CN103434659A - High-temperature-uniformity heat radiator for navigation satellite - Google Patents
High-temperature-uniformity heat radiator for navigation satellite Download PDFInfo
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- CN103434659A CN103434659A CN201310177578XA CN201310177578A CN103434659A CN 103434659 A CN103434659 A CN 103434659A CN 201310177578X A CN201310177578X A CN 201310177578XA CN 201310177578 A CN201310177578 A CN 201310177578A CN 103434659 A CN103434659 A CN 103434659A
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Abstract
The invention discloses a high-temperature-uniformity heat radiator for a navigation satellite and belongs to the technical field of spacecraft heat control. A temperature radiator comprises a honeycomb plate, more than two U-shaped heat tubes, heaters and peripheral equipment, wherein the peripheral equipment is a rubidium clock; the straight tube section of each U-shaped heat tube consists of a tube body and a fin; the cross section of each U-shaped heat tube is T-shaped; the U-shaped section of each U-shaped heat tube only comprises the tube body of the corresponding straight tube section; the U-shaped heat tubes are embedded into the honeycomb plate; the upper surfaces of the fins and the lower surfaces of the tube bodies are respectively attached to the upper and lower inner surfaces of the honeycomb plate; the U-shaped heat tubes are nested with each other, so that the straight tube sections of the U-shaped heat tubes in the honeycomb plate are adjacently arranged; the surface of the honeycomb plate corresponding to the adjacent arrangement area of the straight tube sections serves as an installation area of the rubidium clock; the heaters are uniformly arranged on the tube bodies of the straight tube sections of the U-shaped heat tubes and are used for providing compensation heating amount for the heat radiator. The efficient heat transfer, heat dissipation and heat balance of the temperature radiator can be realized, and requirements on the environment temperature control accuracy of the rubidium atomic clock are met.
Description
Technical field
Invention relates to a kind of exciter, is specifically related to a kind of navigation satellite high-temperature homogeneity heat radiator, belongs to spacecraft Evolution of Thermal Control Technique field.
Background technology
Satellite atomic clock need to be operated under the temperature environment of a high temperature-controlled precision and high temperature control degree of stability usually.Take navigation satellite as example, require the ambient temperature control accuracy of rubidium atomic clock to be better than ± 0.3 ℃, day degree of stability control be better than ± 1 ℃.For this reason, navigation satellite is that rubidium atomic clock equipment is designed with an independently temperature control cludy.
Rubidium atomic clock power consumption used when work will all be converted to used heat, need to it be fallen apart outside star by a stable hot delivering path, to maintain the rubidium clock working environment in a stable range of temperatures.
As unique heat radiation and the heat balance approach of rubidium atomic clock cludy, the thermal design of rubidium atomic clock exciter is one of key factor of rubidium atomic clock operating ambient temperature control.
At present, the orthogonal heat pipes network that general spacecraft adopts carries out the High Efficiency Thermal transmission, as shown in Figure 1: two parallel heat pipes 1 are embedded in parallel to each other bending block 2 inside and fit with the inside face up and down of bending block 2, for evening up the temperature of exciter along its axis direction, and the used heat that will be arranged on equipment generation on the plate of cabin is transferred on the outer heat delivery surface of star, balance heat pipe 3 is arranged on the upper surface of bending block with the direction perpendicular to parallel heat pipes 1, for evening up the thermal load of temperature between parallel heat pipes 11 carrying of every parallel heat pipes of balance, avoid local heat pipe temperature drift, improve the temperature homogeneity of opposite heat tube network area and the utilization ratio of heat delivery surface.Thermal resistance between parallel heat pipes 1 and balance heat pipe 3 is less, and the temperature difference between parallel heat pipes 1 is just less, and the exciter temperature is just more even accordingly.But between parallel heat pipes 1 and balance heat pipe 3, the transmission of heat by contact thermal resistance is constant existence, and then the transmission efficiency and the temperature homogeneity that affect the heat pipe network reach higher target.
Summary of the invention
In view of this, the invention provides a kind of navigation satellite high-temperature homogeneity heat radiator, can realize that High Efficiency Thermal transmission, the hot type of temperature radiation device falls apart and heat balance.
A kind of navigation satellite high-temperature homogeneity heat radiator, comprise bending block, U-shaped heat pipe and temperature booster more than two, and external equipment is rubidium clock; Wherein, the straight length of U-shaped heat pipe is to consist of body and fin, and its cross-sectional plane is the T font, and U-shaped section part only comprises the body portion of straight length;
U-shaped heat pipe is embedded in bending block inside, the upper surface of fin and the lower surface of body are fitted with the inside face up and down of bending block respectively, nested against one another between U-shaped heat pipe, make a straight length in the inner U-shaped heat pipe of bending block form each other adjacent arrangement, bending block surface corresponding to the adjacent arrange regional of straight length is as the installation region of rubidium clock, temperature booster is evenly arranged on the body of U-shaped heat pipe straight length, for heat radiator affords redress, adds heat.
Further, in bending block, the distance between adjacent U-shaped heat pipe straight length is 5～10mm;
Further, temperature booster divides main part of temperature booster and backup temperature booster, and main part of temperature booster adopts upper and lower stack-design structure with the backup temperature booster, when active and standby part of switching occurs, can keep temperature booster to produce heat source position and not change, keep the temperature controlled stability of rubidium clock exciter.
Beneficial effect:
1, the present invention adopts U-shaped heat pipe to replace the orthogonal heat pipes network, and a U-shaped heat pipe can replace two pre-buried heat pipes and can play the effect of balance heat pipe in the orthogonal heat pipes network.Because U-shaped heat pipe itself has good isothermal performance and heat transfer potential, thereby can effectively reduce the impact of the thermal contact resistance between parallel heat pipes and balance heat pipe on whole heat pipe network temperature homogeneity in the orthogonal heat pipes network.The higher temperature homogeneity that keeps whole rubidium clock exciter zone, the radiating efficiency of raising rubidium clock exciter.
2, owing to having cancelled the balance heat pipe in heat radiator, reduce the weight of heat radiator, simplified processing technology simultaneously.
3, through navigation satellite flight validation in-orbit, rubidium clock heat radiator temperature homogeneity is better than 0.2 ℃, and meets rubidium atomic clock sky degree of stability and control the be better than ± technical requirements of 1 ℃.Its performance is better than the orthogonal heat pipes network.
The accompanying drawing explanation
The perspective view that Fig. 1 is heat pipe radiator in prior art;
The birds-eye view that Fig. 2 is heat pipe radiator in prior art;
The perspective view that Fig. 3 is heat radiator of the present invention;
The birds-eye view that Fig. 4 is heat radiator of the present invention.
Wherein, 1-parallel heat pipes, 2-bending block, 3-balance heat pipe, 4-U type heat pipe, 5-rubidium clock, 6-installation region.
The specific embodiment
Below in conjunction with the accompanying drawing embodiment that develops simultaneously, describe the present invention.
As shown in accompanying drawing 3 and 4, the invention provides a kind of navigation satellite high-temperature homogeneity heat radiator, comprise bending block 2, four U-shaped heat pipes 4 and temperature boosters, external equipment is rubidium clock 5; The straight length of the U-shaped heat pipe 4 of each root is that body and fin form, and its cross-sectional plane is the T font, and U-shaped section part only comprises the body portion of straight length; The flow development length of four U-shaped heat pipes 4 and U-shaped section part radian are not of uniform size, and purpose is to make the U-shaped heat pipe 4 can be after bending block 2 is inner pre-buried, and the straight length of four U-shaped heat pipes 4 can arrangement adjacent one another are;
Four U-shaped heat pipes 4 are embedded in bending block inside, the upper surface of fin and the lower surface of body are fitted with the inside face up and down of bending block respectively, nested against one another between U-shaped heat pipe 4, make a straight length in the inner U-shaped heat pipe 4 of bending block 2 form each other adjacent arrangement, bending block surface corresponding to the adjacent arrange regional of straight length is as the installation region 6 of rubidium clock 5; Temperature booster is evenly arranged on the body of U-shaped heat pipe 4 straight lengths, for heat radiator affords redress, adds heat.
Distance in bending block between adjacent U-shaped heat pipe 4 straight lengths is 10mm;
Temperature booster divides main part of temperature booster and backup temperature booster, main part of temperature booster adopts upper and lower stack-design structure with the backup temperature booster, when active and standby part of switching occurs, can keep temperature booster to produce heat source position and not change, keep the temperature controlled stability of rubidium clock exciter.
In sum, these are only preferred embodiment of the present invention, be not intended to limit protection scope of the present invention.Within the spirit and principles in the present invention all, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.
Claims (3)
1. a navigation satellite high-temperature homogeneity heat radiator, is characterized in that, comprising: bending block, U-shaped heat pipe and temperature booster more than two, and external equipment is rubidium clock; Wherein, the straight length of U-shaped heat pipe is to consist of body and fin, and its cross-sectional plane is the T font, and U-shaped section part only comprises the body portion of straight length;
U-shaped heat pipe more than two is embedded in bending block inside, the upper surface of fin and the lower surface of body are fitted with the inside face up and down of bending block respectively, nested against one another between U-shaped heat pipe, make a straight length in the inner U-shaped heat pipe of bending block form each other adjacent arrangement, bending block surface corresponding to the adjacent arrange regional of straight length is as the installation region of rubidium clock, and temperature booster is evenly arranged on the body of U-shaped heat pipe straight length.
2. navigation satellite high-temperature homogeneity heat radiator as claimed in claim 1, is characterized in that in described bending block, the distance between adjacent U-shaped heat pipe straight length is 5～10mm.
3. navigation satellite high-temperature homogeneity heat radiator as claimed in claim 1 or 2, is characterized in that described temperature booster divides main part of temperature booster and backup temperature booster, and main part of temperature booster adopts upper and lower stack-design structure with the backup temperature booster.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310177578XA CN103434659A (en) | 2013-05-14 | 2013-05-14 | High-temperature-uniformity heat radiator for navigation satellite |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310177578XA CN103434659A (en) | 2013-05-14 | 2013-05-14 | High-temperature-uniformity heat radiator for navigation satellite |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104260904A (en) * | 2014-09-11 | 2015-01-07 | 上海卫星工程研究所 | Heat pipe pre-burying method with low contact thermal resistance |
| CN106304796A (en) * | 2016-09-29 | 2017-01-04 | 中国科学院西安光学精密机械研究所 | Multi-functional Compound Spacecraft electronics casing |
| 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 |
| CN109878764A (en) * | 2019-02-28 | 2019-06-14 | 上海微小卫星工程中心 | A kind of mechanical, electrical and heating integrated satellite structure plate |
| CN111806730A (en) * | 2020-06-02 | 2020-10-23 | 上海利正卫星应用技术有限公司 | Phase change radiator |
| CN113401369A (en) * | 2021-06-07 | 2021-09-17 | 长光卫星技术有限公司 | High-efficient expansion heat pipe radiation radiator |
| CN114084380A (en) * | 2021-09-08 | 2022-02-25 | 哈尔滨工业大学 | Inflatable expansion type flexible heat radiator for spacecraft |
| RU2807772C1 (en) * | 2023-03-14 | 2023-11-21 | Акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнёва" | Spacecraft instrument panel |
-
2013
- 2013-05-14 CN CN201310177578XA patent/CN103434659A/en active Pending
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104260904A (en) * | 2014-09-11 | 2015-01-07 | 上海卫星工程研究所 | Heat pipe pre-burying method with low contact thermal resistance |
| CN104260904B (en) * | 2014-09-11 | 2016-08-24 | 上海卫星工程研究所 | The heat pipe built-in process of low thermal contact resistance |
| CN106304796A (en) * | 2016-09-29 | 2017-01-04 | 中国科学院西安光学精密机械研究所 | Multi-functional Compound Spacecraft electronics casing |
| 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 |
| CN109878764A (en) * | 2019-02-28 | 2019-06-14 | 上海微小卫星工程中心 | A kind of mechanical, electrical and heating integrated satellite structure plate |
| CN111806730A (en) * | 2020-06-02 | 2020-10-23 | 上海利正卫星应用技术有限公司 | Phase change radiator |
| CN113401369A (en) * | 2021-06-07 | 2021-09-17 | 长光卫星技术有限公司 | High-efficient expansion heat pipe radiation radiator |
| CN114084380A (en) * | 2021-09-08 | 2022-02-25 | 哈尔滨工业大学 | Inflatable expansion type flexible heat radiator for spacecraft |
| RU2807772C1 (en) * | 2023-03-14 | 2023-11-21 | Акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнёва" | Spacecraft instrument panel |
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Application publication date: 20131211 |