-16 | 2014-10-29 | 奉化市盛强晨亿机械有限公司 | Novel pilot solenoid valve |
| CN105570470A (en) * | 2015-12-20 | 2016-05-11 | 西安航天动力研究所 | Built-in pilot operated solenoid valve |
| CN106989195A (en) * | 2017-05-11 | 2017-07-28 | 西安航天动力研究所 | A kind of guide type electromagnetic pneumatic operated valve and combined control valve |
| CN106989196A (en) * | 2017-05-11 | 2017-07-28 | 西安航天动力研究所 | A kind of electromagnetic actuator device and guide type electromagnetic pneumatic operated valve |
| CN109253305A (en) * | 2018-12-03 | 2019-01-22 | 上海空间推进研究所 | Electromagnetism-gas-driving valve based on differential area area method |
| CN109899566A (en) * | 2019-04-02 | 2019-06-18 | 沈阳航天新光集团有限公司 | A kind of pilot-operated type air-operated solenoid valve |
-
2021
- 2021-12-09 CN CN202111502640.9A patent/CN114352800A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002039429A (en) * | 2000-07-19 | 2002-02-06 | Tgk Co Ltd | Two-stage pilot solenoid valve |
| JP2002168367A (en) * | 2000-11-28 | 2002-06-14 | Pacific Ind Co Ltd | Reversible pilot type solenoid valve |
| JP2004301318A (en) * | 2003-03-19 | 2004-10-28 | Mitsubishi Heavy Ind Ltd | High temperature / high pressure gas direction switching valve |
| CN2784677Y (en) * | 2004-12-10 | 2006-05-31 | 鞍山电磁阀有限责任公司 | Intelligent high-temperature high-pressure solenoid valve |
| CN201057283Y (en) * | 2007-07-20 | 2008-05-07 | 李军 | Oxygen flame-retardant balanced stop valve |
| CN203906964U (en) * | 2014-06-16 | 2014-10-29 | 奉化市盛强晨亿机械有限公司 | Novel pilot solenoid valve |
| CN105570470A (en) * | 2015-12-20 | 2016-05-11 | 西安航天动力研究所 | Built-in pilot operated solenoid valve |
| CN106989195A (en) * | 2017-05-11 | 2017-07-28 | 西安航天动力研究所 | A kind of guide type electromagnetic pneumatic operated valve and combined control valve |
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| CN109253305A (en) * | 2018-12-03 | 2019-01-22 | 上海空间推进研究所 | Electromagnetism-gas-driving valve based on differential area area method |
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