CN110500200A - A kind of micrometeor green high-capacity single group member thruster structure - Google Patents
A kind of micrometeor green high-capacity single group member thruster structure Download PDFInfo
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- CN110500200A CN110500200A CN201910452238.0A CN201910452238A CN110500200A CN 110500200 A CN110500200 A CN 110500200A CN 201910452238 A CN201910452238 A CN 201910452238A CN 110500200 A CN110500200 A CN 110500200A
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- Prior art keywords
- capillary
- micrometeor
- thruster
- group member
- heat
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- 239000003380 propellant Substances 0.000 claims abstract description 37
- 230000003197 catalytic effect Effects 0.000 claims abstract description 21
- 230000005514 two-phase flow Effects 0.000 claims abstract description 13
- 238000002485 combustion reaction Methods 0.000 claims abstract description 10
- 239000007921 spray Substances 0.000 claims abstract description 10
- 238000003421 catalytic decomposition reaction Methods 0.000 claims abstract description 5
- 239000000945 filler Substances 0.000 claims description 52
- 238000003466 welding Methods 0.000 claims description 15
- 239000000919 ceramic Substances 0.000 claims description 13
- 239000000463 material Substances 0.000 claims description 12
- 229910052751 metal Inorganic materials 0.000 claims description 12
- 239000002184 metal Substances 0.000 claims description 12
- 230000004888 barrier function Effects 0.000 claims description 7
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 6
- 229910052802 copper Inorganic materials 0.000 claims description 6
- 239000010949 copper Substances 0.000 claims description 6
- 210000005239 tubule Anatomy 0.000 claims description 6
- 229910052782 aluminium Inorganic materials 0.000 claims description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 4
- 239000003795 chemical substances by application Substances 0.000 claims description 4
- 238000009434 installation Methods 0.000 claims description 4
- 238000009825 accumulation Methods 0.000 claims description 3
- 230000000903 blocking effect Effects 0.000 claims description 3
- 230000001105 regulatory effect Effects 0.000 claims description 2
- 238000006555 catalytic reaction Methods 0.000 claims 1
- 230000000694 effects Effects 0.000 claims 1
- 239000007787 solid Substances 0.000 claims 1
- 239000003054 catalyst Substances 0.000 abstract description 5
- 231100000614 poison Toxicity 0.000 abstract description 2
- 230000007096 poisonous effect Effects 0.000 abstract description 2
- 238000010894 electron beam technology Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 3
- 239000002905 metal composite material Substances 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- OAKJQQAXSVQMHS-UHFFFAOYSA-N Hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 description 2
- 230000033228 biological regulation Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000004411 aluminium Substances 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 230000005764 inhibitory process Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 229910052573 porcelain Inorganic materials 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
-
- 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
-
- 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
-
- 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
-
- 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
Abstract
The present invention relates to a kind of micrometeor green high-capacity single group member thruster structure, propellant under catalyst action, realizes catalytic decomposition in catalytic bed, further sprays after burning through jet pipe generate thrust in a combustion chamber；Thermal control component is mounted in thrust chamber catalytic bed, is carried out temperature to catalytic bed and is controled and monitored.The invention proposes a kind of micrometeor green high-capacity single group member thruster structures, regulate and control capillary temperature by thermally conductive sheet, capillary heat conductive filament etc., inhibit propellant under micrometeor to generate two phase flow in capillary, realizes micrometeor green high-capacity single group member thruster steady operation.Propellant under micrometeor is inhibited to generate two phase flow in capillary, to realize micrometeor green high-capacity single group member thruster steady operation.Micrometeor green high-capacity single group member thruster have the characteristics that high specific impulse, green non-poisonous, light weight, can be pre-packaged, provide required power or torque for micro-nano satellite orbit maneuver, quick response etc., greatly expand the application space of micro-nano satellite.
Description
Technical field
The present invention relates to a kind of micrometeor green high-capacity single group member thruster structures, belong to Push Technology field.
Background technique
With the development of green high-capacity monopropellant propulsion technology, such as ADN Push Technology, thruster performance is greatly mentioned
Rise, but simultaneously because thrust room temperature raising so that thermal environment locating for thruster is more severe, to the design band of thruster
Carry out great challenge, at the same time, for low thrust single group member thruster, thruster working flow is small, so that thruster is to thrust
The raising of room temperature is more sensitive, will lead to propellant in thruster ejector filler capillary and generates two phase flow, forms gas and block up, cause
Thrust is unstable, is unable to satisfy requirement.
Summary of the invention
Present invention solves the technical problem that are as follows: overcome the deficiencies of the prior art and provide a kind of micrometeor green high-capacity list
Constituent element thruster structure reduces conduction of the thrust chamber heat to capillary, by leading by ceramics and metal composite structure cup
Backing, capillary heat conductive filament etc. increase thrust chamber, capillary and extraneous passage of heat, reduce capillary in the thruster course of work
The temperature of pipe inhibits propellant under micrometeor to generate two phase flow in capillary, to realize micrometeor green high-capacity single group member
Thruster working thrust is stablized.
A kind of technical solution that the present invention solves are as follows: micrometeor green high-capacity single group member thruster structure, comprising: micro electric
Magnet valve (1), ejector filler (2), thrust chamber (3) and thermal control component (4)；The outlet of miniature electromagnetic valve (1) and ejector filler (2) entrance connect
It connects, miniature electromagnetic valve (1) is used for the circulation to propellant and carries out on-off control；Ejector filler (2) outlet connects with thrust chamber (3) entrance
Connect, ejector filler (2) realize propellant conveying and obstruct thrust chamber (3) conduction from heat to miniature electromagnetic valve (1) direction simultaneously
The heat of thrust chamber (3) can be conducted to outside；Thrust chamber (3) is by catalytic bed (31), combustion chamber (32) and jet pipe (33) group
At propellant realizes catalytic decomposition under the catalyst action in catalytic bed (31), after further burning in combustion chamber (32)
It is sprayed through jet pipe (33) and generates thrust；Thermal control component (4) is mounted on thrust chamber (3) catalytic bed (31) outer wall, to catalytic bed
(31) temperature is carried out to control and monitor.
Miniature electromagnetic valve (1), including an entrance, make-and-break control switch and one outlet, the propellant warp that entrance is passed through
After crossing make-and-break control switch control circulation and blocking, flowed out from outlet.
Ejector filler (2) is by flange frame (21), capillary (22), thermally conductive sheet (23), cup (24) and capillary heat conductive filament
(25) it forms, miniature electromagnetic valve (1) is mounted on flange frame (21), and cup (24) is for connecting thrust chamber (3), capillary
(22) both ends are respectively welded on flange frame (21) and cup (24), and cup (24) is welded on flange frame (21), thermally conductive
Piece (23) one end is mounted on cup (24), and the connection of thermally conductive sheet (23) other end is external (to specifically refer to external satellite support
Plate), capillary heat conductive filament (25) one end is mounted on capillary (22) close to cup (24) side, and capillary heat conductive filament (25) is another
One end connection is external (specifically referring to external satellite support plate).
When thruster works, thrust chamber (3) generates high temperature, and high temperature conducts to ejector filler (2) direction, passes through thermally conductive sheet (23)
And capillary heat conductive filament (25), heat outside heat derives thruster, will be reduced to the conduction of capillary (22) and in capillary
(22) accumulation on；The other end connection of the outlet of one end connection miniature electromagnetic valve (1) of capillary (22), capillary (22) pushes away
Power room (3) entrance, propellant enters from one end of capillary (22), after flowing through capillary (22), from the another of capillary (22)
End sprays into thrust chamber (3), regulates and controls capillary (22) temperature by thermally conductive sheet (23), capillary heat conductive filament (25) etc., inhibits miniflow
It measures lower propellant and generates two phase flow in capillary (22).
Thermally conductive sheet (23) is made of jointing and thermal conductive belt, is that copper material or silver-colored material, jointing are welded on cup
(24) on, position is the outside of capillary (22) and cup (24) welding position, and thermal conductive belt one end is fixed on jointing, separately
One end is fixed in the support plate of satellite by tabletting, increases a cup (24) and external passage of heat, by thrust chamber (3)
Heat is conducted to outside, reduces conduction of thrust chamber (3) heat to capillary (22).
Capillary heat conductive filament (25) is that copper material or silver-colored material, one end are welded on capillary (22), is located proximate to capillary
Manage (22) and cup (24) welding position, the other end is fixed in the support plate of satellite by tabletting, formed capillary (22) and
External passage of heat reduces temperature at capillary (22).
Flange frame (21) is divided into two parts of flange and frame, and flange is L-type structure, is ejector filler (2) and micro electric
The connecting portion and thruster and external connection mounting surface of magnet valve (1), miniature electromagnetic valve (1) are connected by screw in ejector filler
(2) on flange, and pass through aluminum gasket seal；Frame is hollow cylinder lateral opening hole type structure, realizes barrier thrust chamber (3)
Conduction of the heat to miniature electromagnetic valve (1) direction.
Thruster is connect with external connection using screw, thruster and the thermally conductive installation of external satellite, by ejector filler (2) heat
Conduction to outside, reduce in the thruster course of work and thruster shutdown after ejector filler (2), miniature electromagnetic valve (1) temperature.
Cup (24) includes ceramic connecting piece and metal connecting piece, and ceramic connecting piece and metal connecting piece are welded to connect, pottery
Porcelain connector is the stepped shaft structure with center speaker hole, and the one end of capillary (22) is welded in the speaker hole of center, and multi-diameter shaft is thin
The jointing that thermally conductive sheet (23) are welded in outside wall surface is held, the inner wall of welding metal connector in multi-diameter shaft butt end outside wall surface,
Metal connecting piece both ends of the surface, the frame of one end welded flange frame (21), the other end weld thrust chamber (3).
Capillary (22) is the flow pressure drop control unit of ejector filler (2), and ejector filler (2) is single capillary (22) spray
Structure.
The advantages of the present invention over the prior art are that:
(1) the invention proposes a kind of micrometeor green high-capacity single group member thruster structure, by thermally conductive sheet on ejector filler,
Capillary heat conductive filament etc. increases ejector filler, capillary and extraneous passage of heat, reduces capillary in the thruster course of work
Temperature.
(2) present invention increases heat transfer resistance of the thrust chamber to capillary by ceramics and metal composite structure cup scheme,
Thrust chamber is reduced to conduct to the heat of capillary.
(3) present invention realizes barrier thrust chamber heat and conducts heat to thruster installation by flange frame structure
Conduction of the heat to miniature electromagnetic valve direction is weakened in face.
(4) present invention inhibits propellant under micrometeor to generate two phase flow in capillary by regulation capillary temperature, real
Existing micrometeor green high-capacity single group member thruster steady operation.
(5) present invention realizes that mounting structure is compact by L-type ejector filler flange and external connection, is suitable for being applied to vertical
The micromass culture system of square magnitude micro-nano satellite.
Detailed description of the invention
Fig. 1 is micrometeor green high-capacity single group member thruster structural schematic diagram of the present invention；
Fig. 2 is ejector filler structural schematic diagram；
Fig. 3 is flange circuit theory schematic diagram；
Fig. 4 is cup structural schematic diagram；
Fig. 5 is thrust chamber structural schematic diagram.
Specific embodiment
The present invention relates to a kind of micrometeor green high-capacity single group member thruster structures, including miniature electromagnetic valve (1), ejector filler
(2), thrust chamber (3) and thermal control component (4)；Miniature electromagnetic valve (1) outlet is connect with ejector filler (2) entrance, for propellant
Circulation carry out on-off management；Ejector filler (2) outlet is connect with thrust chamber (3) entrance, by flange frame (21), capillary
(22), thermally conductive sheet (23), cup (24) and capillary heat conductive filament (25) composition, ejector filler (2) flange frame (21) realize barrier
Conduction of the heat to miniature electromagnetic valve (1) direction in thrust chamber (3) course of work, thermally conductive sheet (23) reduce thrust chamber (3) to hair
The heat transfer of tubule (22), capillary heat conductive filament (25) are mounted on capillary (22) close to thrust chamber (3) side, reduce capillary
(22) temperature, capillary (22) realize the conveying of propellant；Thrust chamber (3) is by catalytic bed (31), combustion chamber (32) and jet pipe
(33) it forms, propellant under catalyst action, is realized catalytic decomposition, further fired in combustion chamber (32) in catalytic bed (31)
It is sprayed after burning through jet pipe (33) and generates thrust；Thermal control component (4) is mounted in thrust chamber (3) catalytic bed (31), to catalytic bed
(31) temperature is carried out to control and monitor.The invention proposes a kind of micrometeor green high-capacity single group member thruster structures, by leading
Backing (23), capillary heat conductive filament (25) etc. regulate and control capillary (22) temperature, and propellant is in capillary (22) under inhibition micrometeor
Middle generation two phase flow realizes micrometeor green high-capacity single group member thruster steady operation.
A kind of micrometeor green high-capacity single group member thruster structure of the invention, inhibit micrometeor under propellant in capillary
Middle generation two phase flow, to realize micrometeor green high-capacity single group member thruster steady operation.Micrometeor green high-capacity single group member
Thruster have the characteristics that high specific impulse, green non-poisonous, light weight, can be pre-packaged, be micro-nano satellite orbit maneuver, quick response etc.
Power or torque needed for providing, greatly expand the application space of micro-nano satellite.
As shown in Figure 1, a kind of micrometeor green high-capacity single group member thruster structure, comprising: miniature electromagnetic valve (1), spray
Device (2), thrust chamber (3) and thermal control component (4).Miniature electromagnetic valve (1) carries out on-off control, packet for the circulation to propellant
Include an entrance, make-and-break control switch and one outlet, the propellant that entrance is passed through by make-and-break control switch control circulation and
It after blocking, is flowed out from outlet, the outlet of miniature electromagnetic valve (1) is connect with ejector filler (2) entrance screw, aluminium backing sealing.
As shown in Fig. 2, ejector filler (2) is by flange frame (21), capillary (22), thermally conductive sheet (23), cup (24) and hair
Tubule heat conductive filament (25) composition, ejector filler (2) outlet are connect with thrust chamber (3) entrance electron beam welding, and ejector filler (2), which is realized, to be promoted
The conveying of agent and the heat of thrust chamber (3) is obstructed to the conduction in miniature electromagnetic valve (1) direction and can be by the heat of thrust chamber (3)
It conducts to outside.
Flange frame (21), as shown in figure 3, being divided into two parts of flange and frame, flange is L-type structure, is ejector filler
(2) with the connecting portion of miniature electromagnetic valve (1) and thruster and external connection mounting surface, the outlet of miniature electromagnetic valve (1) passes through
Screw is connected on ejector filler (2) flange, and by aluminum gasket seal, thruster is connect using screw with external connection, pushed away
Power device and the thermally conductive installation of external satellite conduct ejector filler (2) heat to outside, reduce in the thruster course of work and thruster
Ejector filler (2), miniature electromagnetic valve (1) temperature after shutdown.Frame is hollow cylinder lateral opening hole type structure, realizes barrier thrust
Conduction of the heat of room (3) to miniature electromagnetic valve (1) direction.
Cup (24), as shown in figure 4, for ejector filler (2) electron beam welding connection thrust chamber (3), including ceramic connecting piece
And metal connecting piece, on the outside, for ceramic connecting piece in inside, ceramic connecting piece is the ladder with center speaker hole to metal connecting piece
Axle construction, the inner wall of welding metal connector, metal connecting piece both ends of the surface, one end welded flange in multi-diameter shaft butt end outside wall surface
The frame of frame (21), other end electron beam welding thrust chamber (3) weld capillary (22) in the speaker hole of ceramic connecting piece center
One end, capillary (22) be ejector filler (2) flow pressure drop control unit, ejector filler (2) be single capillary (22) spray
Structure, capillary (22) other end are welded on flange frame (21), are welded and are led in ceramic connecting piece multi-diameter shaft taper end outside wall surface
The jointing of backing (23), thermally conductive sheet (23) are made of jointing and thermal conductive belt, are copper material or silver-colored material, jointing
It is welded on cup (24), position is the outside of capillary (22) and cup (24) welding position, and thermal conductive belt one end is fixed on company
On connector, the other end is fixed in the support plate of satellite by tabletting, increases a cup (24) and external passage of heat,
Thrust chamber (3) heat is conducted to outside, conduction of thrust chamber (3) heat to capillary (22) is reduced.
Capillary heat conductive filament (25) are welded on capillary (22), capillary heat conductive filament (25) is copper material or silver-colored material, one
End is welded on capillary (22), is located proximate to capillary (22) and cup (24) welding position, the other end is fixed by tabletting
In the support plate of satellite, capillary (22) and external passage of heat are formed, reduce temperature at capillary (22).
Thrust chamber (3) electron beam welding is connected on ejector filler (2) cup (24), as shown in figure 5, by catalytic bed (31), burning
Room (32) and jet pipe (33) composition, combustion chamber (32) and jet pipe (33) be structure as a whole, catalytic bed (31) and combustion chamber (32) and
Jet pipe (33) electron beam welding, in catalytic bed (31) after loading catalyst with ejector filler (2) cup (24) electron beam welding.It promotes
Agent realizes catalytic decomposition under the catalyst action in catalytic bed (31), through jet pipe after further burning in combustion chamber (32)
(33) it sprays and generates thrust.
Thermal control component (4) is mounted on thrust chamber (3) catalytic bed (31) outer wall, to catalytic bed (31) carry out temperature control and
Monitoring.
When thruster works, thrust chamber (3) generates high temperature, and high temperature conducts to ejector filler (2) direction, passes through thermally conductive sheet (23)
And capillary heat conductive filament (25), heat outside heat derives thruster, will be reduced to the conduction of capillary (22) and in capillary
(22) accumulation on.The heat convection power P of propellant in capillary (22)qThe heat conducted with thrust chamber (3) to ejector filler (2)
Power Pt, thermal power P derived from thermally conductive sheet (23)d, thermal power P derived from capillary heat conductive filament (25)mIt preferably satisfies such as ShiShimonoseki
System: Pq> Pt-Pd-Pm.Wherein, Pm=fm*Cp*Tm, fm* propellant flow rate, C are indicatedpFor the specific heat capacity of propellant, TmFor capillary
The variation mean temperature difference of propellant at 3~5mm of downstream.
The other end of the outlet of one end connection miniature electromagnetic valve (1) of capillary (22), capillary (22) connects thrust chamber
(3) entrance, propellant enters from one end of capillary (22), after flowing through capillary (22), sprays from the other end of capillary (22)
Enter thrust chamber (3), capillary (22) temperature is regulated and controled by thermally conductive sheet (23), capillary heat conductive filament (25) etc., is inhibited under micrometeor
Propellant generates two phase flow in capillary (22).
The heat convection power P of propellant in capillary (22)qThe thermal power conducted with thrust chamber (3) to ejector filler (2)
Pt, thermal power P derived from thermally conductive sheet (23)d, thermal power P derived from capillary heat conductive filament (25)mThe matching for needing to have certain
Property, which is suitable for the low energy flow characteristic propellants such as hydrazine, is also applied for ADN, HAN base green high-capacity propellant.Preferred embodiment
Are as follows: when propellant is ADN base propellant, if PtFor 20W, flow fmWhen for 100mg/s, heat convection power is 14W, it is desirable that
Radiator structure heat-conducting section product >=2.5mm2, capillary inner diameter≤0.3mm, thermally conductive power Pd+Pd>=6W, ensure in small flow,
Do not occur two phase flow in capillary, to ensure TmLower than a certain range, then thermally conductive power is required further to be promoted.For heat dissipation
Structure and power determination need further to be determined by certain experiment.Micrometeor green designed by the invention is high
Energy single group member thruster structure inhibits propellant in capillary to generate two phase flow, realizes micrometeor green high-capacity single group member thrust
Device working thrust is stablized.
The invention proposes a kind of micrometeor green high-capacity single group member thruster structures, pass through thermally conductive sheet, hair on ejector filler
Tubule heat conductive filament etc. increases ejector filler, capillary and extraneous passage of heat, reduces the temperature of capillary in the thruster course of work
Degree.By ceramics and metal composite structure cup scheme, increase heat transfer resistance of the thrust chamber to capillary, reduces thrust chamber to hair
The heat of tubule conducts.By flange frame structure, realizes barrier thrust chamber heat and conducts heat to thruster mounting surface,
Weaken conduction of the heat to miniature electromagnetic valve direction.
The present invention is inhibited propellant under micrometeor to generate two phase flow in capillary, is realized by regulation capillary temperature
Micrometeor green high-capacity single group member thruster steady operation.By L-type ejector filler flange and external connection, realize that mounting structure is tight
It gathers, suitable for being applied to the micromass culture system of cube magnitude micro-nano satellite.
The content that description in the present invention is not described in detail belongs to the well-known technique of those skilled in the art.
Claims (10)
1. a kind of micrometeor green high-capacity single group member thruster structure characterized by comprising miniature electromagnetic valve (1), ejector filler
(2), thrust chamber (3) and thermal control component (4)；
The outlet of miniature electromagnetic valve (1) is connect with ejector filler (2) entrance, miniature electromagnetic valve (1) be used for the circulation of propellant into
The control of row on-off；Ejector filler (2) outlet is connect with thrust chamber (3) entrance, and ejector filler (2) realizes that the conveying of propellant and barrier push away
Conduction from the heat of power room (3) to miniature electromagnetic valve (1) direction and the heat of thrust chamber (3) can be conducted to outside；
Thrust chamber (3) is made of catalytic bed (31), combustion chamber (32) and jet pipe (33), catalysis of the propellant in catalytic bed (31)
Under agent effect, catalytic decomposition is realized, spray after further burning in combustion chamber (32) through jet pipe (33) and generate thrust；Thermal control group
Part (4) is mounted on thrust chamber (3) catalytic bed (31) outer wall, is carried out temperature to catalytic bed (31) and is controled and monitored.
2. a kind of micrometeor green high-capacity single group member thruster structure according to claim 1, which is characterized in that micro electric
Magnet valve (1), including an entrance, make-and-break control switch and one outlet, the propellant that entrance is passed through pass through make-and-break control switch
After control circulation and blocking, flowed out from outlet.
3. a kind of micrometeor green high-capacity single group member thruster structure according to claim 1, it is characterised in that: ejector filler
(2) it is made of flange frame (21), capillary (22), thermally conductive sheet (23), cup (24) and capillary heat conductive filament (25), micro electric
Magnet valve (1) is mounted on flange frame (21), and for connecting thrust chamber (3), capillary (22) both ends are respectively welded cup (24)
On flange frame (21) and cup (24), cup (24) is welded on flange frame (21), and thermally conductive sheet (23) one end is mounted on
On cup (24), the connection of thermally conductive sheet (23) other end is external (specifically referring to external satellite support plate), capillary heat conductive filament
(25) one end is mounted on capillary (22) close to cup (24) side, and the connection of capillary heat conductive filament (25) other end is external.
4. a kind of micrometeor green high-capacity single group member thruster structure according to claim 1, it is characterised in that: thruster
When work, thrust chamber (3) generates high temperature, and high temperature is conducted to ejector filler (2) direction, thermally conductive by thermally conductive sheet (23) and capillary
Silk (25) reduces conduction of the heat to capillary (22) and the accumulation on capillary (22) for outside heat derives thruster；Hair
The other end of the outlet of one end connection miniature electromagnetic valve (1) of tubule (22), capillary (22) connects thrust chamber (3) entrance, pushes away
Enter into agent from one end of capillary (22), after flowing through capillary (22), sprays into thrust chamber from the other end of capillary (22)
(3), capillary (22) temperature is regulated and controled by thermally conductive sheet (23), capillary heat conductive filament (25) etc., propellant under micrometeor is inhibited to exist
Two phase flow is generated in capillary (22).
5. a kind of micrometeor green high-capacity single group member thruster structure according to claim 1, it is characterised in that: thermally conductive sheet
(23) it is made of jointing and thermal conductive belt, is that copper material or silver-colored material, jointing are welded on cup (24), position is hair
The outside of tubule (22) and cup (24) welding position, thermal conductive belt one end are fixed on jointing, and the other end is solid by tabletting
It is scheduled in the support plate of satellite, increases a cup (24) and external passage of heat, thrust chamber (3) heat is conducted to outer
Portion reduces conduction of thrust chamber (3) heat to capillary (22).
6. a kind of micrometeor green high-capacity single group member thruster structure according to claim 1, it is characterised in that: capillary
Heat conductive filament (25) is that copper material or silver-colored material, one end are welded on capillary (22), is located proximate to capillary (22) and cup
(24) welding position, the other end are fixed in the support plate of satellite by tabletting, form capillary (22) and the thermally conductive of outside is led to
Road reduces temperature at capillary (22).
7. a kind of micrometeor green high-capacity single group member thruster structure according to claim 1, it is characterised in that: flange frame
Frame (21) is divided into two parts of flange and frame, and flange is L-type structure, is the interconnecting piece of ejector filler (2) and miniature electromagnetic valve (1)
Position and thruster and external connection mounting surface, miniature electromagnetic valve (1) is connected by screw on ejector filler (2) flange, and is passed through
Aluminum gasket seal；Frame is hollow cylinder lateral opening hole type structure, realizes the heat of barrier thrust chamber (3) to micro electromagnetic
The conduction in valve (1) direction.
8. a kind of micrometeor green high-capacity single group member thruster structure according to claim 1, it is characterised in that: thruster
It is connect with external connection using screw, thruster and the thermally conductive installation of external satellite, ejector filler (2) heat is conducted to outside, drop
In the low-thrust device course of work and thruster shutdown after ejector filler (2), miniature electromagnetic valve (1) temperature.
9. a kind of micrometeor green high-capacity single group member thruster structure according to claim 1, it is characterised in that: cup
It (24) include ceramic connecting piece and metal connecting piece, ceramic connecting piece and metal connecting piece are welded to connect, and ceramic connecting piece is band
The stepped shaft structure of center speaker hole is welded the one end of capillary (22) in the speaker hole of center, is welded in multi-diameter shaft taper end outside wall surface
The jointing of thermally conductive sheet (23) is connect, the inner wall of welding metal connector, metal connecting piece two in multi-diameter shaft butt end outside wall surface
End face, the frame of one end welded flange frame (21), the other end weld thrust chamber (3).
10. a kind of micrometeor green high-capacity single group member thruster structure according to claim 1, it is characterised in that: capillary
The flow pressure drop control unit that (22) are ejector filler (2) is managed, ejector filler (2) is single capillary (22) spray structure.
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| CN110500200B (en) | 2021-02-09 |
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