CN105889548B - A kind of high-temperature fuel gas regulating valve for rocket engine - Google Patents
A kind of high-temperature fuel gas regulating valve for rocket engine Download PDFInfo
- Publication number
- CN105889548B CN105889548B CN201610264243.5A CN201610264243A CN105889548B CN 105889548 B CN105889548 B CN 105889548B CN 201610264243 A CN201610264243 A CN 201610264243A CN 105889548 B CN105889548 B CN 105889548B
- Authority
- CN
- China
- Prior art keywords
- spool
- shaft sleeve
- motor shaft
- valve body
- end cap
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Classifications
-
- 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
- F16K5/00—Plug valves; Taps or cocks comprising only cut-off apparatus having at least one of the sealing faces shaped as a more or less complete surface of a solid of revolution, the opening and closing movement being predominantly rotary
- F16K5/06—Plug valves; Taps or cocks comprising only cut-off apparatus having at least one of the sealing faces shaped as a more or less complete surface of a solid of revolution, the opening and closing movement being predominantly rotary with plugs having spherical surfaces; Packings therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
-
- 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
- F16K31/00—Actuating devices; Operating means; Releasing devices
- F16K31/02—Actuating devices; Operating means; Releasing devices electric; magnetic
- F16K31/04—Actuating devices; Operating means; Releasing devices electric; magnetic using a motor
- F16K31/041—Actuating devices; Operating means; Releasing devices electric; magnetic using a motor for rotating valves
-
- 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
- F16K5/00—Plug valves; Taps or cocks comprising only cut-off apparatus having at least one of the sealing faces shaped as a more or less complete surface of a solid of revolution, the opening and closing movement being predominantly rotary
- F16K5/08—Details
-
- 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
- F16K5/00—Plug valves; Taps or cocks comprising only cut-off apparatus having at least one of the sealing faces shaped as a more or less complete surface of a solid of revolution, the opening and closing movement being predominantly rotary
- F16K5/08—Details
- F16K5/12—Arrangements for modifying the way in which the rate of flow varies during the actuation of the valve
-
- 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
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L59/00—Thermal insulation in general
- F16L59/14—Arrangements for the insulation of pipes or pipe systems
- F16L59/16—Arrangements specially adapted to local requirements at flanges, junctions, valves or the like
- F16L59/168—Flexible insulating material or covers for flanges, junctions, valves or the like
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Electrically Driven Valve-Operating Means (AREA)
- Taps Or Cocks (AREA)
- Mechanically-Actuated Valves (AREA)
Abstract
The invention discloses a kind of high-temperature fuel gas regulating valves for rocket engine, are made of valve body, upper end cover, connection end cap, motor shaft sleeve, rotary shaft, spool and spool bracket.Motor is connected with upper end cover, and motor output shaft is connected with motor shaft sleeve, is connected between motor shaft sleeve and rotary shaft, spool, realizes positioning and transmission；Spool is connect with spool bracket.Appendix insulation is connected mounted on spool bracket both ends with connection end cap；Valve body is threadedly coupled with connection end cap, and valve body is connected with upper end cover by bolt；Connection end cap is connect with fuel gas pipeline.High-temperature fuel gas regulating valve realizes the change of circulation area by changing the rotation angle of valve, and the gas flow of thrust adjusting, the flow-rate adjustment of pack boronitriding or solid rocket ramjet gas generator so as to fulfill solid propellant engine is adjusted；It is and safe and reliable.High-temperature fuel gas regulating valve structure is simple, installation operation is convenient, thermal protection effect is good.
Description
Technical field
The present invention relates to Thrust of Solid Rocket Motor adjusting and Ducted rocket flow-rate adjustment technology, specifically, relating to
And a kind of high-temperature fuel gas regulating valve for rocket engine.
Background technology
In solid engines change propulsive technology and solid rocket ramjet gas flow regulation technology, combustion gas is adjusted
It is a kind of preferable scheme that valve designing scheme, which all be can yet be regarded as, and also has and carried out verification experimental verification compared with multi-scheme.
In existing disclosed technical literature, a kind of electronic cone valve type solid is disclosed in patent of invention 201310345207.8
Rocket ramjet gas flow regulating device, and a kind of cone valve type combustion gas stream is proposed in patent 201310380537.0
Quantity regulating device.For the main distinction in the driving device of valve, regulating device main body is cone valve in this two regulating device patents.
It is very high to the type face requirement of cone during using cone valve progress flow-rate adjustment, it is a kind of line way of contact control, and in high temperature ring
Since the influence of ablation can also influence flow-rate adjustment precision under border.
Invention content
In order to avoid the shortcomings of the prior art, the present invention proposes that a kind of high-temperature fuel gas for rocket engine is adjusted
Valve.This ball-shaped regulation valve used under the conditions of high combustion temperature, the change of circulation area is realized by the rotation angle for changing valve,
Start so as to fulfill thrust adjusting, the flow-rate adjustment of pack boronitriding or the solid-rocket punching press of solid propellant engine
The gas flow of gas generator of machine is adjusted.
The technical solution adopted by the present invention to solve the technical problems is:Including rotary shaft, spool, spool bracket, motor
Axle sleeve, thermal insulation barriers, valve body insulation, valve body, connection end cap, appendix insulation, upper end cover, the spool be ball-shaped, valve
Core is central axial to be provided with through-hole, and spool top is longitudinally equipped with rectangular recess, and rectangular recess center line and axially extending bore central shaft
Line is vertical, and spool is located in spool bracket, and spool is mounted on spool bracket on valve body insulation, and appendix insulation is located at valve
Core bracket both ends are connect respectively with connection end cap, and appendix insulation axially has stepped hole to be connected with connection end cap axial hole,
Spool realizes the control of circulation area with spool bracket engagement；The rotary shaft lower end has rectangular cam and the rectangle on spool recessed
Slot is connected, and rotary shaft upper end is radially provided with rectangular channel and the rectangular cam of motor shaft sleeve lower end is connected, thermal insulation barriers position
Between motor shaft sleeve and rotary shaft, thermal insulation barriers are for heat transfer of the partition from spool to motor shaft sleeve；On the motor shaft sleeve
End central blind hole madial wall is provided with keyway, and motor shaft sleeve passes through key connection, motor shaft sleeve lateral wall top week with motor output shaft
To equipped with seal groove, seal groove is built-in with motor shaft sleeve sealing ring, and motor shaft sleeve side wall lower edge circumferentially has boss, and lower end is set
There is rectangular cam, motor shaft sleeve is clearance fit with rotary shaft, and rotary shaft is clearance fit with spool, realizes positioning and transmission；
The valve body is threadedly coupled with connection end cap, and seal groove is equipped between valve body and connection end cap, and seal groove is built-in with connection end cap
Sealing ring；Valve body is bolted with upper end cover, seal groove is equipped between valve body and upper end cover, it is close that seal groove is built-in with end cap
Seal；Upper end cover is connected with motor, and connection end cap is connect with fuel gas pipeline, and bearing is located on motor shaft sleeve boss, ensures axle sleeve
Rotation and concentricity, between motor shaft sleeve and thermal insulation barriers, valve body insulation be equipped with thermal insulation barriers sealing ring.
Motor shaft sleeve, thermal insulation barriers, rotary shaft and spool are coaxial.
High silica phenolic materials are respectively adopted in the valve body insulation and the thermal insulation barriers.
Tungsten alloy material is respectively adopted with the rotary shaft in the spool.
Advantageous effect
A kind of high-temperature fuel gas regulating valve for rocket engine proposed by the present invention, by valve body, upper end cover, connecting pin
Lid, motor shaft sleeve, rotary shaft, spool and spool bracket composition.Motor is connected with upper end cover, and motor output shaft connects with motor shaft sleeve
It connects, clearance fit connects between motor shaft sleeve and rotary shaft, spool, realizes positioning and transmission；Spool connect real with spool bracket
The control of existing circulation area.Appendix insulation is connected mounted on spool bracket both ends with connection end cap；Valve body and connection end cap
It is threadedly coupled, valve body is connected with upper end cover by bolt, and is realized and sealed by upper end cover sealing ring；Connection end cap and Gas Pipe
Road connects, and bearing is mounted on motor shaft sleeve boss, ensures rotation and the concentricity of axle sleeve.
High-temperature fuel gas regulating valve of the present invention realizes the change of circulation area by changing the rotation angle of valve, so as to fulfill solid
The thrust of body propellant engine is adjusted, the combustion gas of the flow-rate adjustment of pack boronitriding or solid rocket ramjet
The gas flow of generator is adjusted；Realize that the quick of continuous multi-state is adjusted securely and reliably.High-temperature fuel gas regulating valve structure is simple,
Installation operation is convenient, thermal protection effect is good.
Description of the drawings
A kind of high-temperature fuel gas regulating valve for rocket engine of the invention is made with embodiment below in conjunction with the accompanying drawings into
One step is described in detail.
Fig. 1 is high-temperature fuel gas regulating valve structure schematic diagram of the present invention.
Fig. 2 is motor shaft sleeve, rotary shaft and spool connecting portion schematic diagram.
Fig. 3 is 2 middle section sectional view of attached drawing.
Fig. 4 is motor shaft sleeve structure diagram.
Fig. 5 is rotation axis structure diagram.
Fig. 6 is valve core structure schematic diagram.
Fig. 7 is cold-flow test pressure governing response curve graph.
Fig. 8 is hot-fluid testing pressure governing response curve graph.
In figure
1. 5. spool bracket of valve body 2. connection end cap sealing ring, 3. connection end cap, 4. appendix insulation, 6. upper end cover
7. 11. thermal insulation barriers sealing ring of upper end cover sealing ring 8. motor shaft sleeve sealing ring, 9. motor shaft sleeve, 10. bearing, 12. thermal insulation barriers
13. 14. spool of rotary shaft, 15. valve body insulation
Specific embodiment
The present embodiment is a kind of high-temperature fuel gas regulating valve for rocket engine.
Refering to Fig. 1~Fig. 6, the present embodiment is used for the high-temperature fuel gas regulating valve of rocket engine, by valve body 1, connection end cap
Sealing ring 2, connection end cap 3, appendix insulation 4, spool bracket 5, upper end cover 6, upper end cover sealing ring 7, motor shaft sleeve sealing
15 groups of circle 8, motor shaft sleeve 9, bearing 10, thermal insulation barriers sealing ring 11, thermal insulation barriers 12, rotary shaft 13, spool 14 and valve body insulation
Into.Valve body 1 carries and as the installing matrix of internal part；Valve body 1 is connected through a screw thread with connection end cap 3, and valve body 1 is with connecting
Seal groove is equipped between end cap 3, seal groove is built-in with connection end cap sealing ring 2, realizes and is sealed between valve body 1 and connection end cap 3；
Connection end cap 3 is attached with fuel gas pipeline by screw thread, and the dress that hexagonal structure is easily installed is designed in connection end cap 3
Card.Valve body 1 is bolted with upper end cover 6, and 1 upper end of valve body is provided with seal groove, and seal groove is built-in with upper end cover sealing ring
7, it is realized and sealed by upper end cover sealing ring 7 between valve body 1 and upper end cover 6；Motor is fixedly mounted on the top of upper end cover 6.This
Valve body 1 is processed with connection end cap 3, upper end cover 6 using 1Cr18Ni9Ti materials in embodiment.
In the present embodiment, spool 14 is ball-shaped, and spool 14 is central axial to be provided with through-hole, is blast tube, on spool 14
Portion is longitudinally equipped with rectangular recess, and rectangular recess center line and axially extending bore central axis upright；Spool 14 is mounted on spool support
In frame 5, spool 14 is mounted on spool bracket 5 on valve body insulation 15, and spool 14 realizes circulation area with the cooperation of spool bracket 5
Control；Appendix insulation 4 is fixed on 5 both ends of spool bracket and is connect respectively with connection end cap 3, and appendix insulation 4 is axial
There is stepped hole to be connected with 3 axial hole of connection end cap；Spool bracket 5 is used to implement the sealing of spool 14 and support and rotated
Lubrication in journey, spool bracket 5 use C/C composite materials.Appendix insulation 4 protects for the high temperature resistance of pipeline, appendix
Insulation 4 is processed using high silica phenolic materials.13 lower end of rotary shaft connects for the rectangular recess cooperation of rectangular cam and spool 14
It connects, 13 upper end of rotary shaft radially has rectangular channel and the rectangular cam of 9 lower end of motor shaft sleeve to be connected, motor shaft sleeve 9 and rotation
It is clearance fit between axis 13, realizes positioning and transmission；Spool 14, rotary shaft 13 are processed using tungsten alloy material.Motor shaft sleeve 9
Upper end center blind hole madial wall is machined with keyway, i.e., A is identified in figure, and motor shaft sleeve 9 passes through key connection with motor output shaft；Motor
9 lateral wall top of axle sleeve is circumferentially with seal groove, and seal groove is built-in with motor shaft sleeve sealing ring 8,9 side wall lower edge of motor shaft sleeve
Circumferentially there is boss, 9 lower end of motor shaft sleeve is equipped with rectangular cam；Motor shaft sleeve 9 and rotary shaft 13 are clearance fit, rotary shaft 13
It is clearance fit with spool 14, realizes positioning and transmission.Thermal insulation barriers 12 are mounted between motor shaft sleeve 9 and rotary shaft 13, heat-insulated
Part 12 ensures the normal operation work of motor, thermal insulation barriers 12 are using high for separating from spool 14 to the heat transfer of motor shaft sleeve 9
Silica phenolic materials are processed.Spool 14 is mounted on spool bracket 5 on valve body insulation 15, and valve body insulation 15 is interior for being isolated
Portion's heat is conducted to valve body, protects valve body, and valve body insulation 15 is processed using high silica phenolic materials.
In the present embodiment, motor shaft sleeve 9, rotary shaft 13 are driven with spool 14 by rectangular channel and rectangular cam cooperation；Electricity
Mark B is the mounting groove of motor shaft sleeve sealing ring 8 in seal groove, that is, figure of arbor set 9, and the rectangular cam of 9 lower end of motor shaft sleeve is
It is clearance fit that C and the i.e. middle mark D of rectangular channel of 13 upper end of rotary shaft are identified in figure, realizes positioning and transmission.Under rotary shaft 13
It is clearance fit that E and mark F in rectangular recess, that is, figure on spool 14 is identified in the rectangular cam, that is, figure at end, realizes positioning and passes
It is dynamic.
The present embodiment is in the channel contacted with high-temperature fuel gas is realized, all using high temperature resistant composite and high temperature alloy
Material makes processing, realizes the unobstructed of high-temperature fuel gas；It is made in the critical component of control circulation area of ablation resistant material
Processing is realized and keeps the immovable feature of circulation area during the work time.The control of circulation area passes through motor band movable valve plug
14 rotations and the cooperation of spool bracket 5 are realized, and can realize the complete opening and closing of combustion gas runner.
Installation process
Valve body insulation 15 is fixed in valve body 1 first；Then it is adiabatic spool 14 and spool bracket 5 to be mounted on valve body
On part 15, ensure the upper hole of the rectangular recess face valve body insulation 15 of spool 14；By spool bracket 5 and the sub-assembly of spool 14
Mounted on the corresponding position of valve body insulation 15, both sides are symmetrically installed the position for ensureing spool 14；Connection end cap sealing ring 2 is pacified
In the seal groove of valve body 1, connection end cap 3 is mounted on by special spanner on valve body 1, again will after good rotary shaft 13 to be installed
Connection end cap 3 is fastened；Rotary shaft 13 is mounted on 15 corresponding position of valve body insulation, ensures the mark E of rotary shaft 13
Face and the mark F faces of spool 14 are fully mated；Thermal insulation barriers 12 are mounted in the rectangular channel of rotary shaft 13；By thermal insulation barriers sealing ring 11
Mounted on the corresponding position of valve body insulation 15；Motor shaft sleeve 9 is mounted on thermal insulation barriers 12, and the rectangle by motor shaft sleeve 9 is convex
Block is connect with thermal insulation barriers 12；Bearing 10 is fixed on the boss of motor shaft sleeve 9, and is coordinated with 15 corresponding position of valve body insulation；
Motor shaft sleeve sealing ring 8 is placed in the seal groove of motor shaft sleeve 9；Upper end cover sealing ring 7 is corresponded into sealing mounted on valve body 1
In ring recess；Fastening is bolted with valve body 1 in upper end cover 6.
Refering to Fig. 7, Fig. 8, driving device of the MACR3 servo motors as valve is selected, by being keyed mode by servo electricity
Machine is connected with motor shaft sleeve 9.Servo motor programming is carried out according to the purpose of experiment.Pass through high-pressure nitrogen bottle connecting line group
Build the verification system of cold-flow test leakproofness and response characteristic, by test the pressure after valve characterize valve leakproofness and response it is special
Property.In the case where closing valve, open nitrogen cylinder ventilation, test valve whether gas leakage, verify the leakproofness of valve；According to driven by program
The change of pressure after valve is tested in valve start, tests the response characteristic of valve.Verify that its leakproofness and response are special using cold-flow test
Property, verification experimental verification is the result shows that high-temperature fuel gas regulating valve can realize good sealing, and can realize and completely close pipeline, quickly in fact
Existing pressure response.By using the gas generator for the solid propellant that adiabatic combustion temperature is 1523K, the high temperature item of valve is set up
Working characteristics verification system under part, and the hot-fluid experiment of high-temperature fuel gas regulating valve is carried out, adjust valve regulation spirit in experimentation
Living, output pressure is stablized, and each component is disassembled after experiment and shows that high-temperature fuel gas regulating valve internal structure is intact.
Claims (4)
1. a kind of high-temperature fuel gas regulating valve for rocket engine, including rotary shaft, spool, spool bracket, motor shaft sleeve, every
Warmware, valve body insulation, valve body, connection end cap, appendix insulation and upper end cover, it is characterised in that:The spool to be round,
Center spool is axially provided with through-hole, and spool top is longitudinally equipped with rectangular recess, and rectangular recess center line and axially extending bore center
Axis is vertical, and spool is located in spool bracket, and spool bracket uses C/C composite materials, and spool is mounted on valve body with spool bracket
On insulation, appendix insulation is located at spool bracket both ends and is connect respectively with connection end cap, and appendix insulation axially has platform
Rank hole is connected with connection end cap axial hole, and spool realizes the control of circulation area with spool bracket engagement, and can realize combustion gas
The complete opening and closing of runner；The rotary shaft lower end has rectangular cam to be connected with the rectangular recess on spool, rotary shaft upper end
The rectangular cam for being radially provided with rectangular channel and motor shaft sleeve lower end is connected, thermal insulation barriers be located at motor shaft sleeve and rotary shaft it
Between, thermal insulation barriers are for heat transfer of the partition from spool to motor shaft sleeve；The motor shaft sleeve upper end center blind hole madial wall is provided with
Keyway, by key connection, motor shaft sleeve lateral wall top is circumferentially with seal groove for motor shaft sleeve and motor output shaft, in seal groove
Be equipped with motor shaft sleeve sealing ring, motor shaft sleeve side wall lower edge circumferentially has a boss, and lower end is equipped with rectangular cam, motor shaft sleeve with
Rotary shaft is clearance fit, and rotary shaft is clearance fit with spool, realizes positioning and transmission；The valve body and connection end cap screw thread
Connection, is equipped with seal groove between valve body and connection end cap, seal groove is built-in with connection end cap sealing ring；Valve body passes through with upper end cover
It is bolted, seal groove is equipped between valve body and upper end cover, seal groove is built-in with end cap seal circle；Upper end cover is connected with motor,
Connection end cap is connect with fuel gas pipeline, and bearing is located on motor shaft sleeve boss, ensures rotation and the concentricity of axle sleeve, motor shaft sleeve
Thermal insulation barriers sealing ring is equipped between thermal insulation barriers, valve body insulation.
2. the high-temperature fuel gas regulating valve according to claim 1 for rocket engine, it is characterised in that:Motor shaft sleeve,
Thermal insulation barriers, rotary shaft and spool are coaxial.
3. the high-temperature fuel gas regulating valve according to claim 1 for rocket engine, it is characterised in that:The valve body is exhausted
High silica phenolic materials are respectively adopted in warmware and the thermal insulation barriers.
4. the high-temperature fuel gas regulating valve according to claim 1 for rocket engine, it is characterised in that:The spool with
Tungsten alloy material is respectively adopted in the rotary shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610264243.5A CN105889548B (en) | 2016-04-26 | 2016-04-26 | A kind of high-temperature fuel gas regulating valve for rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610264243.5A CN105889548B (en) | 2016-04-26 | 2016-04-26 | A kind of high-temperature fuel gas regulating valve for rocket engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105889548A CN105889548A (en) | 2016-08-24 |
| CN105889548B true CN105889548B (en) | 2018-07-03 |
Family
ID=56704708
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610264243.5A Expired - Fee Related CN105889548B (en) | 2016-04-26 | 2016-04-26 | A kind of high-temperature fuel gas regulating valve for rocket engine |
Country Status (1)
| Country | Link |
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| CN (1) | CN105889548B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106321285B (en) * | 2016-08-26 | 2018-10-02 | 南京理工大学 | The fixed solid rocket ramjet gas flow regulating device of cone valve |
| CN111636979B (en) * | 2020-06-08 | 2021-05-25 | 安徽九州云箭航天技术有限公司 | Switch and flow regulating valve for liquid oxygen main circuit of pump pressure variable thrust liquid rocket engine |
| CN114636004B (en) * | 2022-05-19 | 2022-08-26 | 中国人民解放军火箭军工程大学 | High-temperature fuel product energy management device and spray pipe |
| CN116044617A (en) * | 2023-03-01 | 2023-05-02 | 北京星河动力装备科技有限公司 | Nozzle and rocket engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB847560A (en) * | 1958-09-15 | 1960-09-07 | Rockwell Mfg Co | Rotary ball type fluid valve |
| FR1263041A (en) * | 1959-07-22 | 1961-06-05 | Saunders Valve Co Ltd | Improvements to key taps |
| US6986246B2 (en) * | 2002-05-21 | 2006-01-17 | Mitsubishi Heavy Industries, Ltd. | Side thruster valve and side thruster device |
| CN201747969U (en) * | 2010-04-08 | 2011-02-16 | 金战雄 | Split-type temperature control valve |
| CN102052198A (en) * | 2010-12-23 | 2011-05-11 | 西北工业大学 | Experimental device for full-scale nozzle thermal structure of solid-propellant rocket engine |
| CN204284508U (en) * | 2014-11-11 | 2015-04-22 | 胡光雄 | A kind of composite anti-corrosive acid-proof wear-proof high-temperature resistant ball valve |
| US9022348B2 (en) * | 2011-09-01 | 2015-05-05 | Jianchao Shu | Triple offset butterfly valve and rotary for severe services |
-
2016
- 2016-04-26 CN CN201610264243.5A patent/CN105889548B/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB847560A (en) * | 1958-09-15 | 1960-09-07 | Rockwell Mfg Co | Rotary ball type fluid valve |
| FR1263041A (en) * | 1959-07-22 | 1961-06-05 | Saunders Valve Co Ltd | Improvements to key taps |
| US6986246B2 (en) * | 2002-05-21 | 2006-01-17 | Mitsubishi Heavy Industries, Ltd. | Side thruster valve and side thruster device |
| CN201747969U (en) * | 2010-04-08 | 2011-02-16 | 金战雄 | Split-type temperature control valve |
| CN102052198A (en) * | 2010-12-23 | 2011-05-11 | 西北工业大学 | Experimental device for full-scale nozzle thermal structure of solid-propellant rocket engine |
| US9022348B2 (en) * | 2011-09-01 | 2015-05-05 | Jianchao Shu | Triple offset butterfly valve and rotary for severe services |
| CN204284508U (en) * | 2014-11-11 | 2015-04-22 | 胡光雄 | A kind of composite anti-corrosive acid-proof wear-proof high-temperature resistant ball valve |
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| Publication number | Publication date |
|---|---|
| CN105889548A (en) | 2016-08-24 |
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