CN104035264A - Integrated thermal control device for mini-satellite and spatial optical camera - Google Patents
Integrated thermal control device for mini-satellite and spatial optical camera Download PDFInfo
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- CN104035264A CN104035264A CN201410310145.1A CN201410310145A CN104035264A CN 104035264 A CN104035264 A CN 104035264A CN 201410310145 A CN201410310145 A CN 201410310145A CN 104035264 A CN104035264 A CN 104035264A
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Abstract
The invention discloses an integrated thermal control device for a mini-satellite and a spatial optical camera, and relates to the field of aerospace. The integrated thermal control device solves the problems that due to the facts that active thermal control power consumption provided for the spatial optical camera by the mini-satellite is small and the work temperature of the spatial optical camera can not be kept within a required range, the reliability and the imaging quality of the spatial optical camera are lowered. The integrated thermal control device comprises a plurality of crossed flexible connectors fixed to the sunny side of the spatial optical camera, a plurality of thermal insulation pads arranged on the crossed flexible connectors in a one-to-one mode, a camera solar cell array fixed to the thermal insulation pads and the crossed flexible connectors and connected with the mini-satellite through a cable, and a plurality of layers of thermal insulation assemblies laid on the outer surface of the spatial optical camera and located between the camera solar cell array and the spatial optical camera, wherein a variable cross-section structure of crisscrossed spring plate openings is adopted in the crossed flexible connectors. The work temperature of the spatial optical camera is kept within the required range, the active thermal control power consumption is increased, and the reliability and the imaging quality are improved.
Description
Technical field
The present invention relates to field of aerospace technology, be specifically related to the integrated thermal controls apparatus of a kind of moonlet and space optical camera.
Background technology
Satellite transit is operated in space environment, because temperature under space environment can reach subzero below 100 DEG C, and the working temperature of space optical camera 5 is 20 DEG C, such temperature difference can make the situation such as space optical camera 5 recurring structure frameworks and optical mirror distortion and electronic component failure, causes the imaging capability reduction of space optical camera 5 even to completely lose.In order to ensure that space optical camera 5, working at temperature normally, need to carry out thermal control design to space optical camera 5.At present, the thermal control of space optical camera 5 adopts the thermal control implementation method that passive thermal control combines with Active thermal control.Comprise the passive thermal control method of the coated multilayer insulation material of the outside surface (do not comprise light inlet) of insulation material to space optical camera 5 and Active thermal control method space optical camera 5 being heated with heater element of adopting.
At present, the energy that space optical camera 5 Active thermal controls consume is converted solar energy into electrical energy to realize by satellite sun energy battery battle array completely.Its shortcoming is: for moonlet 6, due to volume and envelope size all less, the limited amount of the satellite sun energy battery battle array that 6 of moonlets can carry, its converting electrical energy is less.Therefore, distribute to space optical camera 5 Active thermal control power consumptions less, the working temperature of space optical camera 5 cannot be remained in claimed range.
Summary of the invention
In order to solve moonlet, thereby to offer space optical camera Active thermal control power consumption less and space optical camera working temperature cannot be remained on to the problem that causes the reliability of space optical camera and image quality to reduce in claimed range, the invention provides the integrated thermal controls apparatus of a kind of moonlet and space optical camera.
The present invention for the technical scheme that technical solution problem adopts as follows:
The integrated thermal controls apparatus of moonlet of the present invention and space optical camera, comprise space optical camera and with the moonlet that space optical camera is fixedly linked, also comprise:
Be fixed on space optical camera towards the multiple intersection flexible connecting members on sunny side, described intersection flexible connecting member adopts the variable section structure of the reed gap of right-angled intersection, for reducing pyroconductivity;
Be placed on one to one the multiple heat insulating mattress that intersect on flexible connecting member;
With the camera solar array that heat insulating mattress and the flexible connecting member that intersects are fixed together, described camera solar array is connected with moonlet by cable;
Be layered on the multilayer insulation assembly on space optical camera outside surface and between camera solar array and space optical camera.
Described intersection flexible connecting member comprise be fixed on space optical camera towards the mount pad on sunny side, be arranged on cylinder table on mount pad, be arranged on upper reed plate gap and lower reed gap on cylinder table; Described upper reed plate gap and lower reed gap are cruciform shape, and described heat insulating mattress is placed on cylinder table.
Described camera solar array is rectangle, falls up two large oblique angles to ensure leaving enough safe distances between itself and moonlet radome fairing.
Described heat insulating mattress adopts polyimide material to make.
Described intersection flexible connecting member adopts titanium alloy material to make.
Described multilayer insulation assembly is formed by 20 layers of two-sided metallized film and 20 layers of terylene net successively intersecting.
The invention has the beneficial effects as follows:
1, adopt moonlet and space optical camera thermal control integrated design, at moonlet in-orbit under state of flight, space optical camera towards camera solar array being set to increase the electric energy transfer capability of moonlet on sunny side, and conduct certain heat energy to space optical camera, increase space optical camera Active thermal control power consumption, in the thermal control of space optical camera, directly use the heat of camera solar array to carry out the temperature control of space optical camera, the active thermal power consumption that space optical camera can be used increases, thermal control power margin increases, and reliability improves.
2, on thermal energy conduction path, adopt heat insulating mattress to carry out heat insulation, prevent that space optical camera local temperature is overheated, improve the image quality of space optical camera.
3, intersection flexible connecting member is designed to the reed gap form of right-angled intersection, can absorb most of kinetic energy by the distortion of intersection flexible connecting member self, thereby change the pyroconductivity in heat conduction, make to enter heat in space optical camera and meet the requirement of camera thermal control, the optical texture that ensures space optical camera is constant, eliminate the impact of the temperature difference simultaneously, improve the image quality of space optical camera.
Brief description of the drawings
Fig. 1 is the front view of moonlet of the present invention and the integrated thermal controls apparatus of space optical camera.
Fig. 2 is the vertical view of the moonlet shown in Fig. 1 and the integrated thermal controls apparatus of space optical camera.
Fig. 3 is the left view of the moonlet shown in Fig. 1 and the integrated thermal controls apparatus of space optical camera.
Fig. 4 is the local amplification view at A place in Fig. 1.
Fig. 5 is the perspective view of intersection flexible connecting member.
Fig. 6 is the front view of intersection flexible connecting member.
Fig. 7 is the left view of the intersection flexible connecting member shown in Fig. 6.
In figure: 1, camera solar array, 2, heat insulating mattress, 3, intersect flexible connecting member, 31, mount pad, 32, cylinder table, 33, upper reed plate gap, 34, lower reed gap, 4, multilayer insulation assembly, 5, space optical camera, 6, moonlet.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail.
As shown in figures 1 and 3, the integrated thermal controls apparatus of moonlet of the present invention and space optical camera, comprise: camera solar array 1, four heat insulating mattress 2, four intersection flexible connecting members 3, multilayer insulation assembly 4, space optical camera 5 and moonlet 6, space optical camera 5 is fixedly connected with moonlet 6, four intersect flexible connecting member 3 by screw be fixedly mounted on space optical camera 5 on sunny side, first four heat insulating mattress 2 being placed on respectively to four intersects on flexible connecting member 3, again camera solar array 1 is placed on four heat insulating mattress 2, then by camera solar array 1, together with heat insulating mattress 2 is fixed by screws in intersection flexible connecting member 3, by the cable of camera solar array 1 pick out after and moonlet 6 link together, multilayer insulation assembly 4 is layered on space optical camera 5 outside surfaces, and between camera solar array 1 and space optical camera 5.
Adopt moonlet 6 and space optical camera 5 thermal control integrated designs, at moonlet 6 in-orbit under state of flight, space optical camera 5 towards camera solar array 1 being set to increase the electric energy transfer capability of moonlet 6 on sunny side, and conduct certain heat energy to space optical camera 5, increase space optical camera 5 Active thermal control power consumptions, in the thermal control of space optical camera 5, directly use the heat of camera solar array 1 to carry out the temperature control of space optical camera 5.As shown in Figure 2, camera solar array 1 is designed to rectangle, fall two large oblique angles up to ensure leaving enough safe distances between itself and moonlet 6 radome fairings, and the structural design of camera solar array 1 fully takes into account the envelope size restrictions of moonlet 6 and the interface relationship with space optical camera 5.
At moonlet 6 under day pattern, camera solar array 1 surface temperature on space optical camera 5 can reach more than 100 DEG C, if directly by this thermal energy conduction to space optical camera 5, can cause space optical camera 5 local temperatures overheated, temperature control level is overproof, cause the image quality degradation of space optical camera 5, therefore, heat insulating mattress 2 is set on thermal energy conduction path to carry out heat insulation, heat insulating mattress 2 adopts polyimide material to make, as shown in Figure 4, heat insulating mattress 2 is arranged on camera solar array 1 and intersects between flexible connecting member 3.
The flexible connecting member 3 that intersects adopts titanium alloy material to make, for reducing pyroconductivity.As Fig. 5, shown in Fig. 6 and Fig. 7, the flexible connecting member 3 that intersects adopts the variable cross section design of the reed gap of right-angled intersection, it comprises mount pad 31, cylinder table 32, upper reed plate gap 33 and lower reed gap 34, mount pad 31 by screw be fixedly mounted on space optical camera 5 on sunny side, cylinder table 32 is integrated with mount pad 31, upper reed plate gap 33 and lower reed gap 34 are arranged on cylinder table 32, upper reed plate gap 33 and lower reed gap 34 are cruciform shape, the upper end of cylinder table 32 is provided with threaded hole, heat insulating mattress 2 is placed on cylinder table 32, again camera solar array 1 is placed on heat insulating mattress 2, then by camera solar array 1, together with heat insulating mattress 2 is fixed by screws in intersection flexible connecting member 3.Integrated thermal controls apparatus of the present invention is assembly and connection at room temperature, but in space environment, at moonlet 6 under day pattern, the surface temperature of camera solar array 1 can reach more than 100 DEG C, and the working temperature of space optical camera 5 is 20 DEG C, because material exists certain thermal expansivity, so the huge temperature difference can make to intersect the two ends of flexible connecting member 3 and produce relative motion, thereby cause the optical texture generation deformation of space optical camera 5, cause the decline of image quality, therefore, intersection flexible connecting member 3 is designed to the reed gap form of right-angled intersection, can absorb most of kinetic energy by intersecting the distortion of flexible connecting member 3 self, thereby change the pyroconductivity in heat conduction, make to enter heat in space optical camera 5 and meet the requirement of camera thermal control, the optical texture that ensures space optical camera 5 is constant, eliminate the impact of the temperature difference simultaneously, improve the image quality of space optical camera 5.
Adopt reed gap (upper reed plate gap 33 and the lower reed gap 34) width of the right-angled intersection of thermal control design software to intersection flexible connecting member 3 and the thickness of heat insulating mattress 2 to be optimized design, the heat that enters space optical camera 5 inside from camera solar array 1 after heat insulating mattress 2 and intersection flexible connecting member 3 meets the requirement of camera thermal control.
In present embodiment, multilayer insulation assembly 4 is formed by 20 layers of two-sided metallized film (6 μ m radiation shield) and 20 layers of terylene net successively intersecting.
Claims (6)
1. the integrated thermal controls apparatus of moonlet and space optical camera, comprise space optical camera (5) and with the moonlet (6) that space optical camera (5) is fixedly linked, it is characterized in that, also comprise:
Be fixed on space optical camera (5) towards the multiple intersection flexible connecting members (3) on sunny side, described intersection flexible connecting member (3) adopts the variable section structure of the reed gap of right-angled intersection, for reducing pyroconductivity;
Be placed on one to one the multiple heat insulating mattress (2) that intersect on flexible connecting member (3);
With the camera solar array (1) that heat insulating mattress (2) and the flexible connecting member (3) that intersects are fixed together, described camera solar array (1) is connected with moonlet (6) by cable;
Be layered on space optical camera (5) outside surface and be positioned at the multilayer insulation assembly (4) between camera solar array (1) and space optical camera (5).
2. the integrated thermal controls apparatus of moonlet according to claim 1 and space optical camera, it is characterized in that, described intersection flexible connecting member (3) comprise be fixed on space optical camera (5) towards the mount pad (31) on sunny side, be arranged on cylinder table (32) on mount pad (31), be arranged on upper reed plate gap (33) and lower reed gap (34) on cylinder table (32); Described upper reed plate gap (33) and lower reed gap (34) are cruciform shape, and described heat insulating mattress (2) is placed on cylinder table (32).
3. the integrated thermal controls apparatus of moonlet according to claim 1 and space optical camera, it is characterized in that, described camera solar array (1) is rectangle, falls up two large oblique angles to ensure leaving enough safe distances between itself and moonlet (6) radome fairing.
4. the integrated thermal controls apparatus of moonlet according to claim 1 and space optical camera, is characterized in that, described heat insulating mattress (2) adopts polyimide material to make.
5. the integrated thermal controls apparatus of moonlet according to claim 1 and space optical camera, is characterized in that, described intersection flexible connecting member (3) adopts titanium alloy material to make.
6. the integrated thermal controls apparatus of moonlet according to claim 1 and space optical camera, is characterized in that, described multilayer insulation assembly (4) is formed by 20 layers of two-sided metallized film and 20 layers of terylene net successively intersecting.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410310145.1A CN104035264B (en) | 2014-06-30 | 2014-06-30 | Moonlet thermal controls apparatus integrated with space optical camera |
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| CN201410310145.1A CN104035264B (en) | 2014-06-30 | 2014-06-30 | Moonlet thermal controls apparatus integrated with space optical camera |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107505843A (en) * | 2017-09-15 | 2017-12-22 | 中国科学院长春光学精密机械与物理研究所 | A kind of Active thermal control optimization method of space optics payload |
| CN107957740A (en) * | 2017-11-15 | 2018-04-24 | 华南理工大学 | A kind of spaceborne temperature-controlling system using thermal conductive wire |
| CN107967393A (en) * | 2017-12-07 | 2018-04-27 | 上海宇航***工程研究所 | A kind of spacecraft bitubular parallel-connection structure based under multi-constraint condition carries design method |
| 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 |
| CN110356590A (en) * | 2019-06-27 | 2019-10-22 | 航天东方红卫星有限公司 | A kind of thermal control method and thermal controls apparatus for camera small outside star |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06350118A (en) * | 1993-06-11 | 1994-12-22 | Canon Inc | Electronic equipment with solar battery |
| CN102530267B (en) * | 2010-12-10 | 2014-09-03 | 上海卫星工程研究所 | Common platform for satellite |
| CN102495515B (en) * | 2011-12-12 | 2014-01-15 | 中国科学院长春光学精密机械与物理研究所 | Heat-insulation cushion applicable to heat control of space camera |
| CN103448920B (en) * | 2013-08-08 | 2016-04-20 | 上海卫星工程研究所 | The precise temperature control device of spaceborne star sensor |
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2014
- 2014-06-30 CN CN201410310145.1A patent/CN104035264B/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107505843A (en) * | 2017-09-15 | 2017-12-22 | 中国科学院长春光学精密机械与物理研究所 | A kind of Active thermal control optimization method of space optics payload |
| CN107505843B (en) * | 2017-09-15 | 2020-05-15 | 中国科学院长春光学精密机械与物理研究所 | Active thermal control optimization method for space optical payload |
| CN107957740A (en) * | 2017-11-15 | 2018-04-24 | 华南理工大学 | A kind of spaceborne temperature-controlling system using thermal conductive wire |
| CN107967393A (en) * | 2017-12-07 | 2018-04-27 | 上海宇航***工程研究所 | A kind of spacecraft bitubular parallel-connection structure based under multi-constraint condition carries design method |
| CN107967393B (en) * | 2017-12-07 | 2021-02-26 | 上海宇航***工程研究所 | Spacecraft double-cylinder parallel structure bearing design method based on multi-constraint condition |
| 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 |
| CN110356590A (en) * | 2019-06-27 | 2019-10-22 | 航天东方红卫星有限公司 | A kind of thermal control method and thermal controls apparatus for camera small outside star |
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| CN104035264B (en) | 2016-11-02 |
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