CN108190048B - Miniature modular butane propulsion system structure and propulsion method - Google Patents
Miniature modular butane propulsion system structure and propulsion method Download PDFInfo
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- CN108190048B CN108190048B CN201711272034.6A CN201711272034A CN108190048B CN 108190048 B CN108190048 B CN 108190048B CN 201711272034 A CN201711272034 A CN 201711272034A CN 108190048 B CN108190048 B CN 108190048B
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- 239000001273 butane Substances 0.000 title claims abstract description 18
- IJDNQMDRQITEOD-UHFFFAOYSA-N n-butane Chemical compound CCCC IJDNQMDRQITEOD-UHFFFAOYSA-N 0.000 title claims abstract description 18
- OFBQJSOFQDEBGM-UHFFFAOYSA-N n-pentane Natural products CCCCC OFBQJSOFQDEBGM-UHFFFAOYSA-N 0.000 title claims abstract description 18
- 238000000034 method Methods 0.000 title abstract description 6
- 239000003380 propellant Substances 0.000 claims abstract description 38
- 238000010438 heat treatment Methods 0.000 claims abstract description 29
- 238000007599 discharging Methods 0.000 claims abstract description 16
- 238000009826 distribution Methods 0.000 claims abstract description 5
- 238000002309 gasification Methods 0.000 claims description 34
- 229910052751 metal Inorganic materials 0.000 claims description 19
- 239000002184 metal Substances 0.000 claims description 19
- 239000007921 spray Substances 0.000 claims description 16
- 239000007788 liquid Substances 0.000 claims description 10
- 229910052755 nonmetal Inorganic materials 0.000 claims description 7
- 238000010146 3D printing Methods 0.000 claims description 5
- 239000007769 metal material Substances 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 3
- 238000012544 monitoring process Methods 0.000 claims description 3
- 238000010276 construction Methods 0.000 claims 6
- 238000013461 design Methods 0.000 abstract description 4
- 230000010354 integration Effects 0.000 abstract description 3
- 238000010923 batch production Methods 0.000 abstract 1
- 238000009434 installation Methods 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 4
- 239000000446 fuel Substances 0.000 description 4
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 239000006200 vaporizer Substances 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 108091092878 Microsatellite Proteins 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000009834 vaporization Methods 0.000 description 1
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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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
- Nozzles (AREA)
Abstract
A micro modular butane propulsion system structure and a propulsion method thereof are disclosed, the structure comprises a module main body structure, an adding and discharging valve, a heating system and an electromagnetic valve; the heating system is positioned in the center of the main structure of the module and is used for carrying out state determination and heating on the propellant; the electromagnetic valves are arranged on the upper part of the module main body structure in parallel and used for on-off management of circulation of the propellant; the charging and discharging valve is positioned in a groove on one side of the module main body structure, is connected with the module main body structure through a screw, and is used for charging and discharging the propellant. The invention adopts a modular design concept to highly integrate the single machines in the traditional propulsion system, has the characteristics of high integration level, small volume, light weight, convenient installation, quick batch production, low cost and the like, and can meet the requirements of the micro-nano satellite on the micro-propulsion system, and is different from the split type distribution structure of the single machines in the traditional propulsion system.
Description
Technical Field
The invention relates to a miniature modular butane propulsion system structure and a propulsion method.
Background
The recent micro-nano satellite rapidly grows up, and the micro-nano satellite has obvious advantages in the global satellite market in the future. Compared with the traditional large satellite, the micro-nano satellite has the characteristics of small volume, light weight, quick response to user demands, short development period, low cost, short service life and the like, has the capability of quickly assembling, testing and forming a space system in batches, can quickly meet the space task demands temporarily proposed, more importantly can complete the tasks of the traditional large satellite by forming a distributed constellation, and is the trend of future military space technology development. According to the characteristics of the micro-nano satellite, the micro-propulsion system is required to have the characteristics of modularization, small volume, light weight and the like, and the miniaturization of the propulsion system is difficult to realize due to the difference of design ideas and processing technologies of the traditional propulsion system.
In order to meet the requirements of a micro-nano satellite on a propulsion system, the invention provides a butane liquefied gas micro-propulsion module which is different from a split type distribution structure of a traditional propulsion system, has the characteristics of high integration level, modularization, low cost and prepackaging, and can meet the requirements of the micro-nano satellite on the micro-propulsion system.
The Chinese patent 'micro liquid fuel propulsion system for micro-nano satellite' (patent number: CN200810220280.1) 'micro liquid fuel propulsion system for micro-nano satellite' is a propulsion system which carries out micro design on the traditional propulsion system, and comprises a pressurized gas generator, a micro propeller, a fuel storage tank for providing liquid fuel for the micro propeller, a pipeline and other structures, all the structures are distributed on a plane, the volume is large, and the requirements of the micro-nano satellite on the volume and the weight of the propulsion system are difficult to meet.
Chinese patent (patent No. CN201420562343.2) "a high pressure gas propulsion system for microsatellites" is characterized by comprising: the high-pressure gas storage bottle is a spherical aluminum alloy inner container, and carbon fibers are wound outside the aluminum alloy inner container; and the high-pressure self-locking cylinder valve is arranged at the mouth of the high-pressure gas storage cylinder and is used for controlling the gas in the high-pressure gas storage cylinder to enter and exit. The patent needs gas compression storage, and the system pressure is large, so the volume and the weight of the storage box are large, and the requirements of the micro-nano satellite on the volume and the weight of a propulsion system cannot be met.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the invention overcomes the defects of the prior art, provides a micro modular butane propulsion system structure, and realizes the modularization and the miniaturization of the structure by carrying out the miniaturization design on a single machine and highly integrating a storage tank, a gasification chamber, a pipeline and the like with larger volume in the traditional propulsion system, thereby greatly reducing the volume and the weight of the micro propulsion system on the premise of ensuring that the performance meets the requirements of micro-nano satellites.
The technical scheme adopted by the invention is as follows: a micro modular butane propulsion system configuration comprising: the device comprises a module main body structure, an adding and discharging valve, a heating system and an electromagnetic valve; the heating system is positioned in the center of the main structure of the module and is used for carrying out state determination and heating on the propellant; the electromagnetic valves are arranged on the upper part of the module main body structure in parallel and used for on-off management of circulation of the propellant; the charging and discharging valve is positioned in a groove on one side of the module main body structure, is connected with the module main body structure through a screw, and is used for charging and discharging the propellant.
The electromagnetic valve mounting bracket is characterized by also comprising a metal auxiliary bracket and an electromagnetic valve mounting bracket; the electromagnetic valve mounting support is fixed at two ends of the electromagnetic valve, and the electromagnetic valve support, the metal auxiliary support and the module main body structure are connected and fixed through screws.
The module main body structure is formed by 3D printing of a non-metal material; the appearance of the main structure of the module is a cuboid structure, and the inside of the main structure of the module comprises a storage tank, a gasification chamber, a circulating pipeline and a spray pipe structure.
The heating system comprises a heater, a temperature sensor and a pressure sensor; wherein the heater is used for heating the propellant flowing into the gasification chamber, and the temperature sensor and the pressure sensor are used for monitoring the temperature and the pressure value of the propellant in the gasification chamber.
The heater comprises a main heater and an auxiliary heater; the main heater and the auxiliary heater are respectively positioned in the circulation pipeline and the gasification chamber; the main heater and the auxiliary heater are both composed of heat capacity and heating wires, the heating wires are wound on the heat capacity, and the heat capacity is generally made of porous medium materials
The metal auxiliary supports are placed in the grooves in the two sides of the module main body structure, screws sequentially penetrate through the electromagnetic valve support, the module main body structure and the metal auxiliary supports, and the electromagnetic valve support can be connected with the module main body structure.
The inside storage tank of module major structure is annular major structure, and the vaporizer is located the annular intermediate position of storage tank for the realization is with the liquid propellant or the complete gasification of gas-liquid mixture propellant that the storage tank flows, and the circulation pipeline is located the clearance of storage tank and vaporizer, for propellant circulation channel, and the quantity of spray tube can be N according to the demand, and its distribution position also can arrange according to the demand, and gaseous propellant passes through the spray tube blowout, produces thrust.
The number of the circulation pipelines is N +1, wherein 1 pipeline is connected with the storage box and the gasification chamber, and the rest N pipelines are connected with the gasification chamber and the spray pipe.
The number of the electromagnetic valves is N +1, the electromagnetic valves are arranged on the upper surface of the module main body structure in parallel, and two ends of the electromagnetic valves are fixed by electromagnetic valve supports.
A miniature modular butane propulsion method comprises the following steps:
1) the electromagnetic valve is arranged on the main body structure through the metal auxiliary bracket and the electromagnetic valve mounting bracket;
2) filling the propellant into the storage tank through a charging and discharging valve;
3) the solenoid valve between the storage tank and the gasification chamber is in an open state, and the propellant can enter the gasification chamber through a circulation pipeline;
4) the heater in the gasification chamber is in a working state, and the heating system also starts to work;
5) and (3) enabling an electromagnetic valve between the gasification chamber and the spray pipe to be in an open state, and spraying the heated gaseous propellant from the spray pipe.
Compared with the prior art, the invention has the advantages that:
(1) the module structure of the micro propulsion system provided by the invention completes the structures of the storage tank, the gasification chamber, the pipeline, the thruster and the like through the 3D printing technology, breaks through the limitation of the traditional processing technology on the structural layout, realizes the high integration of each single machine, does not need special pipeline connection, has compact and novel spatial layout, is designed into a circular structure, is the gasification chamber in the middle of the storage tank, is distributed at the gap part, fully utilizes the space, and realizes the connection between the single machines. This feature allows the volume and weight of the micro propulsion system to be greatly reduced.
(2) According to the invention, the heater is directly arranged in the pipeline and the gasification chamber, and can heat the propellant in two ways of convection heat exchange and conduction heat exchange, so that the heating efficiency is greatly improved on the premise of limited space and heating power.
(3) According to the invention, the electromagnetic valve, the mounting bracket of the discharge valve and the non-metal module main body are connected through the screws, in order to improve the reliability and the service life of the connection of the metal screws and the non-metal material, the structure of the metal auxiliary bracket is designed, and the structure of the metal auxiliary bracket is embedded into the groove of the non-metal module main body structure, so that the direct connection of the metal screws and the metal auxiliary bracket is realized, and the reliability and the service life of the connection are improved.
Drawings
FIG. 1 is a schematic view of a miniature modular butane propulsion system according to the present invention;
FIG. 2 is a schematic diagram of a main structure of a non-metal 3D printing module according to the present invention;
FIG. 3 is a schematic view of the reservoir configuration of the present invention;
fig. 4 is a schematic view of the heater configuration of the present invention.
Detailed Description
As shown in fig. 1, the invention relates to a structure of a micro butane propulsion system, comprising: the device comprises a module main body structure 1, an adding and discharging valve 2, a heating system and an electromagnetic valve 8; the heating system is positioned in the center of the module main body structure 1 and is used for carrying out state determination and heating on the propellant; the electromagnetic valves 8 are arranged on the upper part of the module main body structure 1 in parallel and used for on-off management of circulation of the propellant; the adding and discharging valve 2 is located in a groove on one side of the module main body structure 1, is connected with the module main body structure 1 through a screw, and realizes the filling and discharging of the propellant through the adding and discharging valve 2.
The electromagnetic valve mounting bracket also comprises a metal auxiliary bracket 6 and an electromagnetic valve mounting bracket 7; the two ends of the electromagnetic valve 8 are fixed through the electromagnetic valve mounting bracket 7, and the electromagnetic valve bracket 7, the metal auxiliary bracket 6 and the module main body structure 1 are fixedly connected through screws.
The module main body structure 1 is formed by 3D printing of a non-metal material; the appearance of the module main body structure 1 is a cuboid structure, and the inside of the module main body structure comprises a storage tank 9, a gasification chamber 10, a circulating pipeline 11 and a spray pipe 12 structure.
The heating system comprises a heater 3, a temperature sensor 4 and a pressure sensor 5; wherein the heater 3 is used for heating the propellant flowing into the gasification chamber 10, and the temperature sensor 4 and the pressure sensor 5 are used for monitoring the temperature and the pressure value of the propellant in the gasification chamber 10.
The heater 3 comprises a main heater and a sub-heater; the main heater and the sub-heater are respectively positioned in the circulation pipeline 11 and the gasification chamber 10; the main heater and the auxiliary heater are both composed of a heat capacity 13 and a heating wire 14, the heating wire 14 is wound on the heat capacity 13, and the heat capacity 13 is generally made of porous medium materials
Metal auxiliary supports 6 are placed in grooves in two sides of the module main body structure 1, screws sequentially penetrate through the electromagnetic valve support 7, the module main body structure 1 and the metal auxiliary supports 6, and the electromagnetic valve support 7 can be connected with the module main body structure.
The internal storage tank 9 of the module main structure 1 is an annular main structure, the gasification chamber 10 is located in the annular middle position of the storage tank 9 and used for completely gasifying liquid propellant or gas-liquid mixed propellant flowing out of the storage tank, the circulation pipeline 11 is located in the gap between the storage tank 9 and the gasification chamber 10 and is a propellant circulation channel, the number of the spray pipes 12 can be N according to requirements, the distribution positions of the spray pipes can be arranged according to requirements, and the gaseous propellant is sprayed out through the spray pipes 12 to generate thrust.
The number of the circulation pipelines 11 is N +1, wherein 1 pipeline is connected with the storage tank 9 and the gasification chamber 10, and the other N pipelines are connected with the gasification chamber 10 and the spray pipe 12.
The number of the electromagnetic valves 8 is N +1, the electromagnetic valves are arranged on the module main body structure 1 in parallel, and two ends of the electromagnetic valves are fixed by the electromagnetic valve support 7.
The invention relates to a micro modular butane propelling method which is characterized by comprising the following steps:
1. the electromagnetic valve 8 is arranged on the main structure 1 through the metal auxiliary bracket 6 and the electromagnetic valve mounting bracket 7;
2. the propellant is filled into the storage tank 9 through the charging and discharging valve 2;
3. the solenoid valve 8 between the storage tank 9 and the gasification chamber 10 is in an open state, and the propellant can enter the gasification chamber 10 through a circulation pipeline 11;
4. the heater 3 in the gasification chamber 10 is in a working state, and the heating system also starts to work;
5. the solenoid valve 8 between the vaporisation chamber 10 and the nozzle 12 is switched on and the heated propellant gas is ejected through the nozzle 12.
By adopting the structure of the invention, the mass and the volume of the whole propulsion system can be greatly reduced, thereby meeting the severe requirements of the micro-nano satellite on the propulsion system. The butane propellant is stored in liquid form, and is gasified by a heating and gasifying device and then is injected through a nozzle, so that the thrust is generated.
The present invention has not been described in detail, partly as is known to the person skilled in the art.
Claims (6)
1. A micro modular butane propulsion system construction, comprising: the device comprises a module main body structure (1), an adding and discharging valve (2), a heating system and an electromagnetic valve (8); the heating system is positioned in the center of the module main body structure (1) and is used for carrying out state determination and heating on the propellant; the electromagnetic valves (8) are arranged on the upper part of the module main body structure (1) in parallel and used for on-off management of circulation of the propellant; the charging and discharging valve (2) is positioned in a groove on one side of the module main body structure (1), is connected with the module main body structure (1) through a screw, and is used for charging and discharging the propellant through the charging and discharging valve (2);
the heating system comprises a heater (3), a temperature sensor (4) and a pressure sensor (5); wherein the heater (3) is used for heating the propellant flowing into the gasification chamber (10), and the temperature sensor (4) and the pressure sensor (5) are used for monitoring the temperature and the pressure value of the propellant in the gasification chamber (10);
the heater (3) comprises a main heater and an auxiliary heater; the main heater and the auxiliary heater are respectively positioned in the circulating pipeline (11) and the gasification chamber (10); the main heater and the auxiliary heater are both composed of a heat capacity (13) and a heating wire (14), the heating wire (14) is wound on the heat capacity (13), and the heat capacity (13) is generally made of porous medium materials;
the module main body structure (1) is formed by 3D printing of a non-metal material; the appearance of the module main body structure (1) is a cuboid structure, and the inside of the module main body structure comprises a storage box (9), a gasification chamber (10), a circulating pipeline (11) and a spray pipe (12) structure.
2. A miniature modular butane propulsion system construction, according to claim 1, wherein: the electromagnetic valve mounting bracket also comprises a metal auxiliary bracket (6) and an electromagnetic valve mounting bracket (7); the two ends of the electromagnetic valve (8) are fixed through the electromagnetic valve mounting bracket (7), and the electromagnetic valve mounting bracket (7) and the metal auxiliary bracket (6) are fixedly connected with the module main body structure (1) through screws.
3. A miniature modular butane propulsion system construction, according to claim 2, wherein: the metal auxiliary supports (6) are placed in grooves in two sides of the module main body structure (1), screws sequentially penetrate through the electromagnetic valve support (7), the module main body structure (1) and the metal auxiliary supports (6), and connection of the electromagnetic valve support (7) and the module main body structure can be achieved.
4. A miniature modular butane propulsion system construction according to any one of claims 1 to 3, wherein: the inner storage box (9) of the module main body structure (1) is of an annular main body structure, the gasification chamber (10) is located in the annular middle position of the storage box (9) and used for completely gasifying liquid propellant or gas-liquid mixed propellant flowing out of the storage box, the circulation pipeline (11) is located in the gap between the storage box (9) and the gasification chamber (10) and is a propellant circulation channel, the number of the spray pipes (12) can be N according to requirements, the distribution positions of the spray pipes can also be arranged according to requirements, and gaseous propellant is sprayed out through the spray pipes (12) to generate thrust.
5. A miniature modular butane propulsion system construction according to any one of claims 1 to 3, wherein: the number of the circulation pipelines (11) is N +1, wherein 1 is connected with the storage tank (9) and the gasification chamber (10), and the rest N channels are connected with the gasification chamber (10) and the spray pipe (12).
6. A miniature modular butane propulsion system construction, according to claim 5, wherein: the number of the electromagnetic valves (8) is N +1, the electromagnetic valves are arranged on the module main body structure (1) in parallel, and two ends of the electromagnetic valves are fixed by the electromagnetic valve support (7).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711272034.6A CN108190048B (en) | 2017-12-05 | 2017-12-05 | Miniature modular butane propulsion system structure and propulsion method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711272034.6A CN108190048B (en) | 2017-12-05 | 2017-12-05 | Miniature modular butane propulsion system structure and propulsion method |
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| CN108190048B true CN108190048B (en) | 2020-04-10 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109635378A (en) * | 2018-11-27 | 2019-04-16 | 上海空间推进研究所 | Integrated modular system |
| CN110562496B (en) * | 2019-08-21 | 2021-05-11 | 上海航天控制技术研究所 | Integrated satellite propulsion system |
| CN111114835B (en) * | 2019-12-24 | 2023-06-23 | 兰州空间技术物理研究所 | Liquid propellant supply assembly for electric propulsion and electric propulsion system |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101907040A (en) * | 2010-07-23 | 2010-12-08 | 北京航空航天大学 | Nitrogen cold gas micro propulsion device adopting ring storage tank |
| CN104828262A (en) * | 2015-04-30 | 2015-08-12 | 北京控制工程研究所 | Low-pressure liquefied gas thrust generating method for spacecraft |
| US9796486B1 (en) * | 2013-03-15 | 2017-10-24 | Planetary Resources Development Corp. | Integrated propulsion and primary structure module for microsatellites |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8820359B2 (en) * | 2008-10-21 | 2014-09-02 | The Aerospace Corporation | Seamless fluid storage and transport module |
| US9228570B2 (en) * | 2010-02-16 | 2016-01-05 | University Of Florida Research Foundation, Inc. | Method and apparatus for small satellite propulsion |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101907040A (en) * | 2010-07-23 | 2010-12-08 | 北京航空航天大学 | Nitrogen cold gas micro propulsion device adopting ring storage tank |
| US9796486B1 (en) * | 2013-03-15 | 2017-10-24 | Planetary Resources Development Corp. | Integrated propulsion and primary structure module for microsatellites |
| CN104828262A (en) * | 2015-04-30 | 2015-08-12 | 北京控制工程研究所 | Low-pressure liquefied gas thrust generating method for spacecraft |
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