CN109139298A - A kind of space double elements precise tracking based on two-way single injector centrifugation ejector filler - Google Patents
A kind of space double elements precise tracking based on two-way single injector centrifugation ejector filler Download PDFInfo
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- CN109139298A CN109139298A CN201810924471.XA CN201810924471A CN109139298A CN 109139298 A CN109139298 A CN 109139298A CN 201810924471 A CN201810924471 A CN 201810924471A CN 109139298 A CN109139298 A CN 109139298A
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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
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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
- F02K9/52—Injectors
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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
- F02K9/58—Propellant feed valves
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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
- F02K9/60—Constructional parts; Details not otherwise provided for
-
- 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
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
-
- 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
- F02K9/97—Rocket nozzles
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
A kind of space double elements precise tracking based on two-way single injector centrifugation ejector filler, orbit maneuver suitable for aerospace craft, the mission requirements such as Orbit Transformation, including installing fishplate bar, heating device, control valve, screw, main structure, inner nozzle, outer nozzle, temperature transducer, combustion chamber and jet pipe, after control valve is opened, oxidant, two kinds of propellants of incendiary agent respectively enter the outer nozzle of centrifugal injector, high speed rotation is carried out in the vortex chamber of inner nozzle, eddy flow mist cone is formed in spout, and it is atomized and sprays according to certain mass flow proportional, two kinds of propellants are mixed and burned in the combustion chamber for being coated with fire-resistant oxidation resistant coating, ultimately form high-temperature fuel gas, it expands and accelerates in Laval nozzle, form thrust.
Description
Technical field
The present invention relates to a kind of space for being centrifuged ejector filler and molybdenum silicide composite coating thrust chamber based on two-way single injector is double
Constituent element precise tracking, the mission requirements such as orbit maneuver, Orbit Transformation suitable for aerospace craft.
Background technique
Two-way single injector centrifugal engine realizes oxygen, combustion two-way propellant using the double fuel injection nozzle of nested structure
Spray spray propellant with the rotating jet state of high speed by pressure drop potential energy and cyclonic action, inside, external force disturbs
Under movement is used, partial drop atomization, evaporation participate in hypergolic reaction.
Space precise tracking based on centrifugal single injector spray scheme has high-performance, long-life, combustion stability
The characteristics of well and starting being repeated several times, reliable power can be provided for spacecrafts such as Large-scale satellite platform, in-orbit service cabins,
It can satisfy the mission requirements such as efficient Orbit Transformation and frequent orbit maneuver, have good application potential.
But it is different from high chamber pressure engine, the operating pressure that space propulsion system is capable of providing is limited, in lower pressure
The spray effect for falling nozzle to be improved is relatively difficult.It is difficult under conditions of low pressure drop for centrifugal engine
To obtain ideal injection rate and angle, the quality of atomization is influenced.
In addition, the spray form of centrifugal injector and the design point of combustion chamber all can extremely close burning and cooling generate
Important influence, and there are serious coupled relations.If atomization, blending it is insufficient, engine performance will certainly be big
It gives a discount, if ignition temperature irrational distribution or cooling are insufficient, will lead to combustion chamber localized hyperthermia, and then influence work
Make the service life.
Summary of the invention
Technology of the invention solves the problems, such as: overcoming the deficiencies of the prior art and provide a kind of based on the centrifugation of two-way single injector
The space double elements precise tracking of ejector filler and molybdenum silicide composite coating thrust chamber.
The technical scheme is that a kind of space double elements rail control based on two-way single injector centrifugation ejector filler is started
Machine, engine include control valve, ejector filler, thrust chamber and temperature control device；Control valve is connect with ejector filler, is distinguished by control valve
Control the on-off of oxidant, incendiary agent supply；Ejector filler will be aoxidized using the structure of the coaxial embedded vortex chamber of interior outer nozzle
Agent, incendiary agent spray into the thrust chamber being attached thereto, and temperature control device provides temperature for engine and guarantees, to maintain propellant just
Normal state.
Further, the ejector filler includes installation fishplate bar, main structure, inner nozzle, outer nozzle；Fishplate bar and main body are installed
Structure connection, main structure is for providing the connecting interface of inner nozzle, outer nozzle, control valve；Inner nozzle, outer nozzle are to have
The hollow cylinder of vortex chamber, top side have a ring slot, are uniformly distributed several tangential holes in annular groove；Inner nozzle, outer spray
Mouth is shunk at a certain angle in vortex chamber bottom, is ultimately formed the spout of a cylindrical body, is connected to external environment；Inner nozzle is same
Axis is fitted into outer nozzle inner cavity and fixed, the inside and outside nozzle assembly for fluid of formation.
Further, the installation fishplate bar is the hollow plectane with mounting hole, and installation is inserted on the top of main structure
The center sky portion of fishplate bar simultaneously connects；Main structure is the cylindrical body that there are a centre bore in top, bottom end respectively, and two sides respectively have one
Cylinder table with centre bore；A positioning step is had in main structure bottom center hole and outside cylindrical body；By inner nozzle,
The inside and outside nozzle assembly for fluid that outer nozzle is constituted is packed into from main structure bottom centre hole, is pressed on the hollow positioning table of main structure
It is on rank and fixed；Main structure two sides are butted against and fixed with two control valve outlets respectively with the cylinder table of centre bore.
Further, the top insertion of main structure is installed the center sky portion of fishplate bar and is fixed by electron beam welding；It is interior
Outer nozzle sub-assembly is pressed on the hollow positioning step of main structure and is fixed by electron beam welding.
Further, the adjusting of road flow is controlled by the diameter of inner nozzle tangential hole in ejector filler, from outside flow
Adjusting is controlled by the diameter of outer nozzle tangential hole.
Further, the angle of road atomizing angle is controlled by the length of inner nozzle spout in ejector filler, from outside atomizing angle
Angle controlled by the length of outer nozzle spout.
Further, ejector filler uses all-electronin beam welding structure.
Further, thrust chamber is connect by electron beam welding with ejector filler, and temperature control device passes through laser welding and spray
Device connection.
Further, the thrust chamber includes combustion chamber, jet pipe；Combustion chamber is hollow thin-walled revolution workpiece, minor diameter
One end is straight-cylindrical equal wall thickness cylindrical body, and wall thickness meets requirement of strength design, and top has step, with main structure cylindrical body
Outer step docks slide fit, and is connected by electron beam welding, the other end reduced diameter of wall thickness cylindrical body is waited, in throat
Position diameter reaches minimum, will gradually expand increase again by the diameter of revolving body after throat, and pass through electron beam welding with jet pipe
It connects in succession；Jet pipe is Laval nozzle, is the bell revolving body of thin-walled, according to maximum thrust Profile Design, minor diameter one end and combustion
The major diameter one end for burning room is connected by electron beam welding, welding ends 1~2mm of wall thickness, as bell diameter incrementally increases, wall thickness
It is gradually reduced, in 0.4~0.6mm of thickness of the other end.
Further, the combustor surface applying coating, coating are the silication molybdenum coating of fire-resistant oxidation resistant, are used
Vacuum ion plating+silication packet infiltration method preparation.
Further, the characteristic length of the combustion chamber is greater than 900mm or more.
Further, ejector filler uses titanium alloy material, and thrust chamber substrate uses niobium tungsten alloy material.
Further, the temperature control device includes heating device, cover board, temperature transducer；Heating device, cover board are from top
Portion's centre bore is fitted into the centre bore of main structure, by concordant at the top of main structure at the top of cover board, and passes through laser welding
It is fixed；Temperature transducer is mounted on the step upper end outside main structure cylindrical body, is fixed by laser welding.
Further, the heating device is the wafer-type heater for being embedded in heater strip, in order to improve reliability, collection
At master backup heater strip.
Further, the control valve selects the suitable solenoid valve of latus rectum or latching valve product.
Compared with the prior art, the invention has the advantages that:
(1) double elements precise tracking in space proposed by the present invention uses the design structure of major diameter vortex chamber to mention
High eddy flow influences, and to reduce discharge coefficient, and increases tangential component, ensure that ejector filler may be implemented surely under low drop out condition
Fixed liquid stream spray, atomization.
(2) double elements precise tracking in space proposed by the present invention, ejector filler mainly realize throttling by tangential hole and spout,
Tissue oxygen agent, incendiary agent two-way propellant are controlled respectively with reasonable speed and angle spray by tangential hole and vent length
Out, on the one hand adjustment injection rate, the MOMENTUM DISTRIBUTION that control drop sprays realize cooling and reasonable distribution ratio of burning, separately
It on the one hand is adjustment spray angle, decision hits wall and hits the position of secondary blending after wall, and make combustion flame close to spray panel,
Reduce throat's heating power load.It can adjust by refine tangential hole method and control the hydraulic characteristic of ejector filler, make to spray
It infuses device and obtains preferable consistency and uniformity.
(3) atomization angle of double elements precise tracking in space proposed by the present invention, ejector filler can pass through vent length
It is controlled, vent length will not influence the flow drooping characteristic of ejector filler, but adjustable atomization angle.Vent length is reduced
Atomizing angle can be improved, vent length increase can reduce atomizing angle.
(4) double elements precise tracking in space proposed by the present invention, since only spray unit forms all the way, i.e., in one
The problem of nozzle and an outer nozzle are coaxial damascene structures, therefore there is no multiple spray unit combustion oscillations couplings,
With good Ignition Stability.
(5) it is long to increase combustion chamber using large-scale combustion spatial design for double elements precise tracking in space proposed by the present invention
Degree, hit wall, secondary-atomizing and diffusion blending, the another combustion gas for reserving segment space for drop have enough residence times to realize
Full combustion.
(6) double elements precise tracking in space proposed by the present invention, combustor surface applying coating, coating are anti-for high temperature resistant
The silication molybdenum coating of oxidation is prepared using vacuum ion plating+silication packet infiltration method, surface compact and highly polished, can be advantageous
In secondary-atomizing and cool down sprawling for liquid film, two kind propellant drops more preferable with the matching of the simplex fuel injecting nozzle of big flow
The effect for hitting secondary blending after wall is more ideal.The heatproof of material can be improved using silication molybdenum coating in the combustion chamber of high temperature section
Ability, the allowable work temperature than conventional coatings improve 100 DEG C or more.In addition, can using molybdenum silicide composite coating thrust chamber
To provide relatively smooth wall condition, avoids droplets from nearly wall after hitting wall and be crushed and burn, cause the localized hyperthermia of combustion chamber, and
And there is the temperature resistant capability more increased.
(7) double elements precise tracking in space proposed by the present invention, thermal controls apparatus use integrated, modularized design,
Heating device is the wafer-type heater for being embedded in heater strip, is integrated with master backup heater strip, can be engine in deep space ring
Temperature guarantee is provided under border, prevents propellant from freezing.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of space double elements precise tracking；
Fig. 2 is that two-way single injector is centrifuged ejector filler structural schematic diagram；
Fig. 3 is control valve mounting structure schematic diagram；
Fig. 4 is oxidant flow channel structural schematic diagram；
Fig. 5 is incendiary agent flow passage structure schematic diagram；
Fig. 6 is thrust chamber structural schematic diagram；
Fig. 7 is thermal controls apparatus mounting structure schematic diagram；
Specific embodiment
A specific embodiment of the invention is further described in detail with reference to the accompanying drawing.
It is pushed away as shown in Figure 1, the present invention provides one kind based on two-way single injector centrifugation ejector filler and molybdenum silicide composite coating
The space double elements precise tracking of power room includes installing fishplate bar 1, main structure 2, inner nozzle 3, outer nozzle 4, thrust chamber part
Including combustion chamber 5, jet pipe 6, heating device 7, cover board 8, temperature transducer 9, control valve 10 and screw 11；
As shown in Fig. 2, installation fishplate bar 1 is the hollow plectane with mounting hole, the top insertion installation fishplate bar of main structure 2
1 center sky portion is connected and fixed with installation fishplate bar 1 by electron beam welding；Main structure 2 is top, bottom end has one respectively
Respectively there are the cylinder table for having centre bore in the cylindrical body of centre bore, two sides；In 2 bottom center hole of main structure and outside cylindrical body
Have a positioning step；Inner nozzle 3, outer nozzle 4 are the hollow cylinder with vortex chamber, and top side is with a circle
Annular groove is uniformly distributed several tangential holes in annular groove；Inner nozzle 3, outer nozzle 4 are shunk at a certain angle in vortex chamber bottom, finally
The spout for forming a cylindrical body, is connected to external environment；There is rank in positioning outside 3 cylindrical body of inner nozzle, is filled at the top of outer nozzle 4
Enter, positioning step compresses 4 top of outer nozzle, and is fixed by electron beam welding, forms inside and outside nozzle assembly for fluid；By inner nozzle 3,
The inside and outside nozzle assembly for fluid that outer nozzle 4 is constituted is packed into from 2 bottom centre hole of main structure, is pressed on that main structure 2 is hollow to determine
On the step of position, and fixed by electron beam welding.
As shown in figure 3, main structure 2 each side stretches out the cylinder table for having centre bore, controlled respectively with two
The outlet of valve 10 processed is docked, and is tightened fixation with the installation of several screws 11, is connect control valve 10 closely with main structure 2；Oxygen
Road, combustion road control valve control the on-off of oxidant, incendiary agent supply respectively, and valve is once open, then oxidant, incendiary agent will be into
Enter ejector filler and combustion chamber, is mixed and burned, ignition operation.Wherein, left side oxygen road control valve and outer nozzle runner are connected,
Right side combustion road control valve and outer nozzle runner are connected.
As shown in figure 4, oxidant enters 2 Left-side center hole of main structure from the control valve 10 in left side, pass through outer nozzle 4
Annular groove runner, into annular groove in uniformly distributed tangential hole generate the tangential velocity of high speed, into the vortex chamber of outer nozzle 4, finally
The cylindrical spout formed from outer nozzle 4 and inner nozzle 3 sprays.
As shown in figure 5, incendiary agent enters 2 Left-side center hole of main structure from the control valve 10 on right side, pass through inner nozzle 3
Annular groove runner, into annular groove in uniformly distributed tangential hole generate the tangential velocity of high speed, into the vortex chamber of outer nozzle 3, finally
It is sprayed from the cylindrical spout of inner nozzle 3.
As shown in fig. 6, combustion chamber 5 is the revolving body with hollow cavity, the oxidant sprayed from ejector filler, incendiary agent enter
The intracavitary generation atomization of the middle control of combustion chamber, blending and burning, form high-temperature fuel gas.5 minor diameter one end of combustion chamber is hollow
The wall thickness cylindrical body such as straight tube shape, wall thickness meet requirement of strength design, and top is with outside positioning step, with 2 cylindrical body of main structure
Positioning step lower edge dock slide fit, and by electron beam welding connection.The other end reduced diameter of equal wall thickness cylindrical body,
Reach minimum in throat's position diameter, increase will be gradually expanded by the diameter of revolving body after throat again, pass through electricity with jet pipe
Beamlet is welded to connect；Jet pipe (6) is Laval nozzle, is the bell revolving body of thin-walled, according to maximum thrust Profile Design, minor diameter
One end is connect with the major diameter one end of combustion chamber (5) by electron beam welding, and welding ends wall thickness is relatively thick, it can achieve 1~
2mm, as bell diameter incrementally increases, wall thickness is gradually reduced, and can achieve 0.4~0.6mm in the thickness of the other end.
As shown in fig. 7, heating device 7, cover board 8 are from the centre bore that top center hole is fitted into main structure 2；Heating device
7 be the wafer-type heater for being embedded in heater strip, is integrated with master backup heater strip, can be provided under deep space environment for engine
Temperature guarantee, prevents propellant from freezing；It is concordant with 2 top of main structure by 8 top of cover board, and consolidated by laser welding
It is fixed, ejector filler other parts can be caused to deform to avoid welding heat；Temperature transducer 9 is mounted on 2 cylinder of main structure
External step upper end two sides, are fixed by laser welding, can be respectively as main part and backup, for detecting adding for heater
Temp effect and the fired state for monitoring engine.
The content that description in the present invention is not described in detail belongs to the well-known technique of professional and technical personnel in the field.
Claims (15)
1. a kind of space double elements precise tracking based on two-way single injector centrifugation ejector filler, it is characterised in that: engine packet
Include control valve, ejector filler, thrust chamber and temperature control device；Control valve is connect with ejector filler, controlled respectively by control valve oxidant,
The on-off of incendiary agent supply；Ejector filler is sprayed into oxidant, incendiary agent using the structure of the coaxial embedded vortex chamber of interior outer nozzle
The thrust chamber being attached thereto, temperature control device provides temperature for engine and guarantees, to maintain the normal condition of propellant.
2. engine according to claim 1, it is characterised in that: the ejector filler includes installation fishplate bar (1), main structure
(2), inner nozzle (3), outer nozzle (4)；
Installation fishplate bar (1) is connect with main structure (2), and main structure (2) is for providing inner nozzle (3), outer nozzle (4), control
The connecting interface of valve；Inner nozzle (3), outer nozzle (4) are the hollow cylinder with vortex chamber, and top side has a ring
Slot is uniformly distributed several tangential holes in annular groove；Inner nozzle (3), outer nozzle (4) are shunk at a certain angle in vortex chamber bottom, most
End form is connected at the spout of a cylindrical body with external environment；Inner nozzle (3) is coaxially fitted into outer nozzle (4) inner cavity and fixes,
Form inside and outside nozzle assembly for fluid.
3. engine according to claim 2, it is characterised in that: the installation fishplate bar (1) is in mounting hole
Empty plectane, the center sky portion of top insertion installation fishplate bar (1) of main structure (2) simultaneously connect；Main structure (2) is top, bottom
There is the cylindrical body of a centre bore at end respectively, and respectively there are the cylinder table for having centre bore in two sides；Main structure (2) bottom center
A positioning step is had in hole and outside cylindrical body；The inside and outside nozzle assembly for fluid being made of inner nozzle (3), outer nozzle (4) from
Main structure (2) bottom centre hole is packed into, and is pressed on the hollow positioning step of main structure (2) and fixed；Main structure (2)
Two sides are butted against and fixed with two control valve outlets respectively with the cylinder table of centre bore.
4. engine according to claim 3, it is characterised in that: top insertion installation fishplate bar (1) of main structure (2)
Center sky portion is simultaneously fixed by electron beam welding；Inside and outside nozzle assembly for fluid is pressed on the hollow positioning step of main structure (2)
And it is fixed by electron beam welding.
5. engine according to claim 2 or 3, it is characterised in that: the adjusting of road flow passes through inner nozzle in ejector filler
(3) diameter of tangential hole controls, and the adjusting of from outside flow controlled by the diameter of outer nozzle (4) tangential hole.
6. engine according to claim 2 or 3, it is characterised in that: the angle of road atomizing angle passes through interior spray in ejector filler
The length of mouth (3) spout controls, and the angle of from outside atomizing angle controlled by the length of outer nozzle (4) spout.
7. engine according to claim 1 or 2 or 3, it is characterised in that: ejector filler uses all-electronin beam welding structure.
8. engine according to claim 1, it is characterised in that: thrust chamber is connect by electron beam welding with ejector filler,
Temperature control device is connect by laser welding with ejector filler.
9. engine according to claim 1, it is characterised in that: the thrust chamber includes combustion chamber (5), jet pipe (6)；
Combustion chamber (5) is hollow thin-walled revolution workpiece, and minor diameter one end is straight-cylindrical equal wall thickness cylindrical body, and wall thickness meets intensity
Design requirement, top have step, slide fit are docked with the step outside main structure (2) cylindrical body, and in succession by electron beam welding
It connects, waits the other end reduced diameter of wall thickness cylindrical body, reach minimum in throat's position diameter, pass through revolving body after throat
Diameter will gradually expand increase again, connect with jet pipe by electron beam welding；Jet pipe (6) is Laval nozzle, is thin-walled clock
Shape revolving body, according to maximum thrust Profile Design, major diameter one end of minor diameter one end and combustion chamber (5) passes through electron beam welding
Connection, welding ends 1~2mm of wall thickness, as bell diameter incrementally increases, wall thickness is gradually reduced, the other end thickness 0.4~
0.6mm。
10. according to claim 1 or engine described in 9, it is characterised in that: described combustion chamber (5) surface coatings apply
Layer is the silication molybdenum coating of fire-resistant oxidation resistant, is prepared using vacuum ion plating+silication packet infiltration method.
11. according to claim 1 or engine described in 9, it is characterised in that: the characteristic length of the combustion chamber (5) is greater than
900mm or more.
12. engine according to claim 1, it is characterised in that: ejector filler uses titanium alloy material, and thrust chamber substrate is adopted
With niobium tungsten alloy material.
13. engine according to claim 3, it is characterised in that: the temperature control device includes heating device (7), lid
Plate (8), temperature transducer (9)；
Heating device (7), cover board (8) are from the centre bore that top center hole is fitted into main structure (2), by the top of cover board (8)
It is concordant at the top of main structure (2), and be fixed by laser welding；Temperature transducer (9) is mounted on main structure (2) circle
Step upper end outside cylinder, is fixed by laser welding.
14. engine according to claim 13, it is characterised in that: the heating device (7) is to be embedded in heater strip
Wafer-type heater, in order to improve reliability, integrate master backup heater strip.
15. engine described in 3 or 14 according to claim 1, it is characterised in that: the control valve (10) selects latus rectum suitable
Solenoid valve or latching valve product.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810924471.XA CN109139298B (en) | 2018-08-14 | 2018-08-14 | Space two-component rail-controlled engine based on double-path single-nozzle centrifugal injector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810924471.XA CN109139298B (en) | 2018-08-14 | 2018-08-14 | Space two-component rail-controlled engine based on double-path single-nozzle centrifugal injector |
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| CN109139298B CN109139298B (en) | 2020-04-10 |
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| CN110259604A (en) * | 2019-06-17 | 2019-09-20 | 中国人民解放军国防科技大学 | Pintle injector |
| CN110594037A (en) * | 2019-10-09 | 2019-12-20 | 湖南云顶智能科技有限公司 | Integrated injection rocket engine assembly and engine thereof |
| CN110594044A (en) * | 2019-10-17 | 2019-12-20 | 哈尔滨工程大学 | Flexible extension spray tube with self-adaptive height |
| CN112177804A (en) * | 2020-09-16 | 2021-01-05 | 上海空间推进研究所 | Low-temperature engine suitable for space device |
| CN112196700A (en) * | 2020-09-16 | 2021-01-08 | 西安航天动力研究所 | Inner bottom structure for improving gas temperature uniformity of gas generator |
| CN113006969A (en) * | 2021-04-16 | 2021-06-22 | 西安航天动力研究所 | Gas-liquid injector for depth variable thrust rocket engine |
| CN113107710A (en) * | 2021-05-10 | 2021-07-13 | 苏州旗磐科技有限公司 | Low-thrust double-component attitude control engine |
| CN113740047A (en) * | 2021-09-22 | 2021-12-03 | 西安航天动力研究所 | Universal liquid flow test device suitable for outer nozzles in central nozzle assembly |
| CN114229040A (en) * | 2021-12-17 | 2022-03-25 | 中国长城工业集团有限公司 | Separable independent propulsion cabin system |
| CN114810420A (en) * | 2022-03-31 | 2022-07-29 | 中国人民解放军战略支援部队航天工程大学 | Central gas-liquid coaxial rotational flow model injector capable of measuring gas nuclear pressure oscillation |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3942443A (en) * | 1970-07-20 | 1976-03-09 | Thiokol Corporation | Rocket assisted projectile |
| CN102052197A (en) * | 2010-11-22 | 2011-05-11 | 北京航空航天大学 | Head injector of low-thrust engine for electric discharge and ignition by utilizing nozzle clearance |
| US20110203256A1 (en) * | 2010-02-24 | 2011-08-25 | Chen Yen-Sen | Motor |
| CN106134417B (en) * | 2006-10-19 | 2012-04-04 | 上海空间推进研究所 | Low-thrust rocket |
| CN103867340A (en) * | 2012-12-12 | 2014-06-18 | 中国人民解放军国防科学技术大学 | Dual-rotational-flow inspirator |
| CN108278166A (en) * | 2017-12-20 | 2018-07-13 | 北京控制工程研究所 | A kind of step-like thrust chamber applied to double elements liquid-propellant rocket engine |
-
2018
- 2018-08-14 CN CN201810924471.XA patent/CN109139298B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3942443A (en) * | 1970-07-20 | 1976-03-09 | Thiokol Corporation | Rocket assisted projectile |
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