CN106438108B - It is big to adjust than type solid rocket ramjet gas flow regulating device - Google Patents
It is big to adjust than type solid rocket ramjet gas flow regulating device Download PDFInfo
- Publication number
- CN106438108B CN106438108B CN201610742634.3A CN201610742634A CN106438108B CN 106438108 B CN106438108 B CN 106438108B CN 201610742634 A CN201610742634 A CN 201610742634A CN 106438108 B CN106438108 B CN 106438108B
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- China
- Prior art keywords
- communicating pipe
- pipe
- jet pipe
- gas flow
- transmission shaft
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- Expired - Fee Related
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- 230000001105 regulatory effect Effects 0.000 title claims abstract description 21
- 239000007787 solid Substances 0.000 title claims abstract description 19
- 230000005540 biological transmission Effects 0.000 claims abstract description 34
- 238000002485 combustion reaction Methods 0.000 claims abstract description 16
- 230000008878 coupling Effects 0.000 claims abstract description 11
- 238000010168 coupling process Methods 0.000 claims abstract description 11
- 238000005859 coupling reaction Methods 0.000 claims abstract description 11
- 239000007789 gas Substances 0.000 claims description 25
- 230000007704 transition Effects 0.000 claims description 4
- 239000000567 combustion gas Substances 0.000 claims description 3
- 230000005611 electricity Effects 0.000 claims description 3
- 230000000694 effects Effects 0.000 claims description 2
- 238000003466 welding Methods 0.000 claims description 2
- 239000007921 spray Substances 0.000 abstract description 5
- 230000033001 locomotion Effects 0.000 description 6
- 230000009467 reduction Effects 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 3
- 230000008450 motivation Effects 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 238000004080 punching Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000004886 head movement Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 210000000867 larynx Anatomy 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
- Nozzles (AREA)
Abstract
The invention discloses a kind of big adjustings than type solid rocket ramjet gas flow regulating device, and the jet pipe of flow regulator is combined by the variable jet pipe of the fixed jet pipe of a throat opening area and a throat opening area（Combination spray pipe）, integrally-regulated device is located at outside combustion chamber.Motor is covered positioned at engine end, and motor is connect with transmission shaft using shaft coupling.Transmission shaft, using being threadedly coupled, can be such that cone valve is moved forward and backward with cone valve using screw-driven.Two different jet pipes are connected using communicating pipe, are allowed to generate adjustable gas flow.The configuration of the present invention is simple, the configuration of the present invention is simple, control is accurate, reliable operation, cost is relatively low, has good realizability.
Description
Technical field
The invention belongs to solid rocket ramjet gas flow regulation technology field, specifically a kind of electronic cone valve types
Solid rocket ramjet gas flow regulating device.
Background technology
Solid rocket ramjet has the advantages of punching engine and rocket engine concurrently, have than leaping high, it is small,
The advantages that light-weight, compact-sized, reliable operation, relatively low cost.For guarantee engine with best working performance and well
Thrust regulating power, solid rocket ramjet should carry out gas flow adjusting.The side adjusted at present about gas flow
Case mainly has firm discharge formula, formula of being jammed, non-four kinds of formula and the whirlpool valve type of being jammed.The configuration of flow control valve generally use has column
It is a variety of to fill in guiding valve, rotation cam valve, rotation sliding plate valve, cone valve etc..The transmission mechanism that traditional control system uses generally has hydraulic pressure
Transmission, Mechanical ＆ Electrical Transmission, Pneumatic Transmission.According to working environment and work characteristics, motor drive and Pneumatic Transmission are better than hydraulic drive.
Formula solid rocket ramjet gas flow regulating device of being jammed at present generally uses electric sliding moushroom valve or pneumatic
Formula pin valve device.A kind of gas-flow regulator (patent No. for solid rocket ramjet of Bao Wen, Niu Wenyu etc.
200810075649.4) propose a kind of gas flow of the solid rocket ramjet of pneumatic needle valve type gas consumption adjusting valve
Regulating system, it mainly relies on valve head chamber pressure, driving valve head movement to carry out adjustment of combustion gas flow.Although simple in structure, sound
It answers speed fast, but needs to increase an air machinery, space is larger, since gas is susceptible to leakage, in regulating gas
During flow, it is not easy to reach and accurately controls.Northwestern Polytechnical University Wang Yi woodss propose a kind of jet pipe and combustion chamber at
90 degree of non-coaxial needle valve type gas flow regulating system, although larynx tightening latch easily sealing and thermal protection is easy to implement, experiment system
Volume of uniting is big, cannot reach and accurately control.
Invention content
The purpose of the present invention is to provide a kind of simple in structure, reliable operation, accurate, the low-cost big adjusting ratios of control
Type solid rocket ramjet gas flow regulating device.
Realize that technical solution of the invention is：It is a kind of to adjust than type solid rocket ramjet gas flow tune greatly
Regulating device, including stepper motor, shaft coupling, transmission shaft, cone valve, the first jet pipe, the second jet pipe, communicating pipe, combustion chamber and hair
Motivation end cap；Stepper motor is fixed on engine end and covers, and motor shaft is vertical with end cap face, and stepper motor is with transmission shaft using connection
Axis device is coaxially connected, and transmission shaft is connected through a screw thread with cone valve；It is divided into active segment, transition and fixed section communicating pipe, is driven
Axis uses screw-driven, the first jet pipe to be connected through a screw thread with communicating pipe active segment with communicating pipe active segment, the second jet pipe and company
Siphunculus fixed section one end is connected through a screw thread, communicating pipe the other end of fixed section be fixed on engine end and cover, communicating pipe is fixed
Section and combustion chamber, cone valve pass through the first nozzle throat.
Compared with prior art, the present invention its remarkable advantage：
(1) present invention is compared with traditional tapered valve flow control device, using the fixed jet pipe of a throat opening area and one
The variable jet pipe of a throat opening area is combined into flow regulator, improves throat opening area and adjusts ratio, transmission mechanism is located at hair
Outside motivation combustion chamber, is conducive to carry out igniting experiments, is also beneficial to the follow-up improvement of regulating device.
(2) compared to the traditional cone valve type flow regulator of only single spraying pipe, combination spray pipe is used in of the invention,
Reduce the technological requirement that can be changed jet pipe and cone valve to throat opening area.
(3) transmission mechanism of the present invention is relatively easy, reliable operation, and regulative mode is easier to realize.
Description of the drawings
Attached drawing is big adjusting of the invention than type solid rocket ramjet gas flow regulating device sectional view.
Specific implementation mode
The big adjusting of the present invention is fixed than type solid rocket ramjet gas flow regulating device by a throat opening area
Jet pipe and the variable jet pipe of a throat opening area be combined into the jet pipe (combination spray pipe) of flow regulator, integrally-regulated device
Outside combustion chamber.Specifically include stepper motor, shaft coupling, transmission shaft, cone valve, the first jet pipe, the second jet pipe, communicating pipe
The combustion chamber and.Stepper motor is fixed on engine end and covers, and stepper motor is coaxially connected with transmission shaft using shaft coupling, transmission shaft
It uses screw-driven, transmission shaft to be threadedly coupled with cone valve between communicating pipe, there is sealing ring between transmission shaft and communicating pipe.
Combination spray pipe is overlapped perpendicular to end cover of combustion chamber, taper valve axis with nozzle axis, and movable cone valve and the first jet pipe are constituted
Solid rocket ramjet gas flow regulating device.
Present invention is further described in detail below in conjunction with the accompanying drawings.
In conjunction with Fig. 1, adjusted greatly than type solid rocket ramjet gas flow regulating device the present invention relates to a kind of,
Including stepper motor 1, shaft coupling 2, transmission shaft 3, cone valve 4, the first jet pipe 5, the second jet pipe 6, communicating pipe 7, combustion chamber 8.Step
Stepper motor 1 is fixed on the side that engine end covers, and stepper motor 1 is coaxially connected with transmission shaft 3 using shaft coupling.Transmission shaft
(3) with cone valve 4 using being threadedly coupled, transmission shaft 3 with use screw-driven communicating pipe 7, the first jet pipe 5, the second jet pipe 6 and connect
Siphunculus 7 is threadedly coupled, and cone valve 4 passes through 5 throat of the first jet pipe, has sealing ring between transmission shaft 3 and communicating pipe 7.By stepping
Motor 1, shaft coupling 2, transmission shaft 3, cone valve 4, the first jet pipe 5,7 part of communicating pipe assembly as solid-rocket punching press send out
The variable jet pipe of the throat opening area of motivation, adjusts the gas flow of rocket ramjet, and whole flow regulator is located at combustion
Burn the outside of room.
Embodiment：
It is a kind of to adjust than type solid rocket ramjet gas flow regulating device greatly in conjunction with Fig. 1 comprising stepping electricity
Machine 1, shaft coupling 2, transmission shaft 3, cone valve 4, the first jet pipe 5, the second jet pipe 6, communicating pipe 7, combustion chamber 8, end cover of engine 9；
Stepper motor 1 is fixed on engine end and covers, and motor shaft is vertical with end cap face, and stepper motor 1 uses shaft coupling 2 with transmission shaft 3
Coaxially connected, transmission shaft (3), using being threadedly coupled, divides communicating pipe 7 for active segment, transition and fixed section, transmission with cone valve 4
Axis 3 uses screw-driven, the first jet pipe 5 to use and be threadedly coupled with 7 active segment of communicating pipe with 7 active segment of communicating pipe, the second jet pipe
6, end cover of engine 9 is threadedly coupled with 7 fixed section of communicating pipe, and cone valve 4 passes through 5 throat of the first jet pipe.Divide communicating pipe 7 to live
Dynamic section, transition and fixed section, active segment is axially parallel with fixed section, and changeover portion is with active segment, fixed section using welding.Igniting
When experiment, pressure tap should be also opened on combustion chamber 8, and load onto sensor.
When carrying out igniting experiments, stepper motor 1 receives the instruction that controller is sent out and rotates, the biography for driving motor shaft connected
Moving axis 3 rotates；By thread transmission, transmission shaft 3 is along 5 axial-movement of the first jet pipe；The movement of transmission shaft 3 will drive and it
The axial movement of connected cone valve 4, the effective area of i.e. changeable 2 throat of jet pipe of up and down motion of cone valve 4.Nozzle throat
The variation of effective area can achieve the effect that control gas flow with the pressure and propellant burning rate in change burning room 9.
When certain characteristics of motion is presented in the movement of cone valve (4), the effective area of combination spray pipe throat is also presented one
Fixed changing rule, to achieve the purpose that adjust combustion chamber pressure and gas flow at random.It is combustion gas stream by pressure sensor
It measures regulation closed-loop control system and feedback signal is provided, when needing to increase (or reduction) gas flow, controlled by stepper motor (1)
Cone valve (4) (or upward) movement downwards, can accurately calculate throat opening area by displacement at this time.Nozzle throat significant surface
When product reduces (or increase), combustion chamber (8) internal pressure increases (or reduction), and propellant burning rate increases (or reduction), to make
Gas flow also increases (or reduction).
Claims (2)
1. a kind of big adjusting is than type solid rocket ramjet gas flow regulating device, it is characterised in that：Including stepping electricity
Machine（1）, shaft coupling（2）, transmission shaft（3）, cone valve（4）, the first jet pipe（5）, the second jet pipe（6）, communicating pipe（7）, combustion chamber
（8）And end cover of engine（9）；Stepper motor（1）It is fixed on end cover of engine（9）On, motor shaft is vertical with end cap face, stepping electricity
Machine（1）With transmission shaft（3）Using shaft coupling（2）It is coaxially connected, transmission shaft (3) and cone valve（4）It is connected through a screw thread；Communicating pipe
（7）It is divided into active segment, transition and fixed section, transmission shaft（3）With communicating pipe（7）Active segment uses screw-driven, the first jet pipe
（5）With communicating pipe（7）Active segment is connected through a screw thread, the second jet pipe（6）With communicating pipe（7）Fixed section one end is connected by screw thread
It connects, communicating pipe（7）The other end of fixed section is fixed on end cover of engine（9）On, communicating pipe（7）Fixed section and combustion chamber（8）Even
It is logical, cone valve（4）Across the first jet pipe（5）Throat.
2. big adjusting according to claim 1 is than type solid rocket ramjet gas flow regulating device, feature
It is：The communicating pipe（7）In active segment it is axially parallel with fixed section, changeover portion and active segment, fixed section pass through the company of welding
Logical, combustion gas can be by communicating pipe（7）Fixed section enter communicating pipe（7）Changeover portion, subsequently into communicating pipe（7）Activity
Section, hence into the first jet pipe（5）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610742634.3A CN106438108B (en) | 2016-08-26 | 2016-08-26 | It is big to adjust than type solid rocket ramjet gas flow regulating device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610742634.3A CN106438108B (en) | 2016-08-26 | 2016-08-26 | It is big to adjust than type solid rocket ramjet gas flow regulating device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106438108A CN106438108A (en) | 2017-02-22 |
| CN106438108B true CN106438108B (en) | 2018-10-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610742634.3A Expired - Fee Related CN106438108B (en) | 2016-08-26 | 2016-08-26 | It is big to adjust than type solid rocket ramjet gas flow regulating device |
Country Status (1)
| Country | Link |
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| CN (1) | CN106438108B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107503863A (en) * | 2017-09-06 | 2017-12-22 | 中国航空救生研究所 | A kind of nozzle thrust governor motion of solid propellant rocket |
| CN109225694A (en) * | 2018-09-30 | 2019-01-18 | 南昌大学 | Adjustable melange effect deashing device for pulse blow filter |
| CN112746911B (en) * | 2020-12-29 | 2022-07-19 | 上海空间推进研究所 | Variable thrust engine flow regulating device and on-orbit protection method |
| CN115387934B (en) * | 2022-09-14 | 2024-05-28 | 北京中科宇航技术有限公司 | Solid rocket engine and throat adjusting device thereof |
| CN116221777A (en) * | 2023-02-20 | 2023-06-06 | 中国船舶重工集团公司第七0三研究所 | Combustion chamber head structure with adjustable runner |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5946904A (en) * | 1997-08-12 | 1999-09-07 | Boehnlein; John J. | Ejector ramjet engine |
| JP3510527B2 (en) * | 1999-06-04 | 2004-03-29 | 三菱重工業株式会社 | Lateral thrust control device |
| CN1611761A (en) * | 2003-10-31 | 2005-05-04 | 王德强 | Super combustion pressed engine |
| CN103410632A (en) * | 2013-08-09 | 2013-11-27 | 南京理工大学 | Electric conical valve type gas flow regulator for solid rocket ramjets |
| CN105257429A (en) * | 2015-11-30 | 2016-01-20 | 清华大学 | Combined type rocket engine |
| CN105736179A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Gas flow adjusting device of solid rocket ramjet |
-
2016
- 2016-08-26 CN CN201610742634.3A patent/CN106438108B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5946904A (en) * | 1997-08-12 | 1999-09-07 | Boehnlein; John J. | Ejector ramjet engine |
| JP3510527B2 (en) * | 1999-06-04 | 2004-03-29 | 三菱重工業株式会社 | Lateral thrust control device |
| CN1611761A (en) * | 2003-10-31 | 2005-05-04 | 王德强 | Super combustion pressed engine |
| CN103410632A (en) * | 2013-08-09 | 2013-11-27 | 南京理工大学 | Electric conical valve type gas flow regulator for solid rocket ramjets |
| CN105257429A (en) * | 2015-11-30 | 2016-01-20 | 清华大学 | Combined type rocket engine |
| CN105736179A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Gas flow adjusting device of solid rocket ramjet |
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| Publication number | Publication date |
|---|---|
| CN106438108A (en) | 2017-02-22 |
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Granted publication date: 20181012 |