CN106438108A - Large-regulation-ratio type fuel gas flow regulation device for solid rocket ramjet - Google Patents
Large-regulation-ratio type fuel gas flow regulation device for solid rocket ramjet Download PDFInfo
- Publication number
- CN106438108A CN106438108A CN201610742634.3A CN201610742634A CN106438108A CN 106438108 A CN106438108 A CN 106438108A CN 201610742634 A CN201610742634 A CN 201610742634A CN 106438108 A CN106438108 A CN 106438108A
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- China
- Prior art keywords
- communicating pipe
- gas flow
- transmission shaft
- canned paragraph
- pipe
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Classifications
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- 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
Abstract
The invention discloses a large-regulation-ratio type fuel gas flow regulation device for a solid rocket ramjet. A jet nozzle (combined jet nozzle) of the flow regulation device is composed of a jet nozzle with a fixed throat area and a jet nozzle with a variable throat area; and the whole regulation device is located at the outer part of a combustion chamber. A motor is located on a ramjet end cap; and the motor is connected with a transmission shaft through a shaft coupler. The transmission shaft is connected with a cone valve through a thread; and the cone valve can move frontward and backward through adopting thread driving. By connecting two different jet nozzles through a communicating pipe, an adjustable fuel gas flow is generated. The large-regulation-ratio type fuel gas flow regulation device for the solid rocket ramjet has a simple structure and has the advantages of simple structure, accuracy in controlling, reliability in working, relatively low cost and good implementability.
Description
Technical field
The invention belongs to solid rocket ramjet gas flow regulation technology field, specifically a kind of electronic cone valve type
Solid rocket ramjet gas flow adjusting means.
Background technology
Solid rocket ramjet has the advantage of punching engine and rocket engine concurrently, have than leaping high, small volume,
The advantages of lightweight, compact conformation, reliable operation, cost are relatively low.For ensureing that engine has optimal service behaviour and good
Thrust regulating power, solid rocket ramjet should carry out gas flow regulation.The side adjusting with regard to gas flow at present
Case mainly has firm discharge formula, formula of being jammed, non-formula and four kinds of the whirlpool valve type of being jammed.The configuration that flow control valve generally adopts has post
Plug guiding valve, rotation cam valve, rotation sliding plate valve, cone valve etc. are multiple.The transmission mechanism that traditional control system adopts typically has hydraulic pressure
Transmission, Mechanical ＆ Electrical Transmission, Pneumatic Transmission.According to working environment and work characteristics, motor transmission and Pneumatic Transmission are better than hydraulic drive.
The commonly used electric sliding moushroom valve or pneumatic of formula of being jammed at present solid rocket ramjet gas flow adjusting means
Formula pin valve device.A kind of gas-flow regulator for solid rocket ramjet of Bao Wen, Niu Wenyu etc.（The patent No.
200810075649.4）A kind of gas flow of the solid rocket ramjet of pneumatic needle valve type gas consumption adjusting valve is proposed
Regulating system, it mainly relies on valve head chamber pressure, drives valve head motion to carry out adjustment of combustion gas flow.Although structure is simple, sound
Answer speed fast, but need to increase an air machinery, take up an area space larger, because leaking easily occurs in gas, in regulating gas
During flow, it is not easy to reach precise control.Northwestern Polytechnical University Wang Yi woods is proposed a kind of jet pipe and is become with combustion chamber
90 degree of non-coaxial needle valve type gas flow regulating system is although larynx tightening latch easily sealing and thermal protection are easily realized, but experiment system
System volume is greatly it is impossible to reach precise control.
Content of the invention
It is an object of the invention to provide a kind of structure is simple, reliable operation, control big regulation ratio accurate, with low cost
Type solid rocket ramjet gas flow adjusting means.
The technical solution realizing the present invention is：A kind of big regulation is adjusted than type solid rocket ramjet gas flow
Regulating device, including stepper motor, shaft coupling, power transmission shaft, cone valve, the first jet pipe, the second jet pipe, communicating pipe, combustion chamber and send out
Motivation end cap；Stepper motor is fixed on engine end lid, and motor shaft is vertical with end cap face, and stepper motor and power transmission shaft are using connection
Axial organ is coaxially connected, and power transmission shaft is threaded connection with cone valve；It is divided into active segment, transition and canned paragraph communicating pipe, transmission
Axle adopts screw-driven with communicating pipe active segment, and the first jet pipe is threaded connection with communicating pipe active segment, the second jet pipe and company
Siphunculus canned paragraph one end is threaded connection, communicating pipe the other end of canned paragraph be fixed on engine end lid, communicating pipe is fixed
Section and combustion chamber, cone valve passes through the first nozzle throat.
The present invention compared with prior art, its remarkable advantage：
（1）The present invention compared with traditional tapered valve flow control device, using the fixing jet pipe of throat opening area and a larynx
The jet pipe of portion's variable area is combined into flow regulator, improves throat opening area and adjusts ratio, its transmission mechanism is located at engine
Outside combustion chamber, be conducive to carrying out igniting experiments, be also beneficial to the follow-up improvement of adjusting means.
（2）Compared to the traditional cone valve type flow regulator of only single spraying pipe, in the present invention, employ combination spray pipe,
Reduce the technological requirement of variable jet pipe and cone valve to throat opening area.
（3）Transmission mechanism of the present invention is relatively easy, reliable operation, and its regulative mode is easier to realize.
Brief description
Accompanying drawing is that the present invention is big to be adjusted than type solid rocket ramjet gas flow adjusting means profile.
Specific embodiment
The present invention is big to adjust ratio type solid rocket ramjet gas flow adjusting means, is fixed by a throat opening area
Jet pipe and variable jet pipe of throat opening area be combined into the jet pipe of flow regulator（Combination spray pipe）, integrally-regulated device
Outside combustion chamber.Specifically include stepper motor, shaft coupling, power transmission shaft, cone valve, the first jet pipe, the second jet pipe, communicating pipe
And combustion chamber.Stepper motor is fixed on engine end lid, and stepper motor is coaxially connected using shaft coupling with power transmission shaft, power transmission shaft
Adopt screw-driven and communicating pipe between, power transmission shaft has sealing ring with cone valve with threadeding between power transmission shaft and communicating pipe.
Combination spray pipe is overlapped with nozzle axis perpendicular to end cover of combustion chamber, taper valve axis, and the cone valve of activity and the first jet pipe are constituted
Solid rocket ramjet gas flow adjusting means.
Below in conjunction with the accompanying drawings the present invention is described in further detail.
In conjunction with Fig. 1, the present invention relates to a kind of big regulation ratio type solid rocket ramjet gas flow adjusting means, its
Including stepper motor 1, shaft coupling 2, power 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 on engine end lid, and stepper motor 1 is coaxially connected using shaft coupling with power transmission shaft 3.Power transmission shaft
(3) adopt with cone valve 4 and threaded, power transmission shaft 3 with communicating pipe 7 adopt screw-driven, the first jet pipe 5, the second jet pipe 6 with even
With threaded, cone valve 4 passes through the first jet pipe 5 throat to siphunculus 7, has sealing ring between power transmission shaft 3 and communicating pipe 7.By stepping
Motor 1, shaft coupling 2, power transmission shaft 3, cone valve 4, the first jet pipe 5, the assembly of communicating pipe 7 part are sent out as solid-rocket punching press
The variable jet pipe of the throat opening area of motivation, adjusts the gas flow of rocket ramjet, and overall flow regulator is located at combustion
Burn the outside of room.
Embodiment：
In conjunction with Fig. 1, a kind of big adjust ratio type solid rocket ramjet gas flow adjusting means, it include stepper motor 1,
Shaft coupling 2, power 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；Stepping
Motor 1 is fixed on engine end lid, and motor shaft is vertical with end cap face, and stepper motor 1 and power transmission shaft 3 adopt shaft coupling 2 coaxial
Connect, power transmission shaft (3) is adopted with cone valve 4 threadeds, and is divided into active segment, transition and canned paragraph, power transmission shaft 3 communicating pipe 7
Adopt screw-driven with communicating pipe 7 active segment, the first jet pipe 5 with communicating pipe 7 active segment adopt threadeds, the second jet pipe 6, send out
With communicating pipe 7 canned paragraph with threadeding, cone valve 4 passes through the first jet pipe 5 throat to motivation end cap 9.Communicating pipe 7 is divided into activity
Section, transition and canned paragraph, active segment and canned paragraph are axially in parallel, and changeover portion and active segment, canned paragraph are using welding.Igniting is real
When testing, also should open pressure tap on combustion chamber 8, and load onto sensor.
When carrying out igniting experiments, stepper motor 1 accepts instruction that controller sends and rotates, the biography that drive motor axle is connected
Moving axis 3 rotates；By thread transmission, power transmission shaft 3 is along the first jet pipe 5 axial-movement；The motion of power transmission shaft 3 will drive and it
The axially-movable of connected cone valve 4, the up and down motion of cone valve 4 can change the effective area of jet pipe 2 throat.Nozzle throat
The change of effective area can reach, with the pressure in change burning room 9 and propellant burning rate, the effect controlling gas flow.
When the motion of cone valve 4 assumes certain characteristics of motion, the effective area of combination spray pipe throat also presents necessarily
Changing Pattern, thus reaching the random purpose adjusting combustion chamber pressure and gas flow.It is gas flow by pressure sensor
Regulation closed-loop control system provide feedback signal, when need increase（Or reduce）During gas flow, taper is controlled by stepper motor 1
Valve 4 is downward（Or upwards）Motion, can accurately calculate throat opening area now by displacement.Nozzle throat effective area reduces
（Or increase）When, combustion chamber 8 internal pressure increases（Or reduce）, propellant burning rate increase（Or reduce）, so that gas flow
Also increase（Or reduce）.
Claims (2)
1. a kind of big adjust than type solid rocket ramjet gas flow adjusting means it is characterised in that：Including stepping electricity
Machine（1）, shaft coupling（2）, power 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 power transmission shaft（3）Using shaft coupling（2）Coaxially connected, power transmission shaft (3) and cone valve（4）It is threaded connection；Communicating pipe
（7）It is divided into active segment, transition and canned paragraph, power transmission shaft（3）With communicating pipe（7）Active segment adopts screw-driven, the first jet pipe
（5）With communicating pipe（7）Active segment is threaded connection, the second jet pipe（6）With communicating pipe（7）Canned paragraph one end is by screw thread even
Connect, communicating pipe（7）The other end of canned paragraph is fixed on end cover of engine（9）On, communicating pipe（7）Canned paragraph and combustion chamber（8）Even
Logical, cone valve（4）Through the first jet pipe（5）Throat.
2. big regulation ratio type solid rocket ramjet gas flow adjusting means according to claim 1, its feature
It is：Described communicating pipe（7）In active segment and canned paragraph axially in parallel, changeover portion and active segment, canned paragraph pass through welding even
Logical, combustion gas can be by communicating pipe（7）Canned paragraph 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 true CN106438108A (en) | 2017-02-22 |
| CN106438108B CN106438108B (en) | 2018-10-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610742634.3A Active CN106438108B (en) | 2016-08-26 | 2016-08-26 | It is big to adjust than type solid rocket ramjet gas flow regulating device |
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Cited By (3)
| 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 |
| CN112746911A (en) * | 2020-12-29 | 2021-05-04 | 上海空间推进研究所 | Variable thrust engine flow regulating device and on-orbit protection method |
Family Cites Families (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 |
| CN1318748C (en) * | 2003-10-31 | 2007-05-30 | 王德强 | Super combustion pressed engine |
| CN103410632B (en) * | 2013-08-09 | 2015-06-17 | 南京理工大学 | Electric conical valve type gas flow regulator for solid rocket ramjets |
| CN105257429B (en) * | 2015-11-30 | 2017-03-08 | 清华大学 | Composite rocket engine |
| CN105736179B (en) * | 2016-02-18 | 2018-07-17 | 江西洪都航空工业集团有限责任公司 | A kind of solid rocket ramjet gas flow regulating device |
-
2016
- 2016-08-26 CN CN201610742634.3A patent/CN106438108B/en active Active
Cited By (4)
| 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 |
| CN112746911A (en) * | 2020-12-29 | 2021-05-04 | 上海空间推进研究所 | Variable thrust engine flow regulating device and on-orbit protection method |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106438108B (en) | 2018-10-12 |
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