CN105035365A - Satellite temperature control method allowing rapid responding and multi-orbit adaption - Google Patents
Satellite temperature control method allowing rapid responding and multi-orbit adaption Download PDFInfo
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- CN105035365A CN105035365A CN201510466005.8A CN201510466005A CN105035365A CN 105035365 A CN105035365 A CN 105035365A CN 201510466005 A CN201510466005 A CN 201510466005A CN 105035365 A CN105035365 A CN 105035365A
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Abstract
The invention provides a satellite temperature control method allowing rapid responding and multi-orbit adaption, wherein by adopting a heat pipe network, reinforcing contact thermal conduction, and spraying a high-emissivity thermal control coating inside a satellite to reinforce in-cabin thermal conduction and radiation heat exchange, a temperature field is distributed uniformly in a cabin; a whole satellite temperature level is adjusted by a compensative electric heater; a nightside of a side plate of the satellite is taken as a major heat dissipation face, the outer surface of the nightside is sprayed with a white paint, and all the other outer surfaces of the satellite body, except for the major heat dissipation face, are covered by multiple layers of thermal insulation assemblies; and components outside the satellite are sprayed with a white paint thermal control coating. A propelling cabin has independent design, wherein the entire outside of the cabin is covered by the multiple layers of the thermal insulation assemblies, a baseplate inside the cabin is covered by the multiple layers of the thermal insulation assemblies, and the propelling cabin is finally integrated with a platform cabin. By integral design of machinery, heat and electricity, the satellite temperature control method allowing the rapid responding and the multi-orbit adaption provided by the invention realizes thermal control requirements of the whole satellite under conditions of a sun-synchronous orbit and an inclined track by the temperature control method.
Description
Technical field
The invention belongs to spacecraft Evolution of Thermal Control Technique field, relate to the satellite Temp. control method that a kind of quick response multi-track adapts to.
Background technology
In recent years along with the progress of electronics integrated technology and capacity weight miniaturization technology, the features such as small satellite relies on its higher Integration ofTechnology, cost is low, the lead time is short, achieve develop rapidly.The small satellite of development High Performance capacity weight and low cost, by the effect progress of space technology being played to technology traction and support.
Satellite Thermal Design main task is that period provides a good thermal environment for satellite in orbit, ensures satellite equipment, equipment reliable operation within the range of temperatures of defined; And effectively control the thermal drop of satellite platform.At present, being the technological means of small investment, instant effect by the thermal property that theoretical modeling and computer modeling carry out analog satellite, is also the important research direction of thermal analyses in satellite fields.The main purpose of thermal balancing test of satellite is by obtaining satellite temperature transition in orbit for providing the necessary data of thermal model correction.Effective combination of satellite thermal analyses and thermal test, had both improve thermoanalytical particularity, further provided the approach simplifying thermal balancing test of satellite.
In conventional satellite design propulsion system one circumferentially in platform structure system, the lead time asynchronous meeting of the development of propulsion system week and plateform system produces the impact of restriction mutually on the Development Schedule of whole star, finally affect lead time and the progress of whole star.Under inclined plane condition, whole star is without fixing heat delivery surface, in order to reduce orbit external thermal flux change to the impact of instrument in star, the design of whole magnitude temperatureization, raising thermal control reliability and enough thermal design surpluses in-orbit.One adopts the Active thermal control technology such as Thermal Control Shutter controllable heat dissipation face, reduces satellite sunny slope and the opaco temperature difference, meets the temperature environment requirement that instrument and equipment in star normally works.Adopt Active thermal control means can increase cost and lead time elongation, disagree with the rapid development of satellite, the productive target of low cost.In order to solve the problem, need to develop a kind of simplicity of design, lead time fast speed Satellite Thermal Design method.
At present, under the different rail conditions of satellite thermal design there are the following problems usually:
1, under sun-synchronous orbit condition, in satellite layout propulsion system one circumferentially in platform structure system, propulsion system needs to carry out corresponding thermal design, and platform isothermalization designs, and heat delivery surface sprays paint process.In the method propulsion system be distributed in whole star each regard to thermal control design complicated operation, each surface temperature skewness resource consumption is large, does not utilize the utilization of resources.
2, under inclined plane condition, need to adopt the Active thermal control technology such as Thermal Control Shutter controllable heat dissipation face, reduce satellite sunny slope and the opaco temperature difference, meet the temperature environment requirement that instrument and equipment in star normally works.The major defect of this device is that Heavy Weight, system complex, reliability are low, and for the heat radiation of satellite, cost is too large.
Summary of the invention
The thermal design needs of problems of satellite under multiple rail conditions cannot be adapted to solve prior art, the present invention proposes the satellite Temp. control method that a kind of quick response multi-track adapts to, especially be applicable to controlling the thermal design under Satellite attitude condition.
The present invention is achieved by the following technical solutions.
According to an aspect of the present invention, provide the satellite Temp. control method that a kind of quick response multi-track adapts to, comprise the steps:
-thermal design is carried out to the platform cabin of satellite:
Heat conduction and radiant interchange in strengthening cabin, make uniform distribution of temperature field in cabin;
Adopt compensation electric heater to carry out heat compensation to platform cabin, and then adjust whole star temperature levels;
The opaco of the satellite side plate 3 in platform cabin as main heating panel, the outside face spray-coated white paint thermal control coating of opaco; Other platforms except satellite side plate 3 opaco surfaces be clad multilayer insulation assembly out of my cabin; To the star external member spray-coated white paint thermal control coating in platform cabin.
Preferably, in described strengthening cabin heat conduction and radiant interchange by following any one or appoint various ways to realize:
-on the satellite platform la m 1 and/or satellite platform base plate 2 in platform cabin, heat pipe network is set;
-to the heat conduction of unit contact-enhancing, between the instrument and dashboard of inside, platform cabin, attachment face is encased inside RKTL-DRZ-1 heat-conducting silicone grease;
-inside face spraying high emissivity thermal control coating in platform cabin, that is, the pitch-dark thermal control coating of inner structural members surface spraying SR107-E51 in platform cabin; Instrument cover face (except attachment face) one be aluminum alloy black anodizing thermal control coating, have the pitch-dark thermal control coating of spraying E51-M of requirement on electric performance.。
Preferably, described compensation electric heater is pasted on the inside face of the satellite platform la m 1 in platform cabin, satellite platform base plate 2 and/or satellite side plate 3.
Preferably, also comprise the steps:
-thermal design is carried out to the propulsion module 4 of satellite:
To the complete coated multilayer insulation assembly of the outside face of propulsion module 4;
To the coated multilayer insulation assembly of the cabin tank top plate of propulsion module 4.
According to a second aspect of the invention, provide the satellite Temp. control method that a kind of quick response multi-track adapts to, comprise the steps:
-thermal design is carried out to the propulsion module 4 of satellite:
To the complete coated multilayer insulation assembly of the outside face of propulsion module 4;
To the coated multilayer insulation assembly of the cabin tank top plate of propulsion module 4.
The satellite Temp. control method that quick response multi-track provided by the invention adapts to, adopts in heat pipe network, contact-enhancing heat conduction, star and sprays heat conduction and radiant interchange in the measure strengthening stars such as high emissivity thermal control coating, make uniform distribution of temperature field in star; Compensation electric heater is adopted to carry out heat compensation to satellite; In the opaco outside face spray-coated white paint of satellite, as main heat delivery surface, other celestial body outside face outer cladding multilayer insulation assemblies; Star external member spray-coated white paint thermal control coating; The equal independent design of propulsion module and platform cabin, can carry out subdivision thermal design and assembling; Propulsion module is independent design, out of my cabin complete coated multilayer, the coated multilayer of cabin tank top plate, and last and platform cabin is assembled into whole star.
Whole star Direct to the sun pattern is adopted, the thermal design demand under satellite adopts above-mentioned Temp. control method to meet sun-synchronous orbit and inclined plane condition under inclined plane condition.
Compared with prior art, the present invention has following beneficial effect:
(1) adopt the Temp. control method that response multi-track fast adapts to, by hot computational analysis comparison, the operating mode of thermal balance test can be reduced until cancel thermal balance test, reach the lead time shortening whole star and the object reducing research fund;
(2) adopt the Temp. control method that response multi-track fast adapts to, batch type production is realized for satellite and provides thermal design basis; Section independent thermal design in each cabin plays central role for satellite rapid Design composite assembly, and wherein platform cabin section can adopt interchangeable heat method of designing, and all the other cabin sections can be independent Thermal design.
(3) present invention accomplishes simplicity of design, lead time fast speed designing requirement, solve the thermal design problem of satellite under multi-track condition, good reliability, flexible design simultaneously.
(4) the present invention is by machine, heat, electrical integrated design, adopts above-mentioned Temp. control method to reach the heat control requirement of whole star under realizing sun-synchronous orbit and inclined plane condition.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is the configuration schematic diagram of the satellite of the Temp. control method adopting response multi-track fast to adapt to;
In figure: 1 is platform la m, 2 is satellite platform base plate, and 3 is satellite side plate, and 4 is propulsion module.
Detailed description of the invention
Below embodiments of the invention are elaborated: the present embodiment is implemented under premised on technical solution of the present invention, give detailed embodiment and concrete operating process.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, can also make some distortion and improvement, these all belong to protection scope of the present invention.
Present embodiments provide the satellite Temp. control method that a kind of quick response multi-track adapts to, comprise following any one or appoint multiple step:
-thermal design is carried out to the platform cabin of satellite:
Heat conduction and radiant interchange in strengthening cabin, make uniform distribution of temperature field in cabin;
Compensation electric heater is adopted to carry out heat compensation to platform cabin;
The opaco of the satellite side plate 3 in platform cabin as main heating panel, the outside face spray-coated white paint thermal control coating of opaco; Other platforms except satellite side plate 3 opaco surfaces be clad multilayer insulation assembly out of my cabin; To the star external member spray-coated white paint thermal control coating in platform cabin.
-thermal design is carried out to the propulsion module 4 of satellite:
To the complete coated multilayer insulation assembly of the outside face of propulsion module 4;
To the coated multilayer insulation assembly of the cabin tank top plate of propulsion module 4.
Further, in described strengthening cabin heat conduction and radiant interchange by following any one or appoint various ways to realize:
-on the satellite platform la m 1 and/or satellite platform base plate 2 in platform cabin, heat pipe network is set;
-to the heat conduction of unit contact-enhancing, between instrument and dashboard, attachment face is encased inside RKTL-DRZ-1 heat-conducting silicone grease;
-inside face spraying high emissivity thermal control coating in platform cabin, that is, the pitch-dark thermal control coating of inner structural members surface spraying SR107-E51 in platform cabin; Instrument cover face (except attachment face) one be aluminum alloy black anodizing thermal control coating, have the pitch-dark thermal control coating of spraying E51-M of requirement on electric performance.。
Further, described compensation electric heater is pasted on the inside face of the satellite platform la m 1 in platform cabin, satellite platform base plate 2 and/or satellite side plate 3.
Below in conjunction with accompanying drawing, the present embodiment is described in detail.
As shown in Figure 1:
(1) thermal design is carried out to platform cabin:
Satellite platform la m 1 and satellite platform base plate 2 adopting heat pipe network, to spraying heat conduction and radiant interchange in the measure strengthening stars such as high emissivity thermal control coating in the heat conduction of unit contact-enhancing, star, making uniform distribution of temperature field in star.
Satellite platform la m 1, satellite platform base plate 2 and satellite side plate 3 inside face are pasted compensation electric heater heat compensation is carried out to satellite.
The opaco of satellite side plate 3 is main heat delivery surface, its outside face spray-coated white paint thermal control coating, the coated multilayer insulation assembly of side plate outside face of the non-heat delivery surface of satellite side plate 3; Star external member spray-coated white paint thermal control coating.
(2) thermal design is carried out to propulsion module:
Propulsion module 4 and platform cabin are independent design, can carry out subdivision design and assembling.
Propulsion module 4 is independent design, out of my cabin complete coated multilayer insulation assembly, the coated multilayer insulation assembly of cabin tank top plate.
Whole star Direct to the sun pattern is adopted, the thermal design demand under satellite adopts above-mentioned Temp. control method to meet sun-synchronous orbit and inclined plane condition under inclined plane condition.
In the present embodiment:
Adopt in heat pipe network, contact-enhancing heat conduction, star and spray heat conduction and radiant interchange in the measure strengthening stars such as high emissivity thermal control coating, make uniform distribution of temperature field in star.
Compensation electric heater is adopted to carry out heat compensation to satellite.
The opaco of satellite side plate is main heat delivery surface, other celestial body outside face outer cladding multilayer insulation assemblies; Star external member spray-coated white paint thermal control coating.
Propulsion module and platform cabin are independent design, can carry out subdivision design and assembling.
The opaco of satellite side plate as main heat delivery surface, opaco outside face spray-coated white paint.
Propulsion module is independent design, out of my cabin complete coated multilayer, the coated multilayer of cabin tank top plate.
The Temp. control method that the quick response multi-track that the present embodiment provides adapts to, has effective, that comformability good, enforcement is convenient in thermal control measure feature.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (5)
1. a satellite Temp. control method for response multi-track adaptation fast, is characterized in that, comprise the steps:
-thermal design is carried out to the platform cabin of satellite:
Heat conduction and radiant interchange in strengthening cabin, make uniform distribution of temperature field in cabin;
Compensation electric heater is adopted to carry out heat compensation to platform cabin;
The opaco of the satellite side plate (3) in platform cabin as main heating panel, the outside face spray-coated white paint thermal control coating of opaco; Other platforms except satellite side plate (3) opaco surfaces be clad multilayer insulation assembly out of my cabin; The star external member spray-coated white paint thermal control coating in described platform cabin.
2. the satellite Temp. control method that adapts to of quick response multi-track according to claim 1, is characterized in that, in described strengthening cabin heat conduction and radiant interchange by following any one or appoint various ways to realize:
-on the satellite platform la m (1) and/or satellite platform base plate (2) in platform cabin, heat pipe network is set;
-to the heat conduction of unit contact-enhancing, that is, between the instrument and dashboard of inside, platform cabin, attachment face is encased inside RKTL-DRZ-1 heat-conducting silicone grease;
-inside face spraying high emissivity thermal control coating in platform cabin, that is, the pitch-dark thermal control coating of inner structural members surface spraying SR107-E51 in platform cabin; Except attachment face, the instrument cover face of inside, platform cabin adopts aluminum alloy black anodizing thermal control coating; The pitch-dark thermal control coating of E51-M is then sprayed for there being requirement on electric performance instrument cover face.
3. the satellite Temp. control method of quick response multi-track adaptation according to claim 1, it is characterized in that, described compensation electric heater is pasted on the inside face of the satellite platform la m (1) in platform cabin, satellite platform base plate (2) and/or satellite side plate (3).
4. the satellite Temp. control method of quick response multi-track adaptation according to any one of claim 1 to 3, is characterized in that, also comprise the steps:
-thermal design is carried out to the propulsion module (4) of satellite:
To the complete coated multilayer insulation assembly of the outside face of propulsion module (4);
To the coated multilayer insulation assembly of the cabin tank top plate of propulsion module (4).
5. a satellite Temp. control method for response multi-track adaptation fast, is characterized in that, comprise the steps:
-thermal design is carried out to the propulsion module (4) of satellite:
To the complete coated multilayer insulation assembly of the outside face of propulsion module (4);
To the coated multilayer insulation assembly of the cabin tank top plate of propulsion module (4).
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105775167A (en) * | 2016-04-21 | 2016-07-20 | 西安交通大学 | Satellite structure realizing convection heat exchange on basis of flexible air bag |
| CN106467176A (en) * | 2016-09-08 | 2017-03-01 | 上海卫星工程研究所 | The temp. control method in satellite booster cabin |
| CN109032203A (en) * | 2018-07-10 | 2018-12-18 | 北京空间飞行器总体设计部 | A kind of intelligent independent heat control system |
| CN109344512A (en) * | 2018-10-09 | 2019-02-15 | 中国人民解放军国防科技大学 | Thermal control structure of flying satellite and processing method |
| CN110143294A (en) * | 2019-04-11 | 2019-08-20 | 上海卫星工程研究所 | The full posture aircraft thermal design structure of Star Simulator |
| CN111891407A (en) * | 2020-07-21 | 2020-11-06 | 上海卫星工程研究所 | Temperature equalization control device and control method under unbalanced external heat flow condition |
| CN112034873A (en) * | 2020-09-02 | 2020-12-04 | 中国科学院微小卫星创新研究院 | MEO navigation satellite thermal control system |
| CN112455722A (en) * | 2020-12-07 | 2021-03-09 | 上海卫星工程研究所 | Integrated ultrastable structure system of double-supersatellite platform load cabin and thermal control method thereof |
| CN113120256A (en) * | 2019-12-30 | 2021-07-16 | 北京九天微星科技发展有限公司 | Low-orbit satellite with flat structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6478257B1 (en) * | 2001-06-15 | 2002-11-12 | Space Systems/Loral, Inc. | Phase change material thermal control for electric propulsion |
| JP2003291900A (en) * | 2002-04-05 | 2003-10-15 | Mitsubishi Electric Corp | Heat control device for artificial satellite |
| CN102514730A (en) * | 2011-12-21 | 2012-06-27 | 哈尔滨工业大学 | Electromechanical and thermal integrated satellite structure |
| CN103010487A (en) * | 2012-10-17 | 2013-04-03 | 浙江大学 | Heat control device and heat control method of pico-satellite in isothermal design |
| CN105659752B (en) * | 2010-11-19 | 2013-10-23 | 北京空间飞行器总体设计部 | Without the heat control method of attitude satellite |
-
2015
- 2015-07-31 CN CN201510466005.8A patent/CN105035365A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6478257B1 (en) * | 2001-06-15 | 2002-11-12 | Space Systems/Loral, Inc. | Phase change material thermal control for electric propulsion |
| JP2003291900A (en) * | 2002-04-05 | 2003-10-15 | Mitsubishi Electric Corp | Heat control device for artificial satellite |
| CN105659752B (en) * | 2010-11-19 | 2013-10-23 | 北京空间飞行器总体设计部 | Without the heat control method of attitude satellite |
| CN102514730A (en) * | 2011-12-21 | 2012-06-27 | 哈尔滨工业大学 | Electromechanical and thermal integrated satellite structure |
| CN103010487A (en) * | 2012-10-17 | 2013-04-03 | 浙江大学 | Heat control device and heat control method of pico-satellite in isothermal design |
Non-Patent Citations (3)
| Title |
|---|
| 孔林: "快速响应空间小卫星热控系统设计及关键技术", 《红外与激光工程》 * |
| 易桦等: "无姿态控制微小卫星热设计方法", 《2011年小卫星技术交流会论文集》 * |
| 马伟等: "卫星系统热特性分析", 《航天器工程》 * |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105775167A (en) * | 2016-04-21 | 2016-07-20 | 西安交通大学 | Satellite structure realizing convection heat exchange on basis of flexible air bag |
| CN106467176A (en) * | 2016-09-08 | 2017-03-01 | 上海卫星工程研究所 | The temp. control method in satellite booster cabin |
| CN109032203A (en) * | 2018-07-10 | 2018-12-18 | 北京空间飞行器总体设计部 | A kind of intelligent independent heat control system |
| CN109344512A (en) * | 2018-10-09 | 2019-02-15 | 中国人民解放军国防科技大学 | Thermal control structure of flying satellite and processing method |
| CN109344512B (en) * | 2018-10-09 | 2022-11-11 | 中国人民解放军国防科技大学 | Thermal control structure of flying satellite and processing method |
| CN110143294A (en) * | 2019-04-11 | 2019-08-20 | 上海卫星工程研究所 | The full posture aircraft thermal design structure of Star Simulator |
| CN113120256A (en) * | 2019-12-30 | 2021-07-16 | 北京九天微星科技发展有限公司 | Low-orbit satellite with flat structure |
| CN111891407A (en) * | 2020-07-21 | 2020-11-06 | 上海卫星工程研究所 | Temperature equalization control device and control method under unbalanced external heat flow condition |
| CN112034873A (en) * | 2020-09-02 | 2020-12-04 | 中国科学院微小卫星创新研究院 | MEO navigation satellite thermal control system |
| CN112034873B (en) * | 2020-09-02 | 2024-04-30 | 中国科学院微小卫星创新研究院 | MEO navigation satellite thermal control system |
| CN112455722A (en) * | 2020-12-07 | 2021-03-09 | 上海卫星工程研究所 | Integrated ultrastable structure system of double-supersatellite platform load cabin and thermal control method thereof |
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Application publication date: 20151111 |