CN110500200B - Micro-flow green high-energy single-component thruster structure - Google Patents
Micro-flow green high-energy single-component thruster structure Download PDFInfo
- Publication number
- CN110500200B CN110500200B CN201910452238.0A CN201910452238A CN110500200B CN 110500200 B CN110500200 B CN 110500200B CN 201910452238 A CN201910452238 A CN 201910452238A CN 110500200 B CN110500200 B CN 110500200B
- Authority
- CN
- China
- Prior art keywords
- micro
- capillary
- flow
- heat
- capillary tube
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 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 12
- 238000002485 combustion reaction Methods 0.000 claims abstract description 11
- 239000007921 spray Substances 0.000 claims abstract description 8
- 239000003054 catalyst Substances 0.000 claims abstract description 6
- 230000009471 action Effects 0.000 claims abstract description 5
- 238000012544 monitoring process Methods 0.000 claims abstract description 5
- 238000003421 catalytic decomposition reaction Methods 0.000 claims abstract description 4
- 238000003466 welding Methods 0.000 claims description 20
- 239000000919 ceramic Substances 0.000 claims description 12
- 229910052751 metal Inorganic materials 0.000 claims description 12
- 239000002184 metal Substances 0.000 claims description 12
- 239000000463 material Substances 0.000 claims description 8
- 230000001276 controlling effect Effects 0.000 claims description 7
- 238000000034 method Methods 0.000 claims description 7
- 230000008569 process Effects 0.000 claims description 7
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 6
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 claims description 6
- 229910052802 copper Inorganic materials 0.000 claims description 6
- 239000010949 copper Substances 0.000 claims description 6
- 229910052709 silver Inorganic materials 0.000 claims description 6
- 239000004332 silver Substances 0.000 claims description 6
- 238000003825 pressing Methods 0.000 claims description 5
- 230000001105 regulatory effect Effects 0.000 claims description 5
- 229910052782 aluminium Inorganic materials 0.000 claims description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 4
- 238000009825 accumulation Methods 0.000 claims description 3
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- 231100000956 nontoxicity Toxicity 0.000 abstract description 2
- 230000004044 response Effects 0.000 abstract description 2
- 238000010894 electron beam technology Methods 0.000 description 6
- 238000012546 transfer Methods 0.000 description 6
- 239000002905 metal composite material Substances 0.000 description 3
- OAKJQQAXSVQMHS-UHFFFAOYSA-N Hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
Images
Classifications
-
- 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 invention relates to a micro-flow green high-energy single-component thruster structure.A propellant realizes catalytic decomposition under the action of a catalyst in a catalytic bed, and is further combusted in a combustion chamber and then is sprayed out through a spray pipe to generate thrust; the thermal control assembly is arranged on the thrust chamber catalytic bed and used for controlling and monitoring the temperature of the catalytic bed. The invention provides a micro-flow green high-energy single-component thruster structure, which regulates and controls the temperature of a capillary tube through a heat conduction sheet, a capillary tube heat conduction wire and the like, inhibits a propellant from generating two-phase flow in the capillary tube under micro-flow, and realizes the stable work of the micro-flow green high-energy single-component thruster. And the propellant is inhibited from generating two-phase flow in the capillary under micro flow, so that the stable work of the micro-flow green high-energy single-component thruster is realized. The micro-flow green high-energy single-element thruster has the characteristics of high specific impulse, greenness, no toxicity, light weight, capability of being pre-packaged and the like, provides required force or moment for micro-nano satellite orbit maneuvering, quick response and the like, and greatly expands the application space of the micro-nano satellite.
Description
Technical Field
The invention relates to a micro-flow green high-energy single-component thruster structure, and belongs to the technical field of propulsion.
Background
With the development of green high-energy single-component propulsion technology, such as ADN propulsion technology, the performance of a thruster is greatly improved, but simultaneously, due to the improvement of the temperature of a thrust chamber, the thermal environment where the thruster is located is worse, and great challenges are brought to the design of the thruster.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the micro-flow green high-energy single-component thruster structure is provided, the conduction of heat of a thrust chamber to a capillary is reduced through a front chamber with a ceramic and metal composite structure, heat conduction channels of the thrust chamber, the capillary and the outside are increased through a heat conduction sheet, a capillary heat conduction wire and the like, the temperature of the capillary in the working process of the thruster is reduced, two-phase flow of a propellant in the capillary is inhibited from being generated under micro-flow, and therefore the working thrust stability of the micro-flow green high-energy single-component thruster is achieved.
The technical scheme of the invention is as follows: a micro-flow green high-energy single-component thruster structure comprises: the device comprises a micro electromagnetic valve (1), an injector (2), a thrust chamber (3) and a thermal control assembly (4); the outlet of the micro electromagnetic valve (1) is connected with the inlet of the injector (2), and the micro electromagnetic valve (1) is used for controlling the on-off of the circulation of the propellant; the outlet of the injector (2) is connected with the inlet of the thrust chamber (3), and the injector (2) realizes the transportation of the propellant, blocks the conduction of the heat of the thrust chamber (3) to the direction of the micro solenoid valve (1) and can conduct the heat of the thrust chamber (3) to the outside; the thrust chamber (3) consists of a catalytic bed (31), a combustion chamber (32) and a spray pipe (33), the propellant realizes catalytic decomposition under the action of the catalyst in the catalytic bed (31), and is further combusted in the combustion chamber (32) and then sprayed out through the spray pipe (33) to generate thrust; the thermal control assembly (4) is arranged on the outer wall of a catalytic bed (31) of the thrust chamber (3) and used for controlling and monitoring the temperature of the catalytic bed (31).
The miniature electromagnetic valve (1) comprises an inlet, an on-off control switch and an outlet, and propellant introduced into the inlet flows out of the outlet after being controlled to circulate and be blocked by the on-off control switch.
The injector (2) is composed of a flange frame (21), a capillary tube (22), a heat conducting fin (23), a front chamber (24) and a capillary tube heat conducting wire (25), the micro electromagnetic valve (1) is installed on the flange frame (21), the front chamber (24) is used for being connected with the thrust chamber (3), two ends of the capillary tube (22) are respectively welded on the flange frame (21) and the front chamber (24), the front chamber (24) is welded on the flange frame (21), one end of the heat conducting fin (23) is installed on the front chamber (24), the other end of the heat conducting fin (23) is connected with the outside (specifically, the outside satellite supporting plate is used), one end of the capillary tube heat conducting wire (25) is installed on the side, close to the front chamber (24), of the capillary tube heat conducting wire (25) is connected with the outside.
When the thruster works, the thrust chamber (3) generates high temperature, the high temperature is conducted to the injector (2), heat is conducted out of the thruster through the heat conducting sheets (23) and the capillary heat conducting wires (25), and the conduction of the heat to the capillary (22) and the accumulation of the heat on the capillary (22) are reduced; one end of the capillary tube (22) is connected with an outlet of the miniature electromagnetic valve (1), the other end of the capillary tube (22) is connected with an inlet of the thrust chamber (3), a propellant enters from one end of the capillary tube (22), flows through the capillary tube (22), and then is sprayed into the thrust chamber (3) from the other end of the capillary tube (22), the temperature of the capillary tube (22) is regulated and controlled through the heat conducting fins (23), the capillary tube heat conducting wires (25) and the like, and the generation of two-phase flow of the propellant in the capillary tube (22) under the condition of micro-flow.
The heat conducting strip (23) is composed of a connecting joint and a heat conducting strip, the connecting joint is made of copper materials or silver materials, the connecting joint is welded on the front chamber (24), the position of the connecting joint is the outer side of the welding position of the capillary tube (22) and the front chamber (24), one end of the heat conducting strip is fixed on the connecting joint, the other end of the heat conducting strip is fixed on a supporting plate of a satellite through a pressing sheet, a heat conducting channel between the front chamber (24) and the outside is added, heat of the thrust chamber (3) is conducted to the outside, and conduction of the heat of the thrust chamber (3) to the capillary.
The capillary heat conducting wire (25) is made of copper or silver, one end of the capillary heat conducting wire is welded on the capillary (22) and is close to the welding position of the capillary (22) and the front chamber (24), the other end of the capillary heat conducting wire is fixed on a supporting plate of a satellite through a pressing sheet, a heat conducting channel between the capillary (22) and the outside is formed, and the temperature of the capillary (22) is reduced.
The flange frame (21) is divided into a flange and a frame, the flange is of an L-shaped structure and is a connecting part of the injector (2) and the micro electromagnetic valve (1) and a mounting surface for connecting the thruster and the outside, and the micro electromagnetic valve (1) is connected to the flange of the injector (2) through screws and sealed through an aluminum gasket; the frame is a hollow cylinder with a side surface opening structure, so that the heat of the thrust chamber (3) is blocked from being conducted to the direction of the miniature electromagnetic valve (1).
The thruster is connected with the outside through screws, and is installed with an external satellite in a heat conduction mode, so that heat of the injector (2) is conducted to the outside, and the temperature of the injector (2) and the temperature of the micro electromagnetic valve (1) are reduced in the working process of the thruster and after the thruster is shut down.
The antechamber (24) includes ceramic connecting piece and metal connecting piece, ceramic connecting piece and metal connecting piece welded connection, ceramic connecting piece is the step shaft structure of taking central horn hole, the one end of welding capillary (22) in the central horn hole, the attach fitting of welding conducting strip (23) on the outer wall of step shaft tip, the internal face of welding metal connecting piece on the outer wall of step shaft butt, metal connecting piece both ends face, the frame of one end welding flange frame (21), other end welding thrust chamber (3).
The capillary (22) is a flow pressure drop control component of the injector (2), and the injector (2) is of a single capillary (22) injection structure.
Compared with the prior art, the invention has the advantages that:
(1) the invention provides a micro-flow green high-energy single-component thruster structure, which is characterized in that heat conduction channels between an injector, a capillary and the outside are increased through heat conduction sheets, capillary heat conduction wires and the like on the injector, and the temperature of the capillary in the working process of the thruster is reduced.
(2) The invention increases the heat transfer resistance from the thrust chamber to the capillary tube and reduces the heat transfer from the thrust chamber to the capillary tube through the scheme of the front chamber with the ceramic and metal composite structure.
(3) According to the invention, through the flange frame structure, the heat of the thrust chamber is isolated and conducted to the mounting surface of the thruster, and the conduction of the heat to the direction of the micro electromagnetic valve is weakened.
(4) According to the invention, the temperature of the capillary tube is regulated and controlled, the generation of two-phase flow of the propellant in the capillary tube under micro-flow is inhibited, and the stable work of the micro-flow green high-energy single-component thruster is realized.
(5) The micro-propelling system is connected with the outside through the L-shaped injector flange, realizes compact installation structure, and is suitable for micro-propelling systems applied to micro-nano satellites such as cubesat and the like.
Drawings
FIG. 1 is a schematic structural diagram of a micro-flow green high-energy single-component thruster of the present invention;
FIG. 2 is a schematic view of the injector configuration;
FIG. 3 is a schematic view of a flange frame construction;
FIG. 4 is a schematic view of the front chamber;
fig. 5 is a schematic structural view of the thrust chamber.
Detailed Description
The invention relates to a micro-flow green high-energy single-component thruster structure which comprises a micro electromagnetic valve (1), an injector (2), a thrust chamber (3) and a thermal control assembly (4); the outlet of the micro electromagnetic valve (1) is connected with the inlet of the injector (2) and is used for on-off management of circulation of the propellant; an outlet of the injector (2) is connected with an inlet of the thrust chamber (3) and consists of a flange frame (21), a capillary tube (22), a heat conducting sheet (23), a front chamber (24) and a capillary tube heat conducting wire (25), the flange frame (21) of the injector (2) realizes the purpose of blocking the conduction of heat to the direction of the miniature electromagnetic valve (1) in the working process of the thrust chamber (3), the heat conducting sheet (23) reduces the heat conduction of the thrust chamber (3) to the capillary tube (22), the capillary tube heat conducting wire (25) is arranged on the capillary tube (22) and is close to the side of the thrust chamber (3), the temperature of the capillary tube (22) is reduced, and the capillary tube (22) realizes the transportation of; the thrust chamber (3) consists of a catalytic bed (31), a combustion chamber (32) and a spray pipe (33), the propellant realizes catalytic decomposition under the action of the catalyst in the catalytic bed (31), and is further combusted in the combustion chamber (32) and then sprayed out through the spray pipe (33) to generate thrust; the thermal control assembly (4) is arranged on a catalytic bed (31) of the thrust chamber (3) and used for controlling and monitoring the temperature of the catalytic bed (31). The invention provides a micro-flow green high-energy single-component thruster structure, which regulates and controls the temperature of a capillary tube (22) through a heat conducting sheet (23), a capillary tube heat conducting wire (25) and the like, inhibits a propellant from generating two-phase flow in the capillary tube (22) under micro-flow, and realizes the stable work of the micro-flow green high-energy single-component thruster.
The micro-flow green high-energy single-component thruster structure provided by the invention can inhibit the generation of two-phase flow of the thruster in the capillary under the micro-flow, so that the stable work of the micro-flow green high-energy single-component thruster is realized. The micro-flow green high-energy single-element thruster has the characteristics of high specific impulse, greenness, no toxicity, light weight, capability of being pre-packaged and the like, provides required force or moment for micro-nano satellite orbit maneuvering, quick response and the like, and greatly expands the application space of the micro-nano satellite.
As shown in fig. 1, a micro-flow green high-energy single-component thruster structure includes: the device comprises a micro electromagnetic valve (1), an injector (2), a thrust chamber (3) and a thermal control assembly (4). The miniature electromagnetic valve (1) is used for controlling the on-off of the circulation of propellant and comprises an inlet, an on-off control switch and an outlet, the propellant introduced from the inlet flows out of the outlet after being controlled to circulate and blocked by the on-off control switch, the outlet of the miniature electromagnetic valve (1) is in screw connection with the inlet of the injector (2), and the miniature electromagnetic valve is sealed by an aluminum gasket.
As shown in fig. 2, the injector (2) is composed of a flange frame (21), a capillary tube (22), a heat conducting fin (23), a front chamber (24) and a capillary tube heat conducting wire (25), an outlet of the injector (2) is connected with an inlet of the thrust chamber (3) in an electron beam welding mode, and the injector (2) realizes the transportation of propellant, blocks the conduction of heat of the thrust chamber (3) to the direction of the micro solenoid valve (1) and can conduct the heat of the thrust chamber (3) to the outside.
The flange frame (21) is divided into two parts, namely a flange and a frame, as shown in fig. 3, the flange is of an L-shaped structure and is a connecting part of the injector (2) and the micro electromagnetic valve (1) and a mounting surface of the thruster and external connection, an outlet of the micro electromagnetic valve (1) is connected to the flange of the injector (2) through screws and sealed through an aluminum gasket, the thruster is connected with the external connection through screws and is installed with an external satellite in a heat conduction mode, heat of the injector (2) is conducted to the outside, and the temperature of the injector (2) and the micro electromagnetic valve (1) in the working process of the thruster and after the thruster is shut down is reduced. The frame is a hollow cylinder with a side surface opening structure, so that the heat of the thrust chamber (3) is blocked from being conducted to the direction of the miniature electromagnetic valve (1).
The front chamber (24) is used for connecting the injector (2) with the thrust chamber (3) in an electron beam welding manner and comprises a ceramic connecting piece and a metal connecting piece, wherein the metal connecting piece is arranged on the outer side and on the inner side, the ceramic connecting piece is of a stepped shaft structure with a central horn hole, the inner wall surface of the metal connecting piece is welded on the outer wall surface of the thick end of the stepped shaft, two end surfaces of the metal connecting piece are welded on the frame of a flange frame (21) at one end, the thrust chamber (3) is welded on the electron beam at the other end, one end of a capillary tube (22) is welded in the central horn hole of the ceramic connecting piece, the capillary tube (22) is a flow pressure drop control part of the injector (2), the injector (2) is of a single capillary tube (22) injection structure, the other end of the capillary tube (22) is welded on the flange frame (21, the heat conducting strip (23) is composed of a connecting joint and a heat conducting strip, the connecting joint is made of copper materials or silver materials, the connecting joint is welded on the front chamber (24), the position of the connecting joint is the outer side of the welding position of the capillary tube (22) and the front chamber (24), one end of the heat conducting strip is fixed on the connecting joint, the other end of the heat conducting strip is fixed on a supporting plate of a satellite through a pressing sheet, a heat conducting channel between the front chamber (24) and the outside is added, heat of the thrust chamber (3) is conducted to the outside, and conduction of the heat of the thrust chamber (3) to the capillary.
Capillary heat conduction silk (25) of welding on capillary (22), capillary heat conduction silk (25) are copper material or silver material, and one end welding is on capillary (22), and the position is close to capillary (22) and antechamber (24) welding position, and the other end passes through the preforming to be fixed in the backup pad of satellite, forms capillary (22) and outside heat conduction passageway, reduces capillary (22) department temperature.
The thrust chamber (3) is welded on the forechamber (24) of the injector (2) by an electron beam, as shown in fig. 5, the thrust chamber is composed of a catalytic bed (31), a combustion chamber (32) and a nozzle (33), the combustion chamber (32) and the nozzle (33) are of an integral structure, the catalytic bed (31) is welded with the combustion chamber (32) and the nozzle (33) by the electron beam, and the catalytic bed (31) is welded with the forechamber (24) of the injector (2) by the electron beam after being filled with a catalyst. The propellant is catalyzed and decomposed under the action of the catalyst in the catalytic bed (31), and is further combusted in the combustion chamber (32) and then sprayed out through the spray pipe (33) to generate thrust.
The thermal control assembly (4) is arranged on the outer wall of a catalytic bed (31) of the thrust chamber (3) and used for controlling and monitoring the temperature of the catalytic bed (31).
When the thruster works, the thrust chamber (3) generates high temperature, the high temperature is conducted to the injector (2), heat is conducted out of the thruster through the heat conducting sheets (23) and the capillary heat conducting wires (25), and the conduction of the heat to the capillary (22) and the accumulation of the heat on the capillary (22) are reduced. Convective heat transfer power P of the propellant in the capillary (22)qThermal power P conducted from the thrust chamber (3) to the injector (2)tThermal power P derived from the heat-conducting sheet (23)dThe capillary heat-conducting wire (25) is led outThermal power P ofmThe following relationship is preferably satisfied: pq＞Pt-Pd-Pm. Wherein, Pm＝fm*Cp*Tm，fmIndicates propellant flow, CpIs the specific heat capacity of the propellant, TmThe average temperature difference of the propellant at the position 3-5 mm downstream of the capillary is changed.
One end of the capillary tube (22) is connected with an outlet of the miniature electromagnetic valve (1), the other end of the capillary tube (22) is connected with an inlet of the thrust chamber (3), a propellant enters from one end of the capillary tube (22), flows through the capillary tube (22), and then is sprayed into the thrust chamber (3) from the other end of the capillary tube (22), the temperature of the capillary tube (22) is regulated and controlled through the heat conducting fins (23), the capillary tube heat conducting wires (25) and the like, and the generation of two-phase flow of the propellant in the capillary tube (22) under the condition of micro-flow.
Convective heat transfer power P of the propellant in the capillary (22)qThermal power P conducted from the thrust chamber (3) to the injector (2)tThermal power P derived from the heat-conducting sheet (23)dThermal power P derived from capillary heat-conducting wire (25)mThe structure is suitable for low-energy characteristic propellants such as hydrazine and the like, and is also suitable for ADN and HAN-based green high-energy propellants. The preferred scheme is as follows: when the propellant is an ADN-based propellant, let P betAt a flow rate f of 20WmWhen the heat conduction sectional area is 100mg/s, the heat convection power is 14W, and the heat conduction sectional area of the heat dissipation structure is required to be more than or equal to 2.5mm2Capillary with inner diameter not more than 0.3mm and heat conduction power Pd+PdNot less than 6W, ensuring that two-phase flow does not occur in the capillary tube when the flow is small, and ensuring TmIf the temperature is lower than a certain range, the heat conduction power is required to be further increased. The heat dissipation structure and power determination need to be further determined through certain experiments. The micro-flow green high-energy single-component thruster structure provided by the invention can be used for inhibiting the propellant in the capillary tube from generating two-phase flow, so that the working thrust of the micro-flow green high-energy single-component thruster is stable.
The invention provides a micro-flow green high-energy single-component thruster structure, which is characterized in that heat conduction channels between an injector, a capillary and the outside are increased through heat conduction sheets, capillary heat conduction wires and the like on the injector, and the temperature of the capillary in the working process of the thruster is reduced. Through the scheme of the front chamber with the ceramic and metal composite structure, the heat transfer resistance from the thrust chamber to the capillary tube is increased, and the heat transfer from the thrust chamber to the capillary tube is reduced. Through the flange frame structure, the heat of the thrust chamber is isolated and conducted to the mounting surface of the thruster, and the conduction of the heat to the direction of the micro electromagnetic valve is weakened.
According to the invention, the temperature of the capillary tube is regulated and controlled, the generation of two-phase flow of the propellant in the capillary tube under micro-flow is inhibited, and the stable work of the micro-flow green high-energy single-component thruster is realized. The L-shaped injector flange is connected with the outside, so that the mounting structure is compact, and the micro-propelling system is suitable for micro-propelling systems of micro-nano satellites such as cubic satellites.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (9)
1. The utility model provides a green high energy single component thrustor structure of miniflow which characterized in that includes: the device comprises a micro electromagnetic valve (1), an injector (2), a thrust chamber (3) and a thermal control assembly (4);
the outlet of the micro electromagnetic valve (1) is connected with the inlet of the injector (2), and the micro electromagnetic valve (1) is used for controlling the on-off of the circulation of the propellant; the outlet of the injector (2) is connected with the inlet of the thrust chamber (3), and the injector (2) realizes the transportation of the propellant, blocks the conduction of the heat of the thrust chamber (3) to the direction of the micro solenoid valve (1) and can conduct the heat of the thrust chamber (3) to the outside;
the thrust chamber (3) consists of a catalytic bed (31), a combustion chamber (32) and a spray pipe (33), the propellant realizes catalytic decomposition under the action of the catalyst in the catalytic bed (31), and is further combusted in the combustion chamber (32) and then sprayed out through the spray pipe (33) to generate thrust; the thermal control assembly (4) is arranged on the outer wall of a catalytic bed (31) of the thrust chamber (3) and used for controlling and monitoring the temperature of the catalytic bed (31);
the injector (2) is composed of a flange frame (21), a capillary tube (22), a heat conducting fin (23), a front chamber (24) and a capillary tube heat conducting wire (25), the micro electromagnetic valve (1) is installed on the flange frame (21), the front chamber (24) is used for being connected with the thrust chamber (3), two ends of the capillary tube (22) are respectively welded on the flange frame (21) and the front chamber (24), the front chamber (24) is welded on the flange frame (21), one end of the heat conducting fin (23) is installed on the front chamber (24), the other end of the heat conducting fin (23) is connected with the outside, one end of the capillary tube heat conducting wire (25) is installed on the capillary tube (22) and is close to one side of the front chamber (24), and the other.
2. The micro-flow green high-energy single-component thruster structure as claimed in claim 1, wherein the micro solenoid valve (1) comprises an inlet, an on-off control switch and an outlet, and the propellant introduced into the inlet flows out of the outlet after being controlled to flow and blocked by the on-off control switch.
3. The micro-flow green high-energy single-component thruster structure of claim 1, wherein: when the thruster works, the thrust chamber (3) generates high temperature, the high temperature is conducted to the injector (2), heat is conducted out of the thruster through the heat conducting sheets (23) and the capillary heat conducting wires (25), and the conduction of the heat to the capillary (22) and the accumulation of the heat on the capillary (22) are reduced; one end of the capillary tube (22) is connected with an outlet of the miniature electromagnetic valve (1), the other end of the capillary tube (22) is connected with an inlet of the thrust chamber (3), a propellant enters from one end of the capillary tube (22), flows through the capillary tube (22) and then is sprayed into the thrust chamber (3) from the other end of the capillary tube (22), the temperature of the capillary tube (22) is regulated and controlled through the heat conducting sheet (23) and the capillary tube heat conducting wires (25), and the generation of two-phase flow of the propellant in the capillary tube (22) under the condition of micro-flow is inhibited.
4. The micro-flow green high-energy single-component thruster structure of claim 1, wherein: the heat conducting strip (23) is composed of a connecting joint and a heat conducting strip, the connecting joint is made of copper materials or silver materials, the connecting joint is welded on the front chamber (24), the position of the connecting joint is the outer side of the welding position of the capillary tube (22) and the front chamber (24), one end of the heat conducting strip is fixed on the connecting joint, the other end of the heat conducting strip is fixed on a supporting plate of a satellite through a pressing sheet, a heat conducting channel between the front chamber (24) and the outside is added, heat of the thrust chamber (3) is conducted to the outside, and conduction of the heat of the thrust chamber (3) to the capillary.
5. The micro-flow green high-energy single-component thruster structure of claim 1, wherein: the capillary heat conducting wire (25) is made of copper or silver, one end of the capillary heat conducting wire is welded on the capillary (22) and is close to the welding position of the capillary (22) and the front chamber (24), the other end of the capillary heat conducting wire is fixed on a supporting plate of a satellite through a pressing sheet, a heat conducting channel between the capillary (22) and the outside is formed, and the temperature of the capillary (22) is reduced.
6. The micro-flow green high-energy single-component thruster structure of claim 1, wherein: the flange frame (21) is divided into a flange and a frame, the flange is of an L-shaped structure and is a connecting part of the injector (2) and the micro electromagnetic valve (1) and a mounting surface for connecting the thruster and the outside, and the micro electromagnetic valve (1) is connected to the flange of the injector (2) through screws and sealed through an aluminum gasket; the frame is a hollow cylinder with a side surface opening structure, so that the heat of the thrust chamber (3) is blocked from being conducted to the direction of the miniature electromagnetic valve (1).
7. The micro-flow green high-energy single-component thruster structure of claim 1, wherein: the thruster is connected with the outside through screws, and is installed with an external satellite in a heat conduction mode, so that heat of the injector (2) is conducted to the outside, and the temperature of the injector (2) and the temperature of the micro electromagnetic valve (1) are reduced in the working process of the thruster and after the thruster is shut down.
8. The micro-flow green high-energy single-component thruster structure of claim 1, wherein: the antechamber (24) includes ceramic connecting piece and metal connecting piece, ceramic connecting piece and metal connecting piece welded connection, ceramic connecting piece is the step shaft structure of taking central horn hole, the one end of welding capillary (22) in the central horn hole, the attach fitting of welding conducting strip (23) on the outer wall of step shaft tip, the internal face of welding metal connecting piece on the outer wall of step shaft butt, metal connecting piece both ends face, the frame of one end welding flange frame (21), other end welding thrust chamber (3).
9. The micro-flow green high-energy single-component thruster structure of claim 1, wherein: the capillary (22) is a flow pressure drop control component of the injector (2), and the injector (2) is of a single capillary (22) injection structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910452238.0A CN110500200B (en) | 2019-05-28 | 2019-05-28 | Micro-flow green high-energy single-component thruster structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910452238.0A CN110500200B (en) | 2019-05-28 | 2019-05-28 | Micro-flow green high-energy single-component thruster structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110500200A CN110500200A (en) | 2019-11-26 |
| CN110500200B true CN110500200B (en) | 2021-02-09 |
Family
ID=68585751
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910452238.0A Active CN110500200B (en) | 2019-05-28 | 2019-05-28 | Micro-flow green high-energy single-component thruster structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110500200B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110878724B (en) * | 2019-12-09 | 2022-05-10 | 陕西天回航天技术有限公司 | Self-pressurization pulse work unit component catalytic decomposition gas generator |
| CN111637028B (en) * | 2020-04-28 | 2021-04-13 | 北京控制工程研究所 | Structure for reducing influence of propellant dissolved gas on electric arc thruster |
| CN111550328B (en) * | 2020-05-09 | 2021-02-09 | 北京控制工程研究所 | Ignition method for realizing rapid normal-temperature start of hydroxylamine nitrate engine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101963111A (en) * | 2010-09-28 | 2011-02-02 | 北京航空航天大学 | Sample machine on basis of principle of nitrous oxide mono-component thruster and use method thereof |
| CN106134388B (en) * | 2010-12-10 | 2013-12-11 | 上海空间推进研究所 | A kind of monopropellant engine of nontoxic monopropellant |
| CN106134393B (en) * | 2010-12-15 | 2014-03-19 | 上海空间推进研究所 | Low thrust list constituent element peroxide rocket |
| CN106014688A (en) * | 2016-05-10 | 2016-10-12 | 北京控制工程研究所 | Flow control device and method |
| EP3324028A1 (en) * | 2016-11-17 | 2018-05-23 | ECAPS Aktiebolag | Thruster for liquid low-temperature storable propellant blends and method of starting a thruster |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130239544A1 (en) * | 2012-02-02 | 2013-09-19 | David B. Sisk | Distributed pressurization system |
-
2019
- 2019-05-28 CN CN201910452238.0A patent/CN110500200B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101963111A (en) * | 2010-09-28 | 2011-02-02 | 北京航空航天大学 | Sample machine on basis of principle of nitrous oxide mono-component thruster and use method thereof |
| CN106134388B (en) * | 2010-12-10 | 2013-12-11 | 上海空间推进研究所 | A kind of monopropellant engine of nontoxic monopropellant |
| CN106134393B (en) * | 2010-12-15 | 2014-03-19 | 上海空间推进研究所 | Low thrust list constituent element peroxide rocket |
| CN106014688A (en) * | 2016-05-10 | 2016-10-12 | 北京控制工程研究所 | Flow control device and method |
| EP3324028A1 (en) * | 2016-11-17 | 2018-05-23 | ECAPS Aktiebolag | Thruster for liquid low-temperature storable propellant blends and method of starting a thruster |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110500200A (en) | 2019-11-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110500200B (en) | Micro-flow green high-energy single-component thruster structure | |
| US5363645A (en) | Enclosure containing hot gases cooled by transpiration, in particular the thrust chamber of a rocket engine | |
| JP2005516171A (en) | Fluid processing apparatus and method | |
| CN109855456B (en) | Loop heat pipe radiator with vapor-liquid two-phase flow jet boosting device | |
| CN110118136B (en) | Thrust-adjustable hydrogen peroxide single-component thruster | |
| CN109611301B (en) | Hydrazine arc thruster ignition system for inhibiting pressure from fluctuating greatly | |
| CN110792526B (en) | Double-pulse igniter with common-chamber time-sharing ignition output | |
| US3159238A (en) | Diffuser screen with heat-insulating rungs for exhaust noise suppressor for reactionengines | |
| US5501011A (en) | Method of manufacture of an enclosure containing hot gases cooled by transportation, in particular the thrust chamber of a rocket engine | |
| US3115746A (en) | Hydrogen transpiration cooling of a high temperature surface using a metal hydride asthe coolant material | |
| US4108241A (en) | Heat exchanger and method of making | |
| CN110645117B (en) | Ceramic thrust chamber for monopropellant hydroxyl nitrate amino thruster | |
| JPWO2006093198A1 (en) | Heat transfer thruster | |
| CN109099740B (en) | Truss type vapor-liquid phase change heat transfer device and assembly welding method thereof | |
| JP2002048357A (en) | Spacecraft cooling system using heat pump | |
| JP3282755B2 (en) | Catalytic gas generator | |
| US4199937A (en) | Heat exchanger and method of making | |
| US20210325088A1 (en) | Heat transfer device | |
| CN110332059B (en) | Connecting structure for single-component high-temperature alloy injector and ceramic spray pipe | |
| CN109585877B (en) | Cooling system and heat dissipation method for fuel cell | |
| GB2095336A (en) | Electrothermal gas thrust unit | |
| US4461144A (en) | Electrothermal gas thrust units | |
| CN220270200U (en) | Heat buffer assembly for cold material inlet of spiral plate heat exchanger | |
| CN114017208B (en) | Solid-liquid rocket engine catalytic bed and cooling and preheating system and method thereof | |
| CN219200179U (en) | Sealing structure for cold plate seal head of spacecraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |