CN106640423B - The flow resistance regulating device of low thrust liquid attitude control engine unit - Google Patents
The flow resistance regulating device of low thrust liquid attitude control engine unit Download PDFInfo
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- CN106640423B CN106640423B CN201611031030.4A CN201611031030A CN106640423B CN 106640423 B CN106640423 B CN 106640423B CN 201611031030 A CN201611031030 A CN 201611031030A CN 106640423 B CN106640423 B CN 106640423B
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- ring
- valve
- flow resistance
- restricting orifice
- regulating device
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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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
- F02K9/58—Propellant feed valves
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Magnetically Actuated Valves (AREA)
Abstract
The present invention provides a kind of flow resistance regulating devices of low thrust liquid attitude control engine unit, including thrust chamber shell conduit, zigzag ring-type restricting orifice and solenoid valve, it is provided with propellant inlet hole and outlet opening on the thrust chamber shell conduit, and it is provided with annular liquid collecting cavity before the thrust chamber valve for installing zigzag ring-type restricting orifice, annular liquid collecting cavity is in before solenoid valve import before the valve, restricting orifice after alternative installation valve after the solenoid valve.The present invention has the ability of depth throttling, and has the characteristics that good rectification effect, compact-sized, inhibition water attack, good manufacturability.
Description
Technical field
The present invention relates to a kind of flow resistance regulating devices of low thrust liquid attitude control engine unit.
Background technology
Flow resistance adjusting to the effect that passes through specific regulating measure, the tune of realization fluid component running parameter
Whole, flow measurement, water attack inhibition and the compensation of component flow behavior individual difference and matching etc..
In recent years, Nanjing University of Technology has studied the restriction characteristic of special-shaped valve port in multiple directional control valve, and wherein U-shaped valve port exists
Flow saturation is easy to happen when aperture is larger, and V-arrangement valve port is stronger to the controllability of flow.Tongji University is more in comparative study
After kind abnormity throttling cross sectional shape, it is proposed that a kind of novel cylindrical variable cross-section buffer structure, studies have shown that the structure is with slow
Good effect, design convenience of calculation, advantage simple in structure, easy to process are rushed, the design of most of hydraulic cylinders is can be applied to.
In chemical field, Tianjin chemical design institute is flowed for large scale pipeline, is based on traditional standard single hole AND DEWATERING FOR ORIFICE STRUCTURE, has been carried out more
The research of hole orifice plate forms the symmetrical structure of flowing by adding function hole, it is suppressed that vortex, to improve the stabilization in flow field
Property, reduce vibration and the noise of flowing.In spacecraft space Push Technology field, presently relevant research work is concentrated mainly on
In the research of gas circuit pressure reducing valve, gas circuit pressure reducing valve is to design very cleverly gas throttling and control assembly, by high pressure chest, low
The design of chamber and low pressure adjusting cavity is pressed, pressure feedback mechanism, the automatic throttling for realizing high pressure gas and stabilization are formed.About liquid
The research of road restricting orifice is few, and each model uses standard one-hole AND DEWATERING FOR ORIFICE STRUCTURE mostly, and according to specific installation form, design is closed
Suitable excircle dimension, hole plate thickness, according to Restriction Parameters, the throttle orifice aperture of reasonable design and draw ratio, when necessary in orifice plate
Outer rim Integrated design threaded installation structure.Shanghai Institute of Space Propulsion is directed to certain thrustor module unit, carries out
Restricting orifice installs the research of geometric tolerance, has obtained under specific structure, the ginsengs such as the orifice plate both ends of the surface depth of parallelism, installation gap size
Several influences to the stability that throttles.Shanghai Institute of Space Propulsion is traction with certain model production demand, has carried out section
The analysis and experiment of discharge orifice flow resistance influence factor, as a result show throttle diameter and its tolerance be influence flow resistance variation it is main because
Element, and when throttle diameter gradually increases, influence of the hole tolerance to flow resistance is smaller and smaller, receiving the tolerance of tight throttle diameter can carry
The consistency of high throttle flow resistance.
As spacecraft increasingly develops to miniaturization, high-precision, modularization, type spectrum direction, traditional low thrust liquid
Attitude control engine unit fluid path restricting orifice scheme faces lot of challenges, for example, conventional throttle orifice plate, for the suitable of tiny flow quantity
Answering property is poor, and throttling capacity is insufficient, and after orifice plate microminaturization, the craftsmanship of debugging operations is poor, and the performance to throttle is unstable；It passes
System restricting orifice cannot achieve depth throttling, seriously constrain generalization of the engine pack between different model；Tradition section
Discharge orifice plate is influenced by its disc shape, and after being typically mounted at valve, the effect of reduction water attack is not had in high-pressure system,
If before being mounted on valve, special mechanical interface is needed, it is complicated.There is an urgent need to develop novel throttling devices, meet
The demand of spacecraft space push technological development.
Invention content
The purpose of the present invention is to provide a kind of flow resistance regulating devices of low thrust liquid attitude control engine unit, have deep
The ability of throttling is spent, and has the characteristics that good rectification effect, compact-sized, inhibition water attack, good manufacturability.
To solve the above problems, the technical solution adopted in the present invention is as follows：
A kind of flow resistance regulating device of low thrust liquid attitude control engine unit, including thrust chamber shell conduit, zigzag ring
Shape restricting orifice and solenoid valve are provided with propellant inlet hole and outlet opening on the thrust chamber shell conduit, and are arranged useful
The annular liquid collecting cavity before the thrust chamber valve of installation zigzag ring-type restricting orifice, before the valve annular liquid collecting cavity be in solenoid valve into
Before mouthful, restricting orifice after alternative installation valve after the solenoid valve.
The propellant inlet hole is an elongated hole, and one end connects propellant feed system, before one end and thrust chamber valve
Annular liquid collecting cavity is connected to, and annular liquid collecting cavity is an annular channel before thrust chamber valve, for installing zigzag ring-type restricting orifice,
Propellant outlet opening is that two apertures are formed by connecting, and two axially bored lines are at an angle of 90 degrees.
The thrust chamber shell conduit includes the valve mounting groove of a step pore structure.
Outer positioning ring, interior locating ring, taper segmentation ring and throttling pore are provided on the zigzag ring-type restricting orifice,
The zigzag ring-type restricting orifice is mounted on before the valve of thrust chamber shell conduit in annular liquid collecting cavity, before valve at annular liquid collecting cavity
Before solenoid valve import, the outer positioning ring is a thin wall cylindrical structure, the thin wall cylindrical structure of the outer positioning ring
The outside wall surface clearance fit of outside wall surface and annular liquid collecting cavity before thrust chamber valve, one of the thin wall cylindrical structure of the outer positioning ring
End face links into an integrated entity with taper segmentation ring, and the other end is bonded with the inlet face of solenoid valve, and the interior locating ring is also one thin
Wall cylindrical structure, annular liquid collecting cavity internal face gap before the internal face and thrust chamber valve of the thin wall cylindrical structure of the interior locating ring
Cooperation, an end face of the thin wall cylindrical structure of the interior locating ring divide ring with taper and link into an integrated entity, the other end and with push away
The blind end fitting of annular liquid collecting cavity before the valve of power room.
Further, in above-mentioned flow resistance regulating device, the aperture of the propellant inlet hole is 0.15~0.5mm.
Further, in above-mentioned flow resistance regulating device, the internal diameter size of the annular channel is 6~10mm, outer diameter ruler
Very little is 9~15mm.
Further, in above-mentioned flow resistance regulating device, the outer positioning ring of the zigzag ring-type restricting orifice and interior positioning
Ring plays fixation and the position-limiting action of axially and radially two dimensions of zigzag ring-type restricting orifice jointly.
Further, in above-mentioned flow resistance regulating device, the taper divides ring by annular liquid collecting before the thrust chamber valve
Chamber is divided into two.
Further, in above-mentioned flow resistance regulating device, the throttling pore is distributed on the conical surface of taper segmentation ring.
Further, in above-mentioned flow resistance regulating device, the thickness of the taper segmentation ring is throttling pore maximum diameter of hole
3 times or more, cone angle is chosen between 20 degree to 160 degree.
Further, in above-mentioned flow resistance regulating device, the throttling pore includes single hole, porous or combination hole arrangement.
Further, in above-mentioned flow resistance regulating device, the layout of the throttling pore takes multiple aperture, Duo Zhongbu
Office, multiple numbers scheme.
Further, in above-mentioned flow resistance regulating device, after the zigzag ring-type restricting orifice and the traditional valve of solenoid valve
Restricting orifice is applied in combination.
Further, in above-mentioned flow resistance regulating device, after the traditional valve of the size ratio of the zigzag ring-type restricting orifice
Restricting orifice is 4~5 times big.
Compared with prior art, the present invention has the ability of depth throttling, and, suppression good, compact-sized with rectification effect
The characteristics of water attack processed, good manufacturability.The present invention increases orifice design and cloth due to devising zigzag ring-type restricting orifice
The degree of freedom of office is conducive to the stability for improving throttling capacity and throttling, zigzag ring-type restricting orifice and annular before thrust chamber valve
Liquid collecting cavity is used cooperatively, and easily and reliably realizes the scheme that throttles before valve, is conducive to the water attack effect for inhibiting high-pressure system, it is ensured that
Engine mildness is reliable.Restricting orifice is used cooperatively after the zigzag ring-type restricting orifice valve traditional with solenoid valve, Ke Yishi
The depth throttling of existing thrustor, improves the generalization degree of engine, it is also possible to realize that micro thrust starts
Effective throttling of machine tiny flow quantity.The size ratio tradition orifice plate of zigzag ring-type restricting orifice is 4~5 times big, and does not need screw thread company
It connects and special fixing device, the good manufacturability of orifice plate installation and debugging.
Description of the drawings
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon：
Fig. 1 is the installation diagram of the flow resistance regulating device of the low thrust liquid attitude control engine unit of one embodiment of the invention；
Fig. 2 is the thrust chamber shell of the flow resistance regulating device of the low thrust liquid attitude control engine unit of one embodiment of the invention
Body channel structure figure；
Fig. 3 is the sectional view of the zigzag ring-type throttle orifice harden structure of one embodiment of the invention；
Fig. 4 is the vertical view of the zigzag ring-type throttle orifice harden structure of one embodiment of the invention.
Specific implementation mode
With reference to specific embodiment, the present invention is described in detail.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection domain.
As shown in Figure 1, the present invention provides a kind of flow resistance regulating device of low thrust liquid attitude control engine unit, including push away
Power room housing conduit 1, zigzag ring-type restricting orifice 2 and solenoid valve 3, wherein
Shown in Fig. 2, annular liquid collecting cavity 5, valve before propellant inlet hole 4, thrust chamber valve are provided on thrust chamber shell conduit 1
Door mounting groove 6 and propellant outlet 7.Propellant inlet hole 4 is an elongated hole, and one end connects propellant feed system, one end
It is connected to annular liquid collecting cavity 5 before thrust chamber valve.Annular liquid collecting cavity 5 is an annular channel before thrust chamber valve, for installing zigzag
Cyclic annular restricting orifice 2.Valve mounting groove 6 is a step pore structure, and propellant outlet opening 7 is that two apertures are formed by connecting, two
Axially bored line is at an angle of 90 degrees.Here, propellant inlet hole, annular liquid collecting cavity, outlet opening, valve mounting groove Integrated design are in thrust chamber
It is compact in design, simple in structure on shell.
Shown in Fig. 3, Fig. 4, outer positioning ring 8, interior locating ring 9, taper segmentation ring are provided on zigzag ring-type restricting orifice 2
10 and throttling pore 11.Zigzag ring-type restricting orifice 2 is mounted on before the valve of thrust chamber shell conduit 1 in annular liquid collecting cavity 5, valve
Preceding annular liquid collecting cavity 5 is in before 3 import of solenoid valve.Outer positioning ring 8 is a thin wall cylindrical structure, the thin-walled of outer positioning ring 8
The outside wall surface clearance fit of annular liquid collecting cavity 5 before the outside wall surface and thrust chamber valve of cylindrical structure.The thin wall cylindrical knot of outer positioning ring 8
One end face of structure links into an integrated entity with taper segmentation ring 10, and the other end is bonded with the inlet face of solenoid valve 3.Interior locating ring 9
It is a thin wall cylindrical structure, 5 inner wall of annular liquid collecting cavity before the internal face and thrust chamber valve of the thin wall cylindrical structure of interior locating ring 9
Face clearance fit.One end face of the thin wall cylindrical structure of interior locating ring 9 and taper segmentation ring 10 link into an integrated entity, the other end and
It is bonded with the blind end of annular liquid collecting cavity 5 before thrust chamber valve.Here, the annular liquid collecting cavity needed for the installation of zigzag ring-shaped orifice plate is set
It sets before valve, is not belonging to the drip volume of thrust chamber, because of the response time without influencing engine.Zigzag ring-shaped orifice plate is installed
Before valve, thus valve inlet pressure minimizes, and advantageously reduces the influence of water attack.
In one preferred embodiment of the flow resistance regulating device of the low thrust liquid attitude control engine unit of the present invention, promote
The aperture of agent inlet hole 4 is 0.15~0.5mm.The internal diameter size of annular channel is 6~10mm, and outer diameter is 9~15mm, is protected
Liquid collecting cavity open end face valve inlet face is demonstrate,proved, liquid collecting cavity depth is determined by the axial length of zigzag ring-type restricting orifice, simultaneously
Take into account the feasibility of propellant import layout.
The outer positioning ring 8 and interior locating ring 9 of zigzag ring-type restricting orifice 2 play zigzag ring-type restricting orifice 2 jointly
The axially and radially fixation of two dimensions and position-limiting action.
Taper divides ring 10 and annular liquid collecting cavity 5 before thrust chamber valve is divided into two.
Throttling pore 11 is distributed on the conical surface of taper segmentation ring 10.
The thickness that taper divides ring 10 calculates acquisition according to design, and principle is to ensure that its thickness is 11 largest hole of throttling pore
3 times or more of diameter, cone angle can be generally chosen between 20 degree to 160 degree, be determined by concrete structure.
Throttling pore 11 includes single hole, porous or combination hole arrangement.
According to the demand of Restriction Parameters, throttling pore 11 can be single hole or the porous knot arranged by certain regularity of distribution
Structure can be a kind of aperture or multiple aperture combination distributed architecture.Here, throttle orifice arrangement range is big, allow to take a variety of
Aperture, a variety of layouts, the scheme of multiple numbers greatly expand the effect that orifice throttle, current stabilization, flow equalization distribute.
The size ratio tradition orifice plate of zigzag ring-type restricting orifice is 4~5 times big.
Zigzag ring-type restricting orifice is closed with throttle orifice board group after the traditional valve of solenoid valve and is used, and realizes that vacuum thrust is less than
The depth section of thrustor tiny flow quantity propellant is realized in effective throttling of thrustor tiny flow quantity equal to 5N
Stream ability.Here, if the thrust engine with tiny vacuum thrust that engine is flow very little is less than or equal to 5N or low thrust
Engine need to adapt to different model inlet pressure demand, directly borrow existing product.When need to carry out depth throttling, zigzag is cyclic annular
Orifice plate can be used cooperatively with restricting orifice after traditional valve, realize the work(of tiny flow quantity effectively throttling and the throttling of small flux deepness
Energy.
Each embodiment is described by the way of progressive in this specification, the highlights of each of the examples are with other
The difference of embodiment, identical similar portion just to refer each other the above specific implementation to the present invention between each embodiment
Example is described.It is to be appreciated that the present invention is not limited to the above specific embodiments, those skilled in the art can be with
It makes a variety of changes or changes within the scope of the claims, this is not affected the essence of the present invention.In the feelings not conflicted
Under condition, the feature in embodiments herein and embodiment can be arbitrarily combined with each other.
Claims (9)
1. a kind of flow resistance regulating device of low thrust liquid attitude control engine unit, which is characterized in that including thrust chamber enclosure slot
Road, zigzag ring-type restricting orifice and solenoid valve are provided with propellant inlet hole and outlet opening on the thrust chamber shell conduit,
And it is provided with annular liquid collecting cavity before the thrust chamber valve for installing zigzag ring-type restricting orifice, before the valve at annular liquid collecting cavity
Before the solenoid valve import, restricting orifice after installation valve after the solenoid valve.
2. the flow resistance regulating device of low thrust liquid attitude control engine unit described in claim 1, which is characterized in that described to push away
It is an elongated hole into agent inlet hole, one end connects propellant feed system, and one end is connected to annular liquid collecting cavity before thrust chamber valve,
Annular liquid collecting cavity is an annular channel before thrust chamber valve, and for installing zigzag ring-type restricting orifice, propellant outlet opening is two
A aperture is formed by connecting, and two axially bored lines are at an angle of 90 degrees.
3. the flow resistance regulating device of the low thrust liquid attitude control engine unit described in claim 2, which is characterized in that the Z
It is cyclic annular that outer positioning ring, interior locating ring, taper segmentation ring and throttling pore, the zigzag are provided on font ring-type restricting orifice
For restricting orifice before the valve of thrust chamber shell conduit in annular liquid collecting cavity, the outer positioning ring is a thin wall cylindrical knot
Structure, the outside wall surface clearance fit of annular liquid collecting cavity before the outside wall surface and thrust chamber valve of the thin wall cylindrical structure of the outer positioning ring,
One end face of the thin wall cylindrical structure of the outer positioning ring and taper segmentation ring link into an integrated entity, the other end and solenoid valve into
Mouth face paste is closed, and the interior locating ring is also a thin wall cylindrical structure, the internal face of the thin wall cylindrical structure of the interior locating ring
With annular liquid collecting cavity internal face clearance fit before thrust chamber valve, an end face and the cone of the thin wall cylindrical structure of the interior locating ring
Shape segmentation ring links into an integrated entity, the other end and be bonded with the blind end of annular liquid collecting cavity before thrust chamber valve, the outer positioning ring with
Interior locating ring realizes that the fixation of axially and radially two dimensions of zigzag ring-type restricting orifice and position-limiting action, the throttling are small
Pore size distribution is on the conical surface that taper divides ring.
4. the flow resistance regulating device of low thrust liquid attitude control engine unit according to claim 1, which is characterized in that institute
The internal diameter size for stating annular channel is 6~10mm, and outer diameter is 9~15mm.
5. the flow resistance regulating device of low thrust liquid attitude control engine unit according to claim 3, which is characterized in that institute
It states taper segmentation ring annular liquid collecting cavity before the thrust chamber valve is divided into two.
6. the flow resistance regulating device of low thrust liquid attitude control engine unit according to claim 3, which is characterized in that institute
The thickness for stating taper segmentation ring is 3 times or more of throttling pore maximum diameter of hole, and cone angle is chosen between 20 degree to 160 degree.
7. the flow resistance regulating device of low thrust liquid attitude control engine unit according to claim 3, which is characterized in that institute
State throttling pore include single hole, it is porous or combination hole arrangement.
8. the flow resistance regulating device of low thrust liquid attitude control engine unit according to claim 1, which is characterized in that institute
The layout for stating throttling pore takes multiple aperture, a variety of layouts and multiple numbers.
9. the flow resistance regulating device of low thrust liquid attitude control engine unit according to claim 1, which is characterized in that institute
The size for stating zigzag ring-type restricting orifice is 4~5 times big compared with restricting orifice after solenoid valve valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611031030.4A CN106640423B (en) | 2016-11-16 | 2016-11-16 | The flow resistance regulating device of low thrust liquid attitude control engine unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611031030.4A CN106640423B (en) | 2016-11-16 | 2016-11-16 | The flow resistance regulating device of low thrust liquid attitude control engine unit |
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| Publication Number | Publication Date |
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| CN106640423A CN106640423A (en) | 2017-05-10 |
| CN106640423B true CN106640423B (en) | 2018-08-03 |
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| CN201611031030.4A Active CN106640423B (en) | 2016-11-16 | 2016-11-16 | The flow resistance regulating device of low thrust liquid attitude control engine unit |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108661806B (en) * | 2018-03-19 | 2019-09-17 | 上海空间推进研究所 | A kind of flow resistance regulating device |
| CN112683356A (en) * | 2021-01-21 | 2021-04-20 | 上海凯泉泵业（集团）有限公司 | Annular throttling device |
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| US4353389A (en) * | 1979-10-31 | 1982-10-12 | Messerschmitt-Bolkow-Blohm G.M.B.H. | Hot gas valve |
| US4727902A (en) * | 1985-08-31 | 1988-03-01 | Rheinmetall Gmbh | Valve arrangement |
| CN104405533A (en) * | 2014-10-28 | 2015-03-11 | 上海空间推进研究所 | Sealing structure of small light type liquid rocket attitude control engine |
| CN104401495A (en) * | 2014-10-28 | 2015-03-11 | 上海空间推进研究所 | Plunger joint throttler and use method thereof |
| CN105386894A (en) * | 2015-12-10 | 2016-03-09 | 西安航天动力研究所 | High-pressure large-transformation-ratio flow regulating valve |
| CN106014688A (en) * | 2016-05-10 | 2016-10-12 | 北京控制工程研究所 | Flow control device and method |
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2016
- 2016-11-16 CN CN201611031030.4A patent/CN106640423B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4353389A (en) * | 1979-10-31 | 1982-10-12 | Messerschmitt-Bolkow-Blohm G.M.B.H. | Hot gas valve |
| US4727902A (en) * | 1985-08-31 | 1988-03-01 | Rheinmetall Gmbh | Valve arrangement |
| CN104405533A (en) * | 2014-10-28 | 2015-03-11 | 上海空间推进研究所 | Sealing structure of small light type liquid rocket attitude control engine |
| CN104401495A (en) * | 2014-10-28 | 2015-03-11 | 上海空间推进研究所 | Plunger joint throttler and use method thereof |
| CN105386894A (en) * | 2015-12-10 | 2016-03-09 | 西安航天动力研究所 | High-pressure large-transformation-ratio flow regulating valve |
| CN106014688A (en) * | 2016-05-10 | 2016-10-12 | 北京控制工程研究所 | Flow control device and method |
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| CN106640423A (en) | 2017-05-10 |
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