CN103448925A - High-precision temperature control device for star sensors for satellites - Google Patents
High-precision temperature control device for star sensors for satellites Download PDFInfo
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- CN103448925A CN103448925A CN2013103453704A CN201310345370A CN103448925A CN 103448925 A CN103448925 A CN 103448925A CN 2013103453704 A CN2013103453704 A CN 2013103453704A CN 201310345370 A CN201310345370 A CN 201310345370A CN 103448925 A CN103448925 A CN 103448925A
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Abstract
The invention discloses a high-precision temperature control device for star sensors for satellites. The high-precision temperature control device comprises a star sensor mounting rack, a star sensor, a thermistor, a heater, an outer-posted heating pipe, an independent cooling surface and a multi-layer insulation component. The star sensor, the thermistor and the heater are mounted on the star sensor mounting face of the star sensor mounting rack, the outer-posted heating pipe is connected between the star sensor mounting rack and the independent cooling surface, and the multi-layer insulation component wraps the star sensor mounting rack, the star sensor, the thermistor and the heater. Requirements of high-precision temperature control on the star sensor for the satellite are met, and the device has the advantages of high temperature control precision, fine reliability, flexible design and the like.
Description
Technical field
The present invention relates to the space vehicle temperature control system, be specifically related to star sensor high precision temperature control device for a kind of satellite.
Background technology
Star sensor is as Satellite attitude and orbit control system core parts, it is a kind of high-precision attitude sensitive measurement instrument, determine the attitude of spacecraft by the fixed star of surveying diverse location, survey precision can reach a second class precision, becomes high-precision attitude sensing unit indispensable on the spacecrafts such as satellite, space station.
The temperature levels of star sensor has material impact to survey precision.Star sensor generally is arranged on outside star, and thermal environment is comparatively severe.The heat insulation installation of shade and head, the star sensor shade coats multilayer, subregion spray-coated white paint.
General low orbit satellite is by star sensor head temperature scope-40 to+30 ℃, and high rail Satellite sensor temperature accuracy is higher, requires 20 ± 3 ℃ of the range of temperaturess of the quick attachment face of star.Need to be in conjunction with the outer hot-fluid situation of the quick device of star, thermal control design and computational analysis are carried out in installation site.
Summary of the invention
For defect of the prior art, control requirement for the high-precision temperature that solves star sensor in above-mentioned high rail satellite, the object of the present invention is to provide a kind of simple to operate, attemperating unit that reliability is high.Utilize the present invention, not only reached the accuracy requirement that latter stage, surplus was measured, and package unit and method implement simple, reliability is high.
According to star sensor high precision temperature control device for satellite provided by the invention, comprise the quick mounting bracket of star, star sensor, thermally dependent resistor, temperature booster, outer subsides heat pipe, independent heat delivery surface, multilayer insulation assembly, wherein, star sensor, thermally dependent resistor, temperature booster are installed on the quick attachment face of star of the quick mounting bracket of star, outer subsides heat pipe is connected between the quick mounting bracket of star and independent heat delivery surface, and the multilayer insulation assembly coats the quick mounting bracket of star, star sensor, thermally dependent resistor, temperature booster.
Preferably, thermally dependent resistor is the temperature control thermally dependent resistor.
Preferably, the multilayer insulation assembly adopts multiunit low temperature multiple-structure.
Preferably, the multilayer insulation assembly adopts the low temperature multiple-structure of Unit 10.
Preferably, independent heat delivery surface is the OSR heat delivery surface.
Preferably, the quantity of the quick attachment face of star of the quick mounting bracket of star is 3, is provided with 1 star sensor, 1 thermally dependent resistor, 1 road temperature booster on the quick attachment face of each star.
Preferably, the integrated aluminum-base silicon carbide support of the quick mounting bracket of star.
Preferably, temperature booster adopts stored program control system, and threshold value is 17-23 ℃.
Preferably, a crossbeam that connects the quick attachment face of several stars is arranged on the quick mounting bracket of star, outer subsides heat pipe is installed on the surface of this crossbeam.
Preferably, outer subsides heat pipe is the diplopore heat pipe.
Compared with prior art, the present invention has following beneficial effect:
(1) device simplicity of design, flexible, take the thermal control measures such as heat pipe, temperature booster, thermally dependent resistor, multilayer insulation assembly, independent heat delivery surface, can meet the high-precision temperature requirement of star sensor;
(2) device reliability, parts comprise outer subsides heat pipe, temperature booster, thermally dependent resistor and multilayer insulation assembly and independent heat delivery surface, there be not startup, termination and the Problem of Failure of system in package unit.
The accompanying drawing explanation
By reading the detailed description of non-limiting example being done with reference to the following drawings, it is more obvious that other features, objects and advantages of the present invention will become:
Fig. 1 is star sensor high precision temperature control device schematic diagram for satellite provided by the invention;
Fig. 2 is star sensor high precision temperature control assembly heater interconnecting wiring diagram for satellite provided by the invention;
Fig. 3 is the structured flowchart of satellite provided by the invention with star sensor high precision temperature control device.
In figure:
The 1-thermally dependent resistor;
2-multilayer insulation assembly;
The 3-temperature booster;
4-pastes heat pipe outward;
5-independence heat delivery surface;
The quick temperature booster A of 61-star;
The quick temperature booster B of 62-star;
The quick temperature booster C of 63-star;
The quick mounting bracket of 7-star.
The specific embodiment
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art further to understand the present invention, but not limit in any form the present invention.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.
Fig. 1 is the structural representation of satellite provided by the invention with star sensor high precision temperature control device, described satellite comprises with star sensor high precision temperature control device: the quick mounting bracket of star, star sensor, thermally dependent resistor, temperature booster, outer subsides heat pipe, independent heat delivery surface, multilayer insulation assembly, wherein, star sensor, thermally dependent resistor, temperature booster are installed on the quick attachment face of star of the quick mounting bracket of star, outer subsides heat pipe is connected between the quick mounting bracket of star and independent heat delivery surface, and the multilayer insulation assembly coats the quick mounting bracket of star, star sensor, thermally dependent resistor, temperature booster.Further, the interconnecting wiring diagram that Fig. 2 is temperature booster.
The quick mounting bracket of star adopts integrated aluminum-base silicon carbide support, is processed with 3 planes on the quick mounting bracket of star as three quick attachment faces of star, corresponding star sensor A, B, the C that 3 different directions are installed.A crossbeam that connects three planes is arranged on the quick mounting bracket of integrated star, as the installation surface of outer subsides heat pipe, be used for transferring heat.Independent heat delivery surface is arranged in northern plate, and 3 road temperature boosters are arranged on respectively three quick attachment faces of star of the quick mounting bracket of integrated star.Temperature booster adopts stored program control system, and threshold value is 17-23 ℃.The quick temperature curve of star that application the present invention adopts the quick high precision temperature control device of star to calculate, the quick index request that all meets 20 ± 3 ℃ of 3 stars in different directions.
Above specific embodiments of the invention are described.It will be appreciated that, the present invention is not limited to above-mentioned specific implementations, and those skilled in the art can make various distortion or modification within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (10)
1. star sensor high precision temperature control device for a satellite, it is characterized in that, comprise the quick mounting bracket of star, star sensor, thermally dependent resistor, temperature booster, outer subsides heat pipe, independent heat delivery surface, multilayer insulation assembly, wherein, star sensor, thermally dependent resistor, temperature booster are installed on the quick attachment face of star of the quick mounting bracket of star, outer subsides heat pipe is connected between the quick mounting bracket of star and independent heat delivery surface, and the multilayer insulation assembly coats the quick mounting bracket of star, star sensor, thermally dependent resistor, temperature booster.
2. star sensor high precision temperature control device for satellite according to claim 1, is characterized in that, thermally dependent resistor is the temperature control thermally dependent resistor.
3. star sensor high precision temperature control device for satellite according to claim 1, is characterized in that, the multilayer insulation assembly adopts multiunit low temperature multiple-structure.
4. star sensor high precision temperature control device for satellite according to claim 3, is characterized in that, the multilayer insulation assembly adopts the low temperature multiple-structure of Unit 10.
5. star sensor high precision temperature control device for satellite according to claim 1, is characterized in that, independent heat delivery surface is the OSR heat delivery surface.
6. star sensor high precision temperature control device for satellite according to claim 1, is characterized in that, the quantity of the quick attachment face of star of the quick mounting bracket of star is 3, is provided with 1 star sensor, 1 thermally dependent resistor, 1 road temperature booster on the quick attachment face of each star.
7. star sensor high precision temperature control device for satellite according to claim 1, is characterized in that the integrated aluminum-base silicon carbide support of the quick mounting bracket of star.
8. star sensor high precision temperature control device for satellite according to claim 1, is characterized in that, temperature booster adopts stored program control system, and threshold value is 17-23 ℃.
9. star sensor high precision temperature control device for satellite according to claim 1, is characterized in that, a crossbeam that connects the quick attachment face of several stars is arranged on the quick mounting bracket of star, and outer subsides heat pipe is installed on the surface of this crossbeam.
10. star sensor high precision temperature control device for satellite according to claim 1, is characterized in that, outer subsides heat pipe is the diplopore heat pipe.
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| CN2013103453704A CN103448925A (en) | 2013-08-08 | 2013-08-08 | High-precision temperature control device for star sensors for satellites |
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| CN2013103453704A CN103448925A (en) | 2013-08-08 | 2013-08-08 | High-precision temperature control device for star sensors for satellites |
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Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104102245A (en) * | 2014-05-26 | 2014-10-15 | 航天东方红卫星有限公司 | Thermal control device used for improving satellite temperature control precision and thermal control method |
| CN104125004A (en) * | 2014-07-07 | 2014-10-29 | 江苏中寰卫星导航通信有限公司 | Satellite communication box |
| CN104369876A (en) * | 2014-10-31 | 2015-02-25 | 上海卫星工程研究所 | Low-temperature differential thermal control device for infrared horizon sensors of orbit transfer vehicle |
| CN104443441A (en) * | 2014-10-31 | 2015-03-25 | 上海卫星工程研究所 | Star sensor sub-low temperature independent thermal control device of orbit transfer vehicle |
| CN104743138A (en) * | 2015-02-13 | 2015-07-01 | 上海卫星工程研究所 | High-precision micro-deformation attitude control instrument installing structure for spaceflight |
| CN106114912A (en) * | 2016-08-12 | 2016-11-16 | 上海卫星工程研究所 | GEO track Rotating Platform for High Precision Star Sensor high stable in-orbit points to ensuring method |
| CN106292771A (en) * | 2016-08-04 | 2017-01-04 | 上海航天控制技术研究所 | A kind of star sensor temperature field measurement and control devices and methods therefor |
| CN108601298A (en) * | 2018-04-23 | 2018-09-28 | 北京空间飞行器总体设计部 | A kind of integrated General heat dissipation device of spacecraft star sensor |
| CN108791958A (en) * | 2018-06-15 | 2018-11-13 | 上海卫星工程研究所 | Star sensor illumination adapts to heat control device entirely |
| CN108791959A (en) * | 2018-06-15 | 2018-11-13 | 上海卫星工程研究所 | Star sensor lightweight thermal controls apparatus based on structure mounting plate |
| CN108791961A (en) * | 2018-06-14 | 2018-11-13 | 上海卫星工程研究所 | A kind of GEO satellite large span heat pipe configuration |
| CN108820259A (en) * | 2018-06-25 | 2018-11-16 | 上海卫星工程研究所 | A kind of whole temperature barrier being adapted to the outer rotating mechanism multi-dimensional movement of star |
| CN108860664A (en) * | 2018-06-20 | 2018-11-23 | 上海卫星工程研究所 | The novel thermal controls apparatus of spatial flexible mechanism |
| CN109141472A (en) * | 2018-08-13 | 2019-01-04 | 上海航天控制技术研究所 | For assessing the sight star test device and method of star sensor thermal stability |
| CN105979158B (en) * | 2016-07-14 | 2019-01-15 | 上海航天控制技术研究所 | A kind of star sensor focal plane component |
| CN111124009A (en) * | 2019-12-26 | 2020-05-08 | 兰州空间技术物理研究所 | Autonomous temperature control system for in-orbit operation of deep space energy particle detector |
| CN111572819A (en) * | 2020-04-30 | 2020-08-25 | 上海卫星工程研究所 | Installing support suitable for spacecraft integration high stability bull star sensor |
| CN113879568A (en) * | 2021-09-06 | 2022-01-04 | 中国科学院微小卫星创新研究院 | Pluggable satellite thermal control system and method |
| CN113998157A (en) * | 2021-10-11 | 2022-02-01 | 上海卫星装备研究所 | Spacecraft mechanical-thermal integrated multi-equipment mounting bracket and manufacturing method thereof |
| CN114408221A (en) * | 2022-01-19 | 2022-04-29 | 上海卫星工程研究所 | Satellite-used satellite-sensitive temperature control system |
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Cited By (29)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104102245B (en) * | 2014-05-26 | 2016-03-30 | 航天东方红卫星有限公司 | A kind of thermal controls apparatus and thermal control method improving satellite temperature-controlled precision |
| CN104102245A (en) * | 2014-05-26 | 2014-10-15 | 航天东方红卫星有限公司 | Thermal control device used for improving satellite temperature control precision and thermal control method |
| CN104125004A (en) * | 2014-07-07 | 2014-10-29 | 江苏中寰卫星导航通信有限公司 | Satellite communication box |
| CN104369876A (en) * | 2014-10-31 | 2015-02-25 | 上海卫星工程研究所 | Low-temperature differential thermal control device for infrared horizon sensors of orbit transfer vehicle |
| CN104443441A (en) * | 2014-10-31 | 2015-03-25 | 上海卫星工程研究所 | Star sensor sub-low temperature independent thermal control device of orbit transfer vehicle |
| CN104443441B (en) * | 2014-10-31 | 2016-07-27 | 上海卫星工程研究所 | Orbit transfer vehicle star sensor the is on the low side independent thermal controls apparatus of temperature |
| CN104743138B (en) * | 2015-02-13 | 2017-01-25 | 上海卫星工程研究所 | High-precision micro-deformation attitude control instrument installing structure for spaceflight |
| CN104743138A (en) * | 2015-02-13 | 2015-07-01 | 上海卫星工程研究所 | High-precision micro-deformation attitude control instrument installing structure for spaceflight |
| CN105979158B (en) * | 2016-07-14 | 2019-01-15 | 上海航天控制技术研究所 | A kind of star sensor focal plane component |
| CN106292771A (en) * | 2016-08-04 | 2017-01-04 | 上海航天控制技术研究所 | A kind of star sensor temperature field measurement and control devices and methods therefor |
| CN106292771B (en) * | 2016-08-04 | 2019-02-12 | 上海航天控制技术研究所 | A kind of star sensor temperature field measurement and control device and its method |
| CN106114912A (en) * | 2016-08-12 | 2016-11-16 | 上海卫星工程研究所 | GEO track Rotating Platform for High Precision Star Sensor high stable in-orbit points to ensuring method |
| CN108601298A (en) * | 2018-04-23 | 2018-09-28 | 北京空间飞行器总体设计部 | A kind of integrated General heat dissipation device of spacecraft star sensor |
| CN108791961A (en) * | 2018-06-14 | 2018-11-13 | 上海卫星工程研究所 | A kind of GEO satellite large span heat pipe configuration |
| CN108791958A (en) * | 2018-06-15 | 2018-11-13 | 上海卫星工程研究所 | Star sensor illumination adapts to heat control device entirely |
| CN108791959A (en) * | 2018-06-15 | 2018-11-13 | 上海卫星工程研究所 | Star sensor lightweight thermal controls apparatus based on structure mounting plate |
| CN108860664A (en) * | 2018-06-20 | 2018-11-23 | 上海卫星工程研究所 | The novel thermal controls apparatus of spatial flexible mechanism |
| CN108860664B (en) * | 2018-06-20 | 2020-07-14 | 上海卫星工程研究所 | Novel thermal control device for space flexible mechanism |
| CN108820259A (en) * | 2018-06-25 | 2018-11-16 | 上海卫星工程研究所 | A kind of whole temperature barrier being adapted to the outer rotating mechanism multi-dimensional movement of star |
| CN109141472A (en) * | 2018-08-13 | 2019-01-04 | 上海航天控制技术研究所 | For assessing the sight star test device and method of star sensor thermal stability |
| CN109141472B (en) * | 2018-08-13 | 2020-08-28 | 上海航天控制技术研究所 | Star observation testing device and method for evaluating thermal stability of star sensor |
| CN111124009A (en) * | 2019-12-26 | 2020-05-08 | 兰州空间技术物理研究所 | Autonomous temperature control system for in-orbit operation of deep space energy particle detector |
| CN111572819A (en) * | 2020-04-30 | 2020-08-25 | 上海卫星工程研究所 | Installing support suitable for spacecraft integration high stability bull star sensor |
| CN113879568A (en) * | 2021-09-06 | 2022-01-04 | 中国科学院微小卫星创新研究院 | Pluggable satellite thermal control system and method |
| CN113879568B (en) * | 2021-09-06 | 2022-07-12 | 中国科学院微小卫星创新研究院 | Pluggable satellite thermal control system and method |
| CN113998157A (en) * | 2021-10-11 | 2022-02-01 | 上海卫星装备研究所 | Spacecraft mechanical-thermal integrated multi-equipment mounting bracket and manufacturing method thereof |
| CN113998157B (en) * | 2021-10-11 | 2023-08-11 | 上海卫星装备研究所 | Spacecraft mechanical-thermal integrated multi-equipment mounting bracket and manufacturing method thereof |
| CN114408221A (en) * | 2022-01-19 | 2022-04-29 | 上海卫星工程研究所 | Satellite-used satellite-sensitive temperature control system |
| CN114408221B (en) * | 2022-01-19 | 2024-05-07 | 上海卫星工程研究所 | Satellite-sensitive temperature control system for satellite |
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Application publication date: 20131218 |