CN101943082A - Heating gasification device for liquefied gas micro-propulsion system - Google Patents
Heating gasification device for liquefied gas micro-propulsion system Download PDFInfo
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- CN101943082A CN101943082A CN2010102384953A CN201010238495A CN101943082A CN 101943082 A CN101943082 A CN 101943082A CN 2010102384953 A CN2010102384953 A CN 2010102384953A CN 201010238495 A CN201010238495 A CN 201010238495A CN 101943082 A CN101943082 A CN 101943082A
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- propellant
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- conducting module
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- propulsion system
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Abstract
The invention discloses a heating gasification device for a liquefied gas micro-propulsion system. The device comprises a first propellant storage box, a second propellant storage box, a first heat conducting module, a second heat conducting module, a pressure reducer, a pressure stabilizing tank, a safety valve, a pressure sensor and a filter. In the device, a passive heating mode is adopted, and a satellite internal heat dissipation unit is used as a heat source, so that extra power consumption is not needed; and the gasification device has the advantages of reducing the production cost, fully gasifying the propellant and ensuring that the propellant completes work in the form of gas state, along with simple structure, a few elements and devices and high reliability and safety.
Description
Technical field
The invention belongs to the little Push Technology of liquid gas field, relate to a kind of heating and gasifying device that is used for the little propulsion system of liquid gas.
Background technique
Along with micro-nano satellite obtains more and more widely use, the little propulsion system of liquid gas is with its special advantages, is widely used in to carry out attitude control on the microsatellite and track is kept and controlled.In the little propulsion system of liquid gas since propellant agent be to store with liquid form, during work, need the absorption heat to carry out gasification and become gas, from the thruster of propulsion system, spray then, if the heat that absorbs in the gasification is insufficient, cause gasification not exclusively, just having the part propellant agent sprays from thruster with the form of liquid state, cause the decline of propulsion system specific impulse, and the waste of propellant agent, and might make propulsion system can't reach its projected life, therefore, generally all design heating equipment in the little propulsion system of liquid gas, propellant agent has been heated, guaranteed its gasification.
The little propulsion system of liquid gas is made up of gasification system 17 and propulsion system 18 two-part usually, as shown in Figure 1, heat by the liquid propellant in 16 pairs of propellant tanks 13 of heating equipment in the gasification system 17, after making the liquid propellant gasification, enter into propulsion system 18 via pipeline, the supply pipeline 14 in propulsion system 18 enters into each supply air line 12, arrives in the corresponding thruster 15 through supply air line 12, final ejection from the thruster 15 of propulsion system obtains thrust.But this mode is because heating equipment 16 also needs consumed power, and therefore the power of the little propulsion system consumption of whole liquid gas is bigger, wastes energy.
Summary of the invention:
The object of the present invention is to provide a kind of heating and gasifying device that is used for the little propulsion system of liquid gas, gasification installation of the present invention adopts passive heating mode, promptly from inside satellite heat-sink unit draw heat, thereby propellant agent is heated, do not need to consume extra power; That this covering device has is simple in structure, not consumed power, the sufficient advantage of Btu utilization, and propellant agent is gasified totally.
A kind of heating and gasifying device that is used for the little propulsion system of liquid gas of the present invention mainly comprises first propellant tank, second propellant tank, first heat conducting module, second heat conducting module, decompressor, surge tank, safety valve, pressure transducer and filter.
Be separately installed with first heat conducting module and second heat conducting module on first propellant tank and second propellant tank, first heat conducting module is connected by pipeline with second heat conducting module;
Second heat conducting module is connected with safety valve by pipeline, and safety valve is connected with the inlet four-way, is connected with first propellant tank, second propellant tank by pipeline on the inlet four-way;
First heat conducting module is connected with decompressor, surge tank and filter in turn by pipeline, and filter connects pressure transducer and thruster by the outlet threeway.
Described first heat conducting module and second heat conducting module will be by the heat transfer that obtains on the satellite heat-sink unit to propellant tanks, because liquid propellant agent has certain thermal capacitance, so liquid propellant stores heat, and the liquid propellant temperature can raise; Liquid propellant is stored in the elevated pressures tank, and external connecting pipe road pressure is vacuum, therefore when opening the safety-valve, liquid propellant can flow out in tank under pressure, and along with the variation of pressure, begin gasification, enter second heat conducting module and first heat conducting module subsequently successively, propellant agent further absorbs the heat gasification and is gaseous state; Store pressure because the propulsion system working pressure is lower than propellant agent, therefore the propellant agent through gasification need pass through reduction valve, makes pressure reduce to the propulsion system working pressure; Because of the little propulsion system thrust of liquid gas is very little, the variation in pressure of propellant agent can cause bigger influence to service behaviour, and therefore post-decompression gaseous propellant enters surge tank, makes pressure keep stable, enters in the filter subsequently and filters.So far, through the gasification installation effect, liquid propellant is finished gasification.
The invention has the advantages that:
1, a kind of heating and gasifying device that is used for the little propulsion system of liquid gas is simple in structure, and quality is little, the reliability height;
2, a kind of heating and gasifying device that is used for the little propulsion system of liquid gas adopts passive heat absorption pattern, is the gasification installation thermal source with the inside satellite heat-sink unit, by from drawing the heat-sink unit heat, finishes the purpose to the propellant agent heating, reduces the consumption on the power;
3, a kind of heating and gasifying device that is used for the little propulsion system of liquid gas can make propellant agent fully be gasified, and guarantees that propellant agent finishes the work with gaseous form.
Description of drawings
Fig. 1 is the little propulsion system connection diagram of common liquid gas in the prior art;
Fig. 2 is used for the heating and gasifying device structural drawing of the little propulsion system of liquid gas for the present invention.
Among the figure:
The 1-second propellant tank 2-first propellant tank 3-safety valve
The 4-second heat conducting module 5-first heat conducting module 6-decompressor
7-surge tank 8-filter 9-pressure transducer
10-outlet threeway 11-inlet four-way 12-supply air line
13-propellant tank 14-service 15-thruster
16-heating equipment 17-gasification system 18-propulsion system
Embodiment:
A kind of heating and gasifying device that is used for the little propulsion system of liquid gas of the present invention, comprise first propellant tank 2, second propellant tank 1, first heat conducting module 5, second heat conducting module 4, decompressor 6, surge tank 7, safety valve 3, pressure transducer 9 and filter 8, as shown in Figure 2.
The propellant agent inlet of second heat conducting module 4 is connected with safety valve 3 by pipeline, and safety valve 3 is connected with inlet four-way 11, is connected with first propellant tank 2, second propellant tank 1 by pipeline on the inlet four-way 11.
Extraneous liquid petroleum gas (liquid propane gas) is loaded in first propellant tank 2 and second propellant tank 1 by inlet four-way 11, can change the quality of the liquid propellant that loads according to different mission requirementses.Safety valve 3 is used for making liquid propellant and other line isolation of micro propulsion device in the propellant tank after the filling.First heat conducting module 5 contacts with the radiator of second heat conducting module 4 with satellite thermal control unit, obtains heat by the inside satellite heat-dissipating part.Because liquid propellant agent has certain thermal capacitance, so propellant agent can store heat, and the liquid propellant temperature can raise; Liquid propellant is stored in first propellant tank 2 and second propellant tank 1 of elevated pressures, and external connecting pipe road pressure is vacuum, therefore when opening the safety-valve 3 the time, liquid propellant can flow out in first propellant tank 2, second propellant tank 1 under pressure, and along with the variation of pressure, begin gasification, and enter successively in second heat conducting module 4 and first heat conducting module 5.Described first heat conducting module 5 and 4 indoor designs of second heat conducting module have the U-shaped pipeline, and not vaporized liquid propellant flows in the U-shaped pipeline, absorbs the heat on first heat conducting module 5 and second heat conducting module 4, and not vaporized propellant agent is further gasified.
The propellant agent outlet of first heat conducting module 5 is connected with decompressor 6, surge tank 7 and filter 8 in turn by pipeline, propellant agent after most of gasification and the not vaporized propellant agent of fraction are entered in the decompressor 6 by first heat conducting module 5 and reduce pressure, pressure drop process through decompressor 6, make whole propellant agent gasifications, guarantee that thus propellant agent fully gasifies, so far the propellant agent gasification is finished.Also can make the propellant pressure after the gasification drop to the thruster desired pressure that enters the mouth by decompressor 6 from 0.84MPa.Decompressor 6 post-decompression propane gas enter surge tank 7, make propellant pressure keep stable, guarantee that propellant agent can enter thruster stably, and when micro propulsion device was worked, fluctuation can not appear in the pressure of propellant agent.Propellant agent after the gasification enters into filter 8 and filters, in order to avoid exist impurity to stop up the throat of the thruster in the extraneous propulsion system in the propellant gas after the gasification.Filter 8 is connected with pressure transducer 9 by outlet threeway 10.Outlet threeway 10 is connected with propulsion system.Nitrogen after the filtration finally enters propellant agent supply air line in the propulsion system by outlet threeway 10, enters into thruster via supply air line; Post-decompression propellant pressure is by pressure transducer 9 monitorings.
Claims (4)
1. a heating and gasifying device that is used for the little propulsion system of liquid gas is characterized in that: comprise first propellant tank, second propellant tank, first heat conducting module, second heat conducting module, decompressor, surge tank, safety valve, pressure transducer and filter;
Be separately installed with first heat conducting module and second heat conducting module on first propellant tank and second propellant tank, the propellant agent outlet of second heat conducting module is connected by pipeline with the propellant agent inlet of first heat conducting module;
The propellant agent inlet of second heat conducting module is connected with safety valve by pipeline, and safety valve is connected with the inlet four-way, is connected with first propellant tank, second propellant tank by pipeline on the inlet four-way;
The propellant agent outlet of first heat conducting module is connected with decompressor, surge tank and filter in turn by pipeline, and filter connects pressure transducer and thruster by the outlet threeway.
2. a kind of according to claim 1 heating and gasifying device that is used for the little propulsion system of liquid gas is characterized in that: described first propellant tank and second propellant tank are cylindrical tank.
3. a kind of according to claim 1 heating and gasifying device that is used for the little propulsion system of liquid gas is characterized in that: the pressure that stores in described first propellant tank and second propellant tank is 0.84MPa, and filling liquid propellant gross mass is 0.6kg.
4. a kind of according to claim 1 heating and gasifying device that is used for the little propulsion system of liquid gas is characterized in that: described first heat conducting module and second heat conducting module are inner to be the U-shaped pipeline.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102384953A CN101943082A (en) | 2010-07-23 | 2010-07-23 | Heating gasification device for liquefied gas micro-propulsion system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102384953A CN101943082A (en) | 2010-07-23 | 2010-07-23 | Heating gasification device for liquefied gas micro-propulsion system |
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| CN101943082A true CN101943082A (en) | 2011-01-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2010102384953A Pending CN101943082A (en) | 2010-07-23 | 2010-07-23 | Heating gasification device for liquefied gas micro-propulsion system |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103453963A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Orbital propellant surplus measurement device and method for spacecraft |
| 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 |
| CN106564623A (en) * | 2016-09-30 | 2017-04-19 | 上海空间推进研究所 | System and method for liquefied gas constant-pressure propulsion of small satellite |
| GB2561898A (en) * | 2017-04-28 | 2018-10-31 | Mexichem Fluor Sa De Cv | Improvements in or relating to propellant conditioning assemblies |
| CN110053789A (en) * | 2019-06-05 | 2019-07-26 | 北京宇航天驰空间科技有限公司 | Variable thrust propulsion system and thrust change method |
| CN110395410A (en) * | 2019-07-04 | 2019-11-01 | 南京理工大学 | Rail control all-in-one micro cold air propulsion system |
| CN112918705A (en) * | 2021-03-12 | 2021-06-08 | 深圳航天东方红卫星有限公司 | Thermal control system and method of integrated propulsion subsystem |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| GB2051246A (en) * | 1979-04-25 | 1981-01-14 | British Aerospace | Propellant Feed System |
| CN101508349A (en) * | 2009-03-17 | 2009-08-19 | 北京航空航天大学 | Fluid circuit control device suitable of nano-satellite hot control system |
| CN101508348A (en) * | 2009-03-06 | 2009-08-19 | 上海微小卫星工程中心 | Shutdown control method of self-pressurized liquefied gas propelling system |
-
2010
- 2010-07-23 CN CN2010102384953A patent/CN101943082A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2051246A (en) * | 1979-04-25 | 1981-01-14 | British Aerospace | Propellant Feed System |
| CN101508348A (en) * | 2009-03-06 | 2009-08-19 | 上海微小卫星工程中心 | Shutdown control method of self-pressurized liquefied gas propelling system |
| CN101508349A (en) * | 2009-03-17 | 2009-08-19 | 北京航空航天大学 | Fluid circuit control device suitable of nano-satellite hot control system |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103453963A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Orbital propellant surplus measurement device and method for spacecraft |
| CN103453963B (en) * | 2013-08-08 | 2018-05-18 | 上海卫星工程研究所 | A kind of spacecraft in-orbit Residual Propellant measuring device and method |
| 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 |
| CN104828262B (en) * | 2015-04-30 | 2017-05-03 | 北京控制工程研究所 | Low-pressure liquefied gas thrust generating method for spacecraft |
| CN106564623A (en) * | 2016-09-30 | 2017-04-19 | 上海空间推进研究所 | System and method for liquefied gas constant-pressure propulsion of small satellite |
| CN106564623B (en) * | 2016-09-30 | 2019-05-17 | 上海空间推进研究所 | Grapefruit satellite liquefied gas constant pressure propulsion system and method |
| GB2561898A (en) * | 2017-04-28 | 2018-10-31 | Mexichem Fluor Sa De Cv | Improvements in or relating to propellant conditioning assemblies |
| US11465791B2 (en) | 2017-04-28 | 2022-10-11 | Mexichem Fluor S.A. De C.V. | Propellant conditioning assemblies |
| CN110053789A (en) * | 2019-06-05 | 2019-07-26 | 北京宇航天驰空间科技有限公司 | Variable thrust propulsion system and thrust change method |
| CN110395410A (en) * | 2019-07-04 | 2019-11-01 | 南京理工大学 | Rail control all-in-one micro cold air propulsion system |
| CN112918705A (en) * | 2021-03-12 | 2021-06-08 | 深圳航天东方红卫星有限公司 | Thermal control system and method of integrated propulsion subsystem |
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Application publication date: 20110112 |