CN104373248B - Vacuum jet nozzle - Google Patents
Vacuum jet nozzle Download PDFInfo
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- CN104373248B CN104373248B CN201410588807.1A CN201410588807A CN104373248B CN 104373248 B CN104373248 B CN 104373248B CN 201410588807 A CN201410588807 A CN 201410588807A CN 104373248 B CN104373248 B CN 104373248B
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- discharge
- injection pipe
- liquid
- nozzle
- vacuum jet
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Abstract
According to a kind of vacuum jet nozzle provided by the invention, when it can improve the discharge of spacecraft liquid in-orbit, the nozzle that floss hole near wall is polluted.The present invention keeps channel interior pressure by circular arc contraction mouth, slows down flash distillation and icing so that discharge in orbit can be smoothed out, and it is relatively low to go out flowing liquid air content, atomization cone angle is less, and pipeline inner wall is smooth and ozzle lip is sharp keen can prevent ice pellets from adhering to, and makes discharge smooth.
Description
Technical field
The present invention relates to vacuum jet nozzle, in particular it relates to when the present invention relates to the discharge of spacecraft liquid in-orbit, the device of liquid atomization cone angle can be improved.
Background technology
The discharge of final vehicle tank residual propellant, the high-altitude ignition of rocket engine, international space station add pipeline residual propellant blowing etc., are directed to the vacuum jet of liquid.When liquid enters vacuum, owing to overheated meeting is acutely vaporized flash distillation, forming atomization cone angle, this cone angle is likely to the spacecraft wall near the disposal of pollutants mouth of pipe, and the characteristics such as the optics of spacecraft, mechanics are produced impact, and the normal operation affecting spacecraft notably slows down its life-span.At present, it is devoted to slow down the measure that liquid vacuum discharge pollutes both at home and abroad and is concentrated mainly on the temperature and speed that change liquid discharge, and change above the caliber etc. of discharge pipe.Although these measures can improve the atomization cone angle of liquid vacuum jet to a certain extent, but there are many restrictions in the application, such as low-temperature and high-speed and pipe with small pipe diameter can improve stream atomization cone angle, but the too low caliber of temperature is too small, in discharge process, pipeline very easily ice blocks up and hinders being smoothed out of liquid vacuum discharge, and excessive velocities is then likely to the attitude of spacecraft is caused bigger disturbance.
Summary of the invention
For defect of the prior art; in order to solve these problems; find better discharge approach; the present invention proposes a kind of vacuum jet nozzle; this nozzle can when not changing liquid initial exhaust temperature, speed and discharge caliber; it is effectively improved the atomization cone angle of liquid discharge stream, the spacecraft wall near the protection discharge mouth of pipe.
According to a kind of vacuum jet nozzle provided by the invention, including injection pipe, the inner wall smooth of injection pipe, the internal diameter of the mouthpiece portion of injection pipe shrinks；
The internal diameter of injection pipe is along injection direction, to the nozzle lip of mouthpiece portion from the porch of mouthpiece portion, radius R circular arc and the R/2 being contracted to；
Nozzle lip place is sharp keen.
Preferably, the inner wall roughness of injection pipe is 1.6.
Compared with prior art, the present invention has following beneficial effect:
The present invention can when not changing Spacecraft guidance and control and not additional subsystem, improve spacecraft liquid in-orbit discharge time, to floss hole near wall pollute nozzle.The present invention keeps channel interior pressure by circular arc contraction mouth, slows down flash distillation and icing so that discharge in orbit can be smoothed out, and it is relatively low to go out flowing liquid air content, atomization cone angle is less, and pipeline inner wall is smooth and ozzle lip is sharp keen can prevent ice pellets from adhering to, and makes discharge smooth.
Accompanying drawing explanation
By reading detailed description non-limiting example made with reference to the following drawings, the other features, objects and advantages of the present invention will become more apparent upon:
Fig. 1 is principles of the invention figure.
In figure:
1--injection pipe；
2--mouthpiece portion；
The entrance of 3--mouthpiece portion；
4 nozzle lips.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in detail.Following example will assist in those skilled in the art and are further appreciated by the present invention, but do not limit the present invention in any form.It should be pointed out that, to those skilled in the art, without departing from the inventive concept of the premise, it is also possible to make some deformation and improvement.These broadly fall into protection scope of the present invention.
The present invention improves liquid vacuum jet atomization cone angle and be the technical scheme is that the smooth tapering type mouth of pipe of sharp keen circular arc of employing.The tapering type mouth of pipe has pressurize effect, the vacuum environment pressure conduction to channel interior can be effectively completely cut off when vacuum discharge, channel interior is made to maintain under higher pressure environment, under of a relatively high pressure environment, liquid flashes and vaporization are comparatively slow, the air content of liquid internal decreases so that go out when flowing the air bubble content of liquid atomization its Main Function broken is less, thus slow down the atomization cone angle of liquid discharge stream.Employing smooth inner wall design so that channel interior because of flash distillation freeze time, ice pellets attachment on tube wall is less, and discharge can be smoothed out.Lip is sharp keen also can slow down the ice pellets attachment at ozzle place, it is prevented that ozzle form is changed the liquid discharge stream morphologic change caused, thus liquid jet form is maintained controlled range.
Specifically, in FIG, the nozzle lip place diameter as mouthpiece portion outlet of vacuum jet nozzle, half for the internal caliber of the injection pipe before the porch of mouthpiece portion, play pressure maintaining effect, the channel interior roughness of injection pipe is 1.6, does not make chamfered, keep sharp keen after lip cutting.
About the design parameter that the above present invention adopts, it shall be noted that:
(1) internal diameter of injection pipe is along injection direction, to the nozzle lip of mouthpiece portion from the porch of mouthpiece portion, radius R circular arc and the R/2 being contracted to
This circular arc contraction data is by analyzing the characteristic that under normal pressure, jet situation and vacuum flashing acutely expand, the optimization band that modeling and simulating is comparatively optimized on this basis, optimizing the nozzle processing several different angles different cross section shapes with interval, experiment proves that and show under the numerical value that this circular arc contraction data requires, jet situation is optimum, goes out to flow efflux angle minimum.
(2) inner wall roughness of injection pipe is 1.6
This roughness is after analyzing vacuum jet flash vaporization mechanism, it was shown that acutely heat exchange can cause freezing, it is possible to ice can be caused to block up, and for reducing the probability frozen, reduces icing attachment point, the higher roughness grade number that can reach when being provide applicable industry.
Above specific embodiments of the invention are described.It is to be appreciated that the invention is not limited in above-mentioned particular implementation, those skilled in the art can make various deformation or amendment within the scope of the claims, and this has no effect on the flesh and blood of the present invention.
Claims (2)
1. a vacuum jet nozzle, including injection pipe, it is characterised in that the inner wall smooth of injection pipe, and the internal diameter of the mouthpiece portion of injection pipe shrinks；
The internal diameter of injection pipe is along injection direction, to the nozzle lip of mouthpiece portion from the porch of mouthpiece portion, radius R circular arc is contracted to R/2；
Nozzle lip place is sharp keen.
2. vacuum jet nozzle according to claim 1, it is characterised in that the inner wall roughness of injection pipe is 1.6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410588807.1A CN104373248B (en) | 2014-10-28 | 2014-10-28 | Vacuum jet nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410588807.1A CN104373248B (en) | 2014-10-28 | 2014-10-28 | Vacuum jet nozzle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104373248A CN104373248A (en) | 2015-02-25 |
| CN104373248B true CN104373248B (en) | 2016-07-06 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410588807.1A Active CN104373248B (en) | 2014-10-28 | 2014-10-28 | Vacuum jet nozzle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104373248B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106996349A (en) * | 2017-04-19 | 2017-08-01 | 四川森洁燃气设备有限公司 | A kind of combustion gas adjustable type spout structure |
| CN107187618B (en) * | 2017-05-27 | 2019-08-16 | 上海航天控制技术研究所 | Gas propellant control system and control method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1240882A (en) * | 1998-07-07 | 2000-01-12 | 刘茂本 | Atomizing nozzle of fuel |
| CN1584316A (en) * | 2004-06-04 | 2005-02-23 | 徐小宁 | Fuel atomizing nozzles |
| EP2143927B1 (en) * | 2008-07-11 | 2012-02-29 | Snecma | Liquid-propellant rocket engine with propulsion chamber blanking plug |
| CN103644044A (en) * | 2013-11-26 | 2014-03-19 | 北京航空航天大学 | Multi-component simulative engine applied to vacuum plume effect experimental research and ignition scheme thereof |
-
2014
- 2014-10-28 CN CN201410588807.1A patent/CN104373248B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1240882A (en) * | 1998-07-07 | 2000-01-12 | 刘茂本 | Atomizing nozzle of fuel |
| CN1584316A (en) * | 2004-06-04 | 2005-02-23 | 徐小宁 | Fuel atomizing nozzles |
| EP2143927B1 (en) * | 2008-07-11 | 2012-02-29 | Snecma | Liquid-propellant rocket engine with propulsion chamber blanking plug |
| CN103644044A (en) * | 2013-11-26 | 2014-03-19 | 北京航空航天大学 | Multi-component simulative engine applied to vacuum plume effect experimental research and ignition scheme thereof |
Non-Patent Citations (2)
| Title |
|---|
| 基于Fluent模拟分析的真空下液体射流嘴型的选型;韩宇，李建昌;《真空》;20121031;第6卷(第6期);正文第3.2节，附图1（b） * |
| 火箭剩余推进剂排放过程的分析与模拟;樊青，刘宏立，蒋建政;《力学学报》;20040331;第36卷(第2期);正文第1-3节，附图1、9-11 * |
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| Publication number | Publication date |
|---|---|
| CN104373248A (en) | 2015-02-25 |
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