CN101424862A - Thermal switch for heat control system of camera - Google Patents
Thermal switch for heat control system of camera Download PDFInfo
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- CN101424862A CN101424862A CNA2008100515549A CN200810051554A CN101424862A CN 101424862 A CN101424862 A CN 101424862A CN A2008100515549 A CNA2008100515549 A CN A2008100515549A CN 200810051554 A CN200810051554 A CN 200810051554A CN 101424862 A CN101424862 A CN 101424862A
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Abstract
The invention relates to a switch of a thermal control system for a temperature sensing device, in particular to a thermal switch of a thermal control system for a spatial camera. The thermal switch comprises a left heat conducting block, a right heat conducting block, a movable heat conducting block which can transversally move between the left heat conducting block and the right heat conducting block, a telescopic rod made of materials with the thermal expansion coefficient larger than that of the left heat conducting block, the right heat conducting block and the movable heat conducting block, and a spring. Both the left heat conducting block and the right heat conducting block are provided with blind holes with openings towards the movable heat conducting block; the telescopic rod and the left heat conducting block are arranged in the blind hole of the left heat conducting block in a sliding fit manner; and the spring is arranged in the blind hole of the right heat conducting block. The movable heat conducting block is achieved to be respectively in crossed contact with the left heat conducting block and the right heat conducting block to change a thermal conducting channel through the thermal expansion and the cold shrinkage of the telescopic rod. The thermal switch has the advantages of simple structure, high reliability and long service life, and can achieve the automatic temperature control function of the temperature sensing device.
Description
Technical field
The present invention relates to be applied to the heat control system switch of temperature sensor, particularly a kind of thermal control parts that can be used as variable heat dissipation channels such as space optical remote sensor CCD focal plane component.
Background technology
At present, space camera adopts CCD as sensitive detection parts more.But it is to responsive to temperature, and dark current and the thermonoise that conference increases the CCD device crossed in the too high and temperature fluctuation of temperature levels, causes signal to noise ratio (S/N ratio) to reduce, and influences picture quality.So guarantee that CCD focal plane subassembly (CFPA) is in lower temperature levels and less temperature fluctuation range is the target of CFPA thermal design.
Because the requirement of the residing space environment of camera and optics and physical construction, CFPA is installed in the narrow and small relatively closed environment.In order to reduce influencing each other between the camera each several part, the heat during CCD work will be discharged to space outerpace by heat dissipation channel.As rational heat dissipation path, CFPA is as thermal source, be positioned at the camera outside towards cold black radiant panel as heat sink, effective heat transfer link is set up in the centre.The mathematical description of this heat radiation approach as shown in Equation 1 because heat control system is in case determine that then entire thermal resistance R immobilizes on the heat dissipation path, the heat Q that produces during CCD work also is a definite value, if will guarantee the temperature T of CCD device
AConstant, then require as heat sink radiant panel temperature T
BKeep temperature-resistant.
T
A＝R·Q+T
B (1)
Because radiant panel is positioned at the camera outside, along with the camera attitude changes, when making radiant panel and be in the shade, the time and be subjected to the solar radiation effect, the variation of outer hot-fluid causes the radiant panel temperature variation, when being lower than setting value, the temperature of radiant panel can adopt the method for heating, holding temperature is constant, but when the temperature of radiant panel is higher than setting value, is difficult to guarantee the temperature stabilization of CFPA.
Summary of the invention
The objective of the invention is to propose a kind of thermal switch that is used for the space camera heat control system,, effectively guarantee the stability of space camera work to overcome the shortcoming of the difficult control of temperature of sensitive detection parts CCD focal plane component (CFPA) in the present space camera.
The present invention is used for the thermal switch of space camera heat control system, comprises left heat-conducting block (1), right heat-conducting block (3), the movable heat-conducting block (2) that can move to the left and right between left heat-conducting block (1) and right heat-conducting block (3), expansion link (4) and spring (6); Described left heat-conducting block (1) and right heat-conducting block (3) are equipped with the blind hole of opening to movable heat-conducting block (2), described expansion link (4) and left heat-conducting block (1) are in the left heat-conducting block of being arranged on of sliding fit (1) blind hole, on its two ends are connected at the bottom of left heat-conducting block (1) blind hole respectively and on the movable heat-conducting block (2); Described spring (6) is arranged in right heat-conducting block (3) blind hole, and its two ends are replaced respectively at the bottom of right heat-conducting block (3) blind hole and on the movable heat-conducting block (2);
Described expansion link (4) is made greater than the material of left and right heat-conducting block and movable heat-conducting block with coefficient of linear thermal expansion.
The using method and the principle of work of thermal switch of the present invention are:
The left and right heat-conducting block of thermal switch of the present invention is linked by heat pipe and two radiant panels that are arranged on the space camera both sides respectively, and movable heat-conducting block links by the CFPA of flexible heat pipe and space camera CCD.The heat that produces during CCD work, be transmitted to the movable heat-conducting block of thermal switch via flexible heat pipe, be transmitted to coupled radiant panel space-ward heat loss through radiation by left heat-conducting block or right heat-conducting block again, thereby set up heat-transfer path from the CCD focal plane subassembly to the space external environment condition.
When the radiant panel that links to each other with left heat-conducting block is in dorsad the sun one side, because the pressure effect of spring is with movable heat-conducting block overlaying on left heat-conducting block tightly, and break away from right heat-conducting block, the heat radiation conduction path of this moment is the radiant panel that extremely links to each other with left heat-conducting block through movable heat-conducting block, left heat-conducting block from CFPA;
When the variation owing to the camera attitude makes the radiant panel that links to each other with left heat-conducting block towards the solar time, under the effect of sun direct irradiation, cause the temperature rising and the expansion link of thermal switch is pushed up movable heat-conducting block from left heat-conducting block because of the heat expansion elongation, and be pressed on the right heat-conducting block, the heat radiation conduction path of this moment is another piece radiant panel that extremely links to each other with right heat-conducting block through movable heat-conducting block, right heat-conducting block from CFPA.
When the variation once more owing to the camera attitude is in towards the sun radiant panel that links to each other with right heat-conducting block, and the radiant panel that links to each other with left heat-conducting block is in the solar time dorsad, because the expansion link shrinkage of thermal switch, make movable heat-conducting block press to left heat-conducting block again and change heat dissipation channel once more.
Thermal switch of the present invention has solved space camera effectively and has been difficult to realize the technical barrier of the temperature of stable control CCD device because of the variation of operating attitude, and it is simple in structure, reliability is high, long service life; Realized temperature automatically controlled function.Can be widely used in relevant spacecraft temperature control and other occasion.
Description of drawings
Fig. 1 is the structural representation that the present invention is used for the thermal switch of space camera heat control system;
Fig. 2, Fig. 3 are the principle of work synoptic diagram of thermal switch of the present invention.
Embodiment
The embodiment that provides below in conjunction with accompanying drawing is described in further detail the present invention.
With reference to Fig. 1, the thermal switch that is used for the space camera heat control system, comprise the left heat-conducting block (1) made with invar, right heat-conducting block (3), the movable heat-conducting block (2) that between left heat-conducting block (1) and right heat-conducting block (3), can move to the left and right, expansion link (4) and spring (6); Described left heat-conducting block (1) and right heat-conducting block (3) are equipped with the blind hole of opening to movable heat-conducting block (2), described expansion link (4) and left heat-conducting block (1) are in the left heat-conducting block of being arranged on of sliding fit (1) blind hole, on its two ends are connected at the bottom of left heat-conducting block (1) blind hole respectively and on the movable heat-conducting block (2); Described spring (6) is arranged in right heat-conducting block (3) blind hole, and its two ends are replaced respectively at the bottom of right heat-conducting block (3) blind hole and on the movable heat-conducting block (2);
Described expansion link (4) is made greater than the aluminum alloy materials of left and right heat-conducting block and movable heat-conducting block with coefficient of linear thermal expansion.
In described spring (6), also place and hold the guide rod (5) that is fixed on the movable heat-conducting block (2) one by one, be beneficial to the mobile guide of movable heat-conducting block.
Described expansion link (4) is made the dumbbell shape structure of middle part hollow out, makes it can produce certain elastic deformation under bigger pressure.
As shown in Figure 2, the normality of thermal switch is that left heat-conducting block (1) and movable heat-conducting block (2) are fit-state, under the resilient force of spring 6, has increased the normal pressure of left heat-conducting block (1) and movable heat-conducting block (2) surface of contact, makes the thermal contact resistance resistance less.The heat overwhelming majority of CCD focal plane component is delivered to radiation cold plate I along the left channel of connecting and goes up diffusing in space.
As shown in Figure 3, be subjected to the effect of direct solar radiation as radiation cold plate I, temperature is elevated to can not bear the heat sink time spent of doing, expansion link 4 causes elongation because temperature raises, its elongation is greater than the elongation of left heat-conducting block (1) and movable heat-conducting block (2), so expansion link is owing to the moving movable heat-conducting block of variation promotion of self size moves to the right, cause left heat-conducting block (1) to separate with the surface of contact of movable heat-conducting block (2), movable heat-conducting block (2) and right heat-conducting block (3) are fitted, and the heat of CCD focal plane component mainly was delivered to radiation cold plate II along right channel and went up and loose in space this moment.Continuation heats up when causing expansion link 4 to continue elongation as radiation cold plate I, can make that binding face is tightr, and thermal resistance reduces; If further temperature rise makes expansion link 4 produce further elongation trend, then expansion link 4 self produces the elasticity sex change.And when the temperature of radiation cold plate I reduced, the temperature of expansion link 4 also decreased, and extension rod shrinks, and adds the effect of upper spring simultaneously, the normality of fitting and getting back to thermal switch with left heat-conducting block (1) on the left of movable heat-conducting block (2) is return.At this moment, continue cooling as radiation cold plate I and cause extension rod 4 to produce the trend that continues contraction, will increase contact surface positive pressure, make that contact is more effective; If further cooling then makes extension rod 4 self produce the elasticity sex change, eliminated the further increase of stress.Because the structure and material characteristics of extension rod 4 have enlarged the Applicable temperature scope of thermal switch in this way.
Claims (3)
1. thermal switch that is used for the space camera heat control system, it is characterized in that, comprise left heat-conducting block (1), right heat-conducting block (3), the movable heat-conducting block (2) that between left heat-conducting block (1) and right heat-conducting block (3), can move to the left and right, expansion link (4) and spring (6); Described left heat-conducting block (1) and right heat-conducting block (3) are equipped with the blind hole of opening to movable heat-conducting block (2), described expansion link (4) and left heat-conducting block (1) are in the left heat-conducting block of being arranged on of sliding fit (1) blind hole, on its two ends are connected at the bottom of left heat-conducting block (1) blind hole respectively and on the movable heat-conducting block (2); Described spring (6) is arranged in right heat-conducting block (3) blind hole, and its two ends are replaced respectively at the bottom of right heat-conducting block (3) blind hole and on the movable heat-conducting block (2);
Described expansion link (4) is made greater than the material of left and right heat-conducting block and movable heat-conducting block with coefficient of linear thermal expansion.
2. the thermal switch that is used for the space camera heat control system according to claim 1, it is characterized in that described expansion link (4) make the middle part hollow out the dumbbell shape structure.
3. the thermal switch that is used for the space camera heat control system according to claim 1 is characterized in that, also places to hold the guide rod (5) that is fixed on the movable heat-conducting block (2) one by one in described spring (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008100515549A CN101424862B (en) | 2008-12-09 | 2008-12-09 | Thermal switch for heat control system of camera |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008100515549A CN101424862B (en) | 2008-12-09 | 2008-12-09 | Thermal switch for heat control system of camera |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101424862A true CN101424862A (en) | 2009-05-06 |
| CN101424862B CN101424862B (en) | 2010-06-02 |
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ID=40615551
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2008100515549A Expired - Fee Related CN101424862B (en) | 2008-12-09 | 2008-12-09 | Thermal switch for heat control system of camera |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102325390A (en) * | 2011-04-15 | 2012-01-18 | 中国科学院长春光学精密机械与物理研究所 | Automatic control system for thermal testing infrared radiation heater of spatial camera and method |
| CN103488031A (en) * | 2013-08-29 | 2014-01-01 | 中国科学院长春光学精密机械与物理研究所 | Aviation camera subsection split mounting type optical window defrosting and demisting device |
| CN103616790A (en) * | 2013-11-25 | 2014-03-05 | 中国科学院长春光学精密机械与物理研究所 | Space camera initiative thermal control method based on temperature levels |
| CN103968869A (en) * | 2014-05-04 | 2014-08-06 | 中国科学院长春光学精密机械与物理研究所 | Energy-saving radiator for space optical remote sensor CCD component |
| CN105698768A (en) * | 2016-03-02 | 2016-06-22 | 中国科学院长春光学精密机械与物理研究所 | Large-view-field and high-integration-density focal plane structure of off-axis camera for space |
| CN113815906A (en) * | 2020-11-05 | 2021-12-21 | 山东大学 | Loop heat pipe and thermal control system thereof |
| CN114161169A (en) * | 2021-12-31 | 2022-03-11 | 霍山嘉远智能制造有限公司 | Preheating cutter for machining R groove in inner hole of butterfly valve body |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2400545A (en) * | 2003-03-01 | 2004-10-20 | David Mcanulty | A temperature-controlled camera case |
| CN2739671Y (en) * | 2004-10-22 | 2005-11-09 | 中国科学院西安光学精密机械研究所 | Digital camera temperature control device |
| CN200941653Y (en) * | 2006-05-18 | 2007-08-29 | 中国科学院长春光学精密机械与物理研究所 | Thermal controller of CCD camera |
-
2008
- 2008-12-09 CN CN2008100515549A patent/CN101424862B/en not_active Expired - Fee Related
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102325390B (en) * | 2011-04-15 | 2012-12-12 | 中国科学院长春光学精密机械与物理研究所 | Automatic control system for thermal testing infrared radiation heater of spatial camera and method |
| CN102325390A (en) * | 2011-04-15 | 2012-01-18 | 中国科学院长春光学精密机械与物理研究所 | Automatic control system for thermal testing infrared radiation heater of spatial camera and method |
| CN103488031A (en) * | 2013-08-29 | 2014-01-01 | 中国科学院长春光学精密机械与物理研究所 | Aviation camera subsection split mounting type optical window defrosting and demisting device |
| CN103488031B (en) * | 2013-08-29 | 2016-12-07 | 中国科学院长春光学精密机械与物理研究所 | Aviation camera subsection split mounting type optical window defrosting and demisting device |
| CN103616790A (en) * | 2013-11-25 | 2014-03-05 | 中国科学院长春光学精密机械与物理研究所 | Space camera initiative thermal control method based on temperature levels |
| CN103616790B (en) * | 2013-11-25 | 2016-03-02 | 中国科学院长春光学精密机械与物理研究所 | A kind of space camera Active thermal control method based on temperature levels |
| CN103968869B (en) * | 2014-05-04 | 2017-01-18 | 中国科学院长春光学精密机械与物理研究所 | Energy-saving radiator for space optical remote sensor CCD component |
| CN103968869A (en) * | 2014-05-04 | 2014-08-06 | 中国科学院长春光学精密机械与物理研究所 | Energy-saving radiator for space optical remote sensor CCD component |
| CN105698768A (en) * | 2016-03-02 | 2016-06-22 | 中国科学院长春光学精密机械与物理研究所 | Large-view-field and high-integration-density focal plane structure of off-axis camera for space |
| CN105698768B (en) * | 2016-03-02 | 2018-08-03 | 中国科学院长春光学精密机械与物理研究所 | The space big visual field high integration focal plane structure of off-axis camera |
| CN113815906A (en) * | 2020-11-05 | 2021-12-21 | 山东大学 | Loop heat pipe and thermal control system thereof |
| CN113815906B (en) * | 2020-11-05 | 2023-12-15 | 山东大学 | Loop heat pipe and thermal control system thereof |
| CN114161169A (en) * | 2021-12-31 | 2022-03-11 | 霍山嘉远智能制造有限公司 | Preheating cutter for machining R groove in inner hole of butterfly valve body |
| CN114161169B (en) * | 2021-12-31 | 2024-01-26 | 霍山嘉远智能制造有限公司 | Preheating cutter for machining inner hole R groove of butterfly valve body |
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| Publication number | Publication date |
|---|---|
| CN101424862B (en) | 2010-06-02 |
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Granted publication date: 20100602 Termination date: 20111209 |