CN105889548A - High-temperature fuel gas adjusting valve used for rocket engine - Google Patents
High-temperature fuel gas adjusting valve used for rocket engine Download PDFInfo
- Publication number
- CN105889548A CN105889548A CN201610264243.5A CN201610264243A CN105889548A CN 105889548 A CN105889548 A CN 105889548A CN 201610264243 A CN201610264243 A CN 201610264243A CN 105889548 A CN105889548 A CN 105889548A
- Authority
- CN
- China
- Prior art keywords
- spool
- fuel gas
- shaft sleeve
- motor shaft
- valve
- 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.)
- Granted
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Classifications
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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
- 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
Abstract
The invention discloses a high-temperature fuel gas adjusting valve used for a rocket engine. The high-temperature fuel gas adjusting valve used for the rocket engine is composed of a valve body, an upper end cover, connection end covers, a motor shaft sleeve, a rotating shaft, a valve element and a valve element bracket. The motor is fixedly connected with the upper end cover; an output shaft of the motor is fixedly connected with the motor shaft sleeve which is connected with the rotating shaft and the valve element in a cooperative manner, and positioning and transmission are achieved; and the valve element is connected with the valve element bracket. Gas conveying pipe heat insulating pieces are installed at the two ends of the valve element bracket and fixedly connected with the connection end covers; the valve body is in threaded connection with the connection end covers and is fixedly connected with the upper end cover through bolts; and the connection end covers are connected with a fuel gas pipeline. The high-temperature fuel gas adjusting valve changes the circulating area by changing the rotating angle of the valve, and therefore thrust adjustment of a solid propellant engine, flow adjustment of a solid fuel gas generator or fuel gas flow adjustment of a primary fuel gas generator of the solid rocket ramjet engine can be achieved; and the high-temperature fuel gas adjusting valve is safe and reliable. The high-temperature fuel gas adjusting valve is simple in structure, convenient to install and operate and good in heat protection effect.
Description
Technical field
The present invention relates to Thrust of Solid Rocket Motor regulation and Ducted rocket Flow-rate adjustment technology, specifically
Say, relate to a kind of high-temperature fuel gas for rocket engine and regulate valve.
Background technology
In solid engines change propulsive technology and solid rocket ramjet gas flow regulation technology, combustion
It is a kind of preferably scheme that controlled atmosphere joint valve design all be can yet be regarded as, and also has relatively multi-scheme to be tested
Checking.
In existing disclosed technical literature, patent of invention 201310345207.8 discloses a kind of electronic cone valve
Formula solid rocket ramjet gas flow adjusting means, and patent 201310380537.0 proposes
A kind of cone valve type gas flow adjusting means.In these two adjusting means patents, the main distinction is in the driving of valve
On device, adjusting means main body is cone valve.When using cone valve to carry out Flow-rate adjustment, the profile to cone requires very
Height, is that a kind of linear contact lay mode controls, and also can affect flow due to the impact of ablation in high temperature environments
Degree of regulation.
Summary of the invention
The deficiency existed in order to avoid prior art, the present invention proposes a kind of high temperature for rocket engine and fires
Controlled atmosphere joint valve.This ball-shaped regulation valve used under the conditions of height combustion temperature, real by changing the anglec of rotation of valve
The change of existing circulation area, thus realize the thrust regulation of solid propellant engine, pack boronitriding
Flow-rate adjustment or gas generator of solid rocket ramjet gas flow regulation.
The technical solution adopted for the present invention to solve the technical problems is: include rotary shaft, spool, spool bracket,
Motor shaft sleeve, thermal insulation barriers, valve body insulation, valve body, connection end cap, appendix insulation, upper end cover,
Described spool is ball-shaped, and center spool axially has through hole, and spool top is longitudinally provided with rectangular recess, and square
Connected in star centrage and axially extending bore central axis upright, spool is positioned at spool bracket, spool and spool torr
Frame is arranged on valve body insulation, appendix insulation be positioned at spool bracket two ends respectively be connected end cap connect,
Appendix insulation axially has stepped hole and is connected end cap axial hole and is connected, and spool is real with spool bracket engagement
The control of existing circulation area；Described rotary shaft lower end has rectangular cam to be connected with the rectangular recess on spool,
Rotary shaft upper end radially has the rectangular cam of rectangular channel and motor shaft sleeve lower end and is connected, and thermal insulation barriers is positioned at
Between motor shaft sleeve and rotary shaft, thermal insulation barriers is for cutting off by spool to the conduction of heat of motor shaft sleeve；Described electricity
Central blind hole medial wall, arbor set upper side has keyway, motor shaft sleeve and motor output shaft and passes through bonded, electricity
Arbor set top, lateral wall is circumferentially with seal groove, and seal groove is built-in with motor shaft sleeve sealing ring, motor shaft sleeve
Sidewall lower limb circumference has boss, bottom to be provided with rectangular cam, and motor shaft sleeve and rotary shaft are matched in clearance,
Rotary shaft and spool are matched in clearance, it is achieved location and transmission；Described valve body with to be connected end cap threaded,
Valve body is provided with seal groove with being connected between end cap, and seal groove is built-in with connection end cap seal circle；Valve body and upper end
Lid is bolted, and is provided with seal groove between valve body and upper end cover, and seal groove is built-in with end cap seal circle；
Upper end cover is connected with motor, connects end cap and is connected with fuel gas pipeline, and bearing is positioned on motor shaft sleeve boss, protects
The rotation of card axle sleeve and axiality, be provided with thermal insulation barriers and seal between motor shaft sleeve and thermal insulation barriers, valve body insulation
Circle.
Motor shaft sleeve, thermal insulation barriers, rotary shaft are coaxial with spool.
Described valve body insulation and described thermal insulation barriers are respectively adopted high silica phenolic materials.
Described spool and described rotary shaft are respectively adopted tungsten alloy material.
Beneficial effect
A kind of high-temperature fuel gas for rocket engine that the present invention proposes regulates valve, by valve body, upper end cover, company
Connect end cap, motor shaft sleeve, rotary shaft, spool and spool bracket composition.Motor is connected with upper end cover, motor
Output shaft is connected with motor shaft sleeve, and between motor shaft sleeve with rotary shaft, spool, matched in clearance is connected, it is achieved fixed
Position and transmission；Spool is connected the control realizing circulation area with spool bracket.Appendix insulation is arranged on valve
Core bracket two ends are connected with being connected end cap；Valve body is with to be connected end cap threaded, and valve body and upper end cover pass through spiral shell
Bolt is connected, and realizes sealing by upper end cover sealing ring；Connecting end cap to be connected with fuel gas pipeline, bearing is installed
On motor shaft sleeve boss, it is ensured that the rotation of axle sleeve and axiality.
High-temperature fuel gas of the present invention regulation valve realizes the change of circulation area by the anglec of rotation changing valve, thus
Realize the thrust regulation of solid propellant engine, the Flow-rate adjustment of pack boronitriding or solid-rocket punching
The gas flow regulation of gas generator of hydraulic motor；The quickly regulation safety realizing continuous multi-state can
Lean on.High-temperature fuel gas regulating valve structure is simple, it is easy to operate to install, thermal protection is effective.
Accompanying drawing explanation
High-temperature fuel gas for rocket engine a kind of to the present invention with embodiment regulates valve below in conjunction with the accompanying drawings
It is described in further 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 accompanying drawing 2 middle section sectional view.
Fig. 4 is motor shaft sleeve structural representation.
Fig. 5 is revolute axes configuration schematic diagram.
Fig. 6 is valve core structure schematic diagram.
Fig. 7 is cold-flow test pressure governing response curve chart.
Fig. 8 is hot-fluid testing pressure governing response curve chart.
In figure
1. valve body 2. connects end cap seal circle 3. and connects end cap 4. appendix insulation 5. spool bracket 6. upper end cover
7. upper end cover sealing ring 8. motor shaft sleeve sealing ring 9. motor shaft sleeve 10. bearing 11. thermal insulation barriers sealing ring
12. thermal insulation barriers 13. rotary shaft 14. spool 15. valve body insulations
Detailed description of the invention
The present embodiment is that a kind of high-temperature fuel gas for rocket engine regulates valve.
Refering to Fig. 1～Fig. 6, the present embodiment is for the high-temperature fuel gas regulation valve of rocket engine, by valve body 1, even
Connect end cap seal circle 2, to connect end cap 3, appendix insulation 4, spool bracket 5, upper end cover 6, upper end cover close
Seal 7, motor shaft sleeve sealing ring 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 15 form.Valve body 1 carries and as the installation matrix of internal part；
Valve body 1 is threaded connection with being connected end cap 3, and valve body 1 is provided with seal groove, seal groove with being connected between end cap 3
Be built-in with connection end cap seal circle 2, it is achieved valve body 1 be connected between end cap 3 sealing；Connect end cap 3 and combustion gas
Pipeline is attached by screw thread, is connecting being installed of being designed with that hexagonal structure is easily installed on end cap 3.Valve body 1
Being bolted with upper end cover 6, valve body 1 upper end has seal groove, and seal groove is built-in with upper end cover and seals
Circle 7, realizes sealing by upper end cover sealing ring 7 between valve body 1 and upper end cover 6；Motor is fixedly mounted on upper end
The top of lid 6.In the present embodiment, valve body 1 all uses 1Cr18Ni9Ti material to add with being connected end cap 3, upper end cover 6
Work.
In the present embodiment, spool 14 is ball-shaped, and spool 14 is central axial has through hole, for blast tube,
Spool 14 top is longitudinally provided with rectangular recess, and rectangular recess centrage and axially extending bore central axis upright；
Spool 14 is arranged in spool bracket 5, and spool 14 and spool bracket 5 are arranged on valve body insulation 15,
Spool 14 coordinates the control realizing circulation area with spool bracket 5；Appendix insulation 4 is fixed on spool torr
Frame 5 two ends respectively be connected end cap 3 and connect, appendix insulation 4 axially has stepped hole and is connected end cap 3
Axial hole is connected；Spool bracket 5 is used for realizing the profit in the sealing of spool 14 and support and rotation process
Sliding, spool bracket 5 uses C/C composite.Appendix insulation 4 protects for the high temperature resistance of pipeline,
Appendix insulation 4 uses high silica phenolic materials to process.Rotary shaft 13 lower end is rectangular cam and spool 14
Rectangular recess be connected, rotary shaft 13 upper end radially has rectangular channel convex with the rectangle of motor shaft sleeve 9 lower end
Block is connected, and is matched in clearance between motor shaft sleeve 9 and rotary shaft 13, it is achieved location and transmission；Spool
14, rotary shaft 13 uses tungsten alloy material to process.Motor shaft sleeve 9 upper end center blind hole medial wall is machined with key
Identifying A in groove, i.e. figure, motor shaft sleeve 9 and motor output shaft are by bonded；On motor shaft sleeve 9 lateral wall
Portion is circumferentially with seal groove, and seal groove is built-in with motor shaft sleeve sealing ring 8, motor shaft sleeve 9 sidewall lower limb week
To there being boss, motor shaft sleeve 9 bottom is provided with rectangular cam；Motor shaft sleeve 9 is joined for gap with rotary shaft 13
Closing, rotary shaft 13 and spool 14 are matched in clearance, it is achieved location and transmission.Thermal insulation barriers 12 is arranged on motor
Between axle sleeve 9 and rotary shaft 13, thermal insulation barriers 12 is used for cutting off by spool 14 to the conduction of heat of motor shaft sleeve 9,
Ensureing the normal operation work of motor, thermal insulation barriers 12 uses high silica phenolic materials to process.Spool 14 and valve
Core bracket 5 is arranged on valve body insulation 15, and valve body insulation 15 is used for isolating internal heat and passes to valve body
Leading, protect valve body, valve body insulation 15 uses high silica phenolic materials to process.
In the present embodiment, motor shaft sleeve 9, rotary shaft 13 rely on rectangular channel to coordinate biography with rectangular cam with spool 14
Dynamic；The seal groove of motor shaft sleeve 9 i.e. figure identifies the mounting groove that B is motor shaft sleeve sealing ring 8, motor shaft sleeve 9
The middle D that identifies is matched in clearance with the rectangular channel of rotary shaft 13 upper end to identify C in the rectangular cam of lower end i.e. figure,
Realize location and transmission.The rectangular cam i.e. figure of rotary shaft 13 lower end identifies E and the rectangular recess on spool 14
I.e. identifying F in figure is matched in clearance, it is achieved location and transmission.
The present embodiment, in realizing the passage contacted with high-temperature fuel gas, all uses high temperature resistant composite and height
Temperature alloy material fabrication and processing, it is achieved high-temperature fuel gas unobstructed；The critical component controlling circulation area is adopted
Use ablation resistant material fabrication and processing, it is achieved keep the immovable feature of circulation area in the course of the work.Circulation
The control of area rotates the realization that coordinates with spool bracket 5 by driven by motor spool 14, and can realize combustion gas
The complete opening and closing of runner.
Installation process
First valve body insulation 15 is fixed in valve body 1；Then spool 14 and spool bracket 5 are arranged on valve
On body insulation 15, it is ensured that the rectangular recess of spool 14 just upper hole to valve body insulation 15；By spool bracket 5
With the correspondence position that the molectron of spool 14 is arranged on valve body insulation 15, both sides are symmetrically installed guarantee spool 14
Position；It is arranged on connecting end cap seal circle 2 in the seal groove of valve body 1, connects end cap 3 and pass through special spanner
It is arranged on valve body 1, again connection end cap 3 is fastened after good rotary shaft 13 to be installed；Rotary shaft 13 is pacified
It is contained on valve body insulation 15 correspondence position, it is ensured that the mark E face of rotary shaft 13 is complete with the mark F face of spool 14
Full cooperation；Thermal insulation barriers 12 is arranged in the rectangular channel of rotary shaft 13；Thermal insulation barriers sealing ring 11 is arranged on valve body
The correspondence position of insulation 15；Motor shaft sleeve 9 is arranged on thermal insulation barriers 12, and the rectangle by motor shaft sleeve 9 is convex
Block is connected with thermal insulation barriers 12；Bearing 10 is fixed on the boss of motor shaft sleeve 9, and corresponding with valve body insulation 15
Position coordinates；Motor shaft sleeve sealing ring 8 is placed in the seal groove of motor shaft sleeve 9；By upper end cover sealing ring 7
It is arranged in the corresponding seal groove of valve body 1；Upper end cover 6 and valve body 1 are bolted fastening.
Refering to Fig. 7, Fig. 8, selection MACR3 servomotor, will by bonded mode as the driving means of valve
Servomotor is connected with motor shaft sleeve 9.Servomotor programming is carried out according to the purpose of test.Pass through high pressure
Nitrogen cylinder connecting line sets up cold-flow test sealing and the checking system of response characteristic, after test valve
Pressure characterizes sealing and the response characteristic of valve.In the case of closing valve closing, open nitrogen cylinder ventilation, check
Whether valve leaks gas, the sealing of checking valve；According to driven by program valve start, the change of pressure after test valve,
The response characteristic of test valve.Cold-flow test is utilized to verify its sealing and response characteristic, verification experimental verification result table
Bright high-temperature fuel gas regulation valve can realize well sealing, and can realize completely closing pipeline, quickly realizes pressure
Response.The gas generator of the solid propellant by using adiabatic combustion temperature to be 1523K, sets up the height of valve
Operating characteristic checking system under the conditions of temperature, and carry out the hot-fluid test of high-temperature fuel gas regulation valve, experimentation
Middle regulation valve regulation is flexible, and output pressure is stable, disassembles each parts and show that high-temperature fuel gas regulates in valve after test
Portion's structure is intact.
Claims (4)
1. one kind for rocket engine high-temperature fuel gas regulation valve, it is characterised in that: include rotary shaft, spool,
Spool bracket, motor shaft sleeve, thermal insulation barriers, valve body insulation, valve body, connection end cap, appendix insulation,
Upper end cover, described spool is ball-shaped, and center spool axially has through hole, and spool top is longitudinally provided with rectangle
Groove, and rectangular recess centrage and axially extending bore central axis upright, spool is positioned at spool bracket, spool
Be arranged on valve body insulation with spool bracket, appendix insulation be positioned at spool bracket two ends respectively be connected
End cap connects, and appendix insulation axially has stepped hole and is connected end cap axial hole and is connected, spool and spool
Bracket engagement realizes the control of circulation area；Described rotary shaft lower end has rectangular cam recessed with the rectangle on spool
Slot fit connects, and rotary shaft upper end radially has the rectangular cam of rectangular channel and motor shaft sleeve lower end and is connected,
Thermal insulation barriers is between motor shaft sleeve and rotary shaft, and thermal insulation barriers is for cutting off by spool to the heat biography of motor shaft sleeve
Lead；Described motor shaft sleeve upper end center blind hole medial wall has keyway, and motor shaft sleeve passes through with motor output shaft
Bonded, top, motor shaft sleeve lateral wall is circumferentially with seal groove, and seal groove is built-in with motor shaft sleeve sealing ring,
Motor shaft sleeve sidewall lower limb circumference has boss, bottom to be provided with rectangular cam, and motor shaft sleeve with rotary shaft is
Matched in clearance, rotary shaft and spool are matched in clearance, it is achieved location and transmission；Described valve body be connected end cap
Threaded, valve body is provided with seal groove with being connected between end cap, and seal groove is built-in with connection end cap seal circle；
Valve body is bolted with upper end cover, is provided with seal groove between valve body and upper end cover, and seal groove is built-in with end
Lid sealing ring；Upper end cover is connected with motor, connects end cap and is connected with fuel gas pipeline, and bearing is positioned at motor shaft sleeve
On boss, it is ensured that the rotation of axle sleeve and axiality, it is provided with between motor shaft sleeve and thermal insulation barriers, valve body insulation
Thermal insulation barriers sealing ring.
High-temperature fuel gas for rocket engine the most according to claim 1 regulates valve, it is characterised in that:
Motor shaft sleeve, thermal insulation barriers, rotary shaft are coaxial with spool.
High-temperature fuel gas for rocket engine the most according to claim 1 regulates valve, it is characterised in that:
Described valve body insulation and described thermal insulation barriers are respectively adopted high silica phenolic materials.
High-temperature fuel gas for rocket engine the most according to claim 1 regulates valve, it is characterised in that:
Described spool and described rotary shaft are respectively adopted tungsten alloy material.
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 true CN105889548A (en) | 2016-08-24 |
| CN105889548B 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 |
|---|---|
| CN (1) | CN105889548B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106321285A (en) * | 2016-08-26 | 2017-01-11 | 南京理工大学 | Poppet valve fixing type gas flow adjusting device of solid rocket ramjet |
| CN111636979A (en) * | 2020-06-08 | 2020-09-08 | 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 |
| CN114636004A (en) * | 2022-05-19 | 2022-06-17 | 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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| 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 |
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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 |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106321285A (en) * | 2016-08-26 | 2017-01-11 | 南京理工大学 | Poppet valve fixing type gas flow adjusting device of solid rocket ramjet |
| CN111636979A (en) * | 2020-06-08 | 2020-09-08 | 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 |
| CN114636004A (en) * | 2022-05-19 | 2022-06-17 | 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105889548B (en) | 2018-07-03 |
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