CN104035264B - Moonlet thermal controls apparatus integrated with space optical camera - Google Patents
Moonlet thermal controls apparatus integrated with space optical camera Download PDFInfo
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- CN104035264B CN104035264B CN201410310145.1A CN201410310145A CN104035264B CN 104035264 B CN104035264 B CN 104035264B CN 201410310145 A CN201410310145 A CN 201410310145A CN 104035264 B CN104035264 B CN 104035264B
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- space optical
- optical camera
- moonlet
- camera
- flexible connecting
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Abstract
Moonlet thermal controls apparatus integrated with space optical camera, relate to aerospace field, solve moonlet be supplied to space optical camera Active thermal control power consumption less and in space optical camera operating temperature cannot being maintained at claimed range thus the problem causing the reliability of space optical camera and image quality to reduce.The variable section structure of the reed gap of decussation is used towards the multiple intersection flexible connecting members on sunny side, the flexible connecting member that intersects including being fixed on space optical camera；It is placed on the multiple heat insulating mattress intersected on flexible connecting member one to one；The camera solar array being fixed together with heat insulating mattress and the flexible connecting member that intersects, camera solar array is connected with moonlet by cable；It is layered on the multilayer insulation assembly on space optical camera outer surface and between camera solar array and space optical camera.The operating temperature of space optical camera is maintained in claimed range, and active thermal power consumption increases, and reliability and image quality increase.
Description
Technical field
The present invention relates to field of aerospace technology, be specifically related to a kind of moonlet and space optical camera one
Change thermal controls apparatus.
Background technology
Satellite transit is operated in space environment, owing under space environment, temperature can reach subzero less than 100 DEG C,
And the operating temperature of space optical camera 5 is 20 DEG C, such temperature difference can make space optical camera 5 tie
Structure framework and the situation such as optical mirror deformation and electronic component failure, cause space optical camera 5
Imaging capability reduction even completely loses.In order to ensure that space optical camera 5 works at normal temperatures,
Need space optical camera 5 is carried out thermal control design.At present, the thermal control of space optical camera 5 uses passively
The thermal control implementation that thermal control combines with Active thermal control.Including using insulation material to space optical camera 5
Outer surface (not including light inlet) cladding multilayer insulation material passive thermal control method and with heater element pair
Space optical camera 5 carries out the Active thermal control method heated.
At present, the energy that space optical camera 5 Active thermal control is consumed is entirely by satellite sun energy cell array
Convert solar energy into electrical energy and realize.Its shortcoming is: for moonlet 6, due to volume and envelope size
The least, the limited amount of the satellite sun energy cell array that moonlet 6 is carried by, its converting electrical energy is less.
Therefore, space optical camera 5 Active thermal control power consumption is distributed to less, it is impossible to by the work of space optical camera 5
It is maintained in claimed range as temperature.
Summary of the invention
In order to solve moonlet, to be supplied to space optical camera Active thermal control power consumption less and cannot be by space optics
Camera operating temperature is maintained in claimed range thus causes reliability and the image quality fall of space optical camera
Low problem, the present invention provides a kind of moonlet thermal controls apparatus integrated with space optical camera.
The present invention solves that the technical scheme that technical problem is used is as follows:
The moonlet of present invention thermal controls apparatus integrated with space optical camera, including space optical camera and with
The moonlet that space optical camera is fixedly linked, also includes:
Being fixed on space optical camera towards the multiple intersection flexible connecting members on sunny side, described intersection flexibly connects
Part uses the variable section structure of the reed gap of decussation, is used for reducing pyroconductivity；
It is placed on the multiple heat insulating mattress intersected on flexible connecting member one to one；
The camera solar array being fixed together with heat insulating mattress and the flexible connecting member that intersects, described camera is too
Sun can cell array be connected with moonlet by cable；
It is layered on space optical camera outer surface and between camera solar array and space optical camera
Multilayer insulation assembly.
Described intersection flexible connecting member include being fixed on space optical camera towards the mounting seat on sunny side, be arranged on
Cylinder table in mounting seat, the upper reed plate gap being arranged on cylinder table and lower reed gap；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, and the most two big oblique angles are to ensure itself and moonlet
Enough safe distances are left between trousers.
Described heat insulating mattress uses polyimide material to make.
Described intersection flexible connecting member uses 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 intersecting successively.
The invention has the beneficial effects as follows:
1, moonlet and space optical camera thermal control integrated design are used, in moonlet state of flight in-orbit
Under, turning with the electric energy increasing moonlet towards arranging camera solar array on sunny side at space optical camera
Transducing power, and conduct certain heat energy to space optical camera, increase space optical camera Active thermal control power consumption,
The heat of camera solar array is i.e. directly used to carry out space optics phase in the thermal control of space optical camera
The temperature of machine controls, space optical camera can active thermal power consumption increase, thermal control power margin increases, can
Improve by property.
2, use heat insulating mattress to be thermally shielded on thermal energy conduction path, prevent space optical camera local temperature mistake
Heat, improves the image quality of space optical camera.
3, intersection flexible connecting member is designed to the reed gap form of decussation, can be by intersecting flexibility even
The deformation of fitting self absorbs major part kinetic energy, thus changes the pyroconductivity in conduction of heat, makes entrance space
Heat in optical camera meets the requirement of camera thermal control, it is ensured that the optical texture of space optical camera is constant,
Eliminate the impact of the temperature difference simultaneously, improve the image quality of space optical camera.
Accompanying drawing explanation
Fig. 1 is the front view of the moonlet thermal controls apparatus integrated with space optical camera of the present invention.
Fig. 2 is the top view of the thermal controls apparatus integrated with space optical camera of the moonlet shown in Fig. 1.
Fig. 3 is the left view of the thermal controls apparatus integrated with space optical camera of the moonlet shown in Fig. 1.
Fig. 4 is the enlarged partial sectional view in Fig. 1 at A.
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, install
Seat, 32, cylinder table, 33, upper reed plate gap, 34, lower reed gap, 4, multilayer insulation assembly, 5,
Space optical camera, 6, moonlet.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is described in further detail.
As shown in figures 1 and 3, the moonlet of present invention thermal controls apparatus integrated with space optical camera, bag
Include: 1, four heat insulating mattress of camera solar array 2, four intersection flexible connecting member 3, multilayer insulation group
Part 4, space optical camera 5 and moonlet 6, space optical camera 5 is fixing with moonlet 6 to be connected, four
Intersect flexible connecting member 3 by screw be fixedly mounted on space optical camera 5 towards on sunny side, first by four
Heat insulating mattress 2 is individually positioned in four and intersects on flexible connecting member 3, then is placed by camera solar array 1
On four heat insulating mattress 2, then by camera solar array 1, heat insulating mattress 2 and the flexible connecting member 3 that intersects
It is fixed by screws in together, is connected to moonlet 6 after the cable of camera solar array 1 is picked out
Together, multilayer insulation assembly 4 is layered on space optical camera 5 outer surface, and is positioned at camera solaode
Between battle array 1 and space optical camera 5.
Use moonlet 6 and space optical camera 5 thermal control integrated design, at moonlet 6 flight shape in-orbit
Under state, on sunny side, camera solar array 1 is set to increase moonlet 6 at space optical camera 5
Electric energy transfer capability, and conduct certain heat energy to space optical camera 5, increase space optical camera 5
Active thermal control power consumption, i.e. directly uses camera solar array 1 in the thermal control of space optical camera 5
Heat carries out the temperature of space optical camera 5 and controls.As in figure 2 it is shown, camera solar array 1 designs
Rectangularity, the most two big oblique angles are to ensure to leave enough peaces between itself and moonlet 6 trousers
Full distance, the structure design of camera solar array 1 fully takes into account the envelope size limitation of moonlet 6
And with the interface relationship of space optical camera 5.
Under moonlet 6 is to day pattern, the camera solar array 1 surface temperature on space optical camera 5
Degree 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 temperature is overheated, and temperature control level is overproof, and the image quality causing space optical camera 5 is tight
Heavily declining, therefore, arrange heat insulating mattress 2 and be thermally shielded on thermal energy conduction path, heat insulating mattress 2 uses polyamides
Imines material is made, and as shown in Figure 4, heat insulating mattress 2 is arranged on camera solar array 1 and flexibility of intersecting
Between connector 3.
The flexible connecting member 3 that intersects uses titanium alloy material to make, and is used for reducing pyroconductivity.Such as Fig. 5, Fig. 6
Shown in Fig. 7, the flexible connecting member 3 that intersects uses the variable cross-section design of the reed gap of decussation, its bag
Including mounting seat 31, cylinder table 32, upper reed plate gap 33 and lower reed gap 34, mounting seat 31 passes through screw
Be fixedly mounted on space optical camera 5 towards on sunny side, cylinder table 32 is integrated with mounting seat 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 is cruciform shape, and the upper end of cylinder table 32 is provided with screwed hole, and heat insulating mattress 2 is placed on circle
On pylon 32, then camera solar array 1 is placed on heat insulating mattress 2, then by camera solar-electricity
Together with pond battle array 1, heat insulating mattress 2 are fixed by screws in intersection flexible connecting member 3.The one heat-transformation of the present invention
Control device is at room temperature assembly and connection, but in space environment, under moonlet 6 is to day pattern,
The surface temperature of camera solar array 1 can reach more than 100 DEG C, and the work temperature of space optical camera 5
Degree is 20 DEG C, and owing to material exists certain thermal coefficient of expansion, the hugest temperature difference can make intersection flexibility even
The two ends of fitting 3 produce relative motion, thus cause the optical texture of space optical camera 5 to deform upon,
Cause the decline of image quality, therefore, intersection flexible connecting member 3 is designed to the reed gap of decussation
Form, can absorb major part kinetic energy by the deformation of intersection flexible connecting member 3 self, thus change conduction of heat
In pyroconductivity, make the heat in entrance space optical camera 5 meet the requirement of camera thermal control, it is ensured that empty
Between the optical texture of optical camera 5 constant, eliminate the impact of the temperature difference simultaneously, improve space optical camera 5
Image quality.
(upper reed plate slits to the reed gap of the decussation of intersection flexible connecting member 3 to use thermal control design software
Mouthfuls 33 and lower reed gap 34) thickness of width and heat insulating mattress 2 is optimized design, from camera solar energy
It is full that cell array 1 enters the heat within space optical camera 5 after heat insulating mattress 2 and intersection flexible connecting member 3
The requirement of foot camera thermal control.
In present embodiment, multilayer insulation assembly 4 is by 20 layers of two-sided metallized film (6 μm radiation shield) and 20
Layer terylene net intersecting successively forms.
Claims (6)
1. moonlet thermal controls apparatus integrated with space optical camera, including space optical camera (5) and with
The moonlet (6) that space optical camera (5) is fixedly linked, it is characterised in that also include:
It is fixed on space optical camera (5) towards the multiple intersection flexible connecting members (3) on sunny side, described intersection
Flexible connecting member (3) uses the variable section structure of the reed gap of decussation, is used for reducing pyroconductivity；
It is placed on the multiple heat insulating mattress (2) intersected on flexible connecting member (3) one to one；
The camera solar array (1) being fixed together with heat insulating mattress (2) and the flexible connecting member (3) that intersects,
Described camera solar array (1) is connected with moonlet (6) by cable；
It is layered on space optical camera (5) outer surface and is positioned at camera solar array (1) and spatial light
Learn the multilayer insulation assembly (4) between camera (5).
Moonlet the most according to claim 1 thermal controls apparatus integrated with space optical camera, its feature
Being, described intersection flexible connecting member (3) includes being fixed on space optical camera (5) towards the peace on sunny side
Dress seat (31), be arranged in mounting seat (31) cylinder table (32), be arranged on cylinder table (32)
Upper reed plate gap (33) and lower reed gap (34)；Described upper reed plate gap (33) and lower reed gap (34)
Relative to position become decussation, described heat insulating mattress (2) is placed on cylinder table (32).
Moonlet the most according to claim 1 thermal controls apparatus integrated with space optical camera, its feature
Being, described camera solar array (1) is rectangle, the most two big oblique angles with ensure its with
Enough safe distances are left between moonlet (6) trousers.
Moonlet the most according to claim 1 thermal controls apparatus integrated with space optical camera, its feature
Being, described heat insulating mattress (2) uses polyimide material to make.
Moonlet the most according to claim 1 thermal controls apparatus integrated with space optical camera, its feature
Being, described intersection flexible connecting member (3) uses titanium alloy material to make.
Moonlet the most according to claim 1 thermal controls apparatus integrated with space optical camera, its feature
Being, described multilayer insulation assembly (4) is by 20 layers of two-sided metallized film and 20 layers of terylene net cross-bedding successively
Fold and form.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410310145.1A CN104035264B (en) | 2014-06-30 | 2014-06-30 | Moonlet thermal controls apparatus integrated with space optical camera |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410310145.1A CN104035264B (en) | 2014-06-30 | 2014-06-30 | Moonlet thermal controls apparatus integrated with space optical camera |
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| Publication Number | Publication Date |
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| CN104035264A CN104035264A (en) | 2014-09-10 |
| CN104035264B true CN104035264B (en) | 2016-11-02 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410310145.1A Active CN104035264B (en) | 2014-06-30 | 2014-06-30 | Moonlet thermal controls apparatus integrated with space optical camera |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN107957740B (en) * | 2017-11-15 | 2023-03-10 | 华南理工大学 | Satellite-borne temperature control system using heat conducting wires |
| CN107967393B (en) * | 2017-12-07 | 2021-02-26 | 上海宇航系统工程研究所 | Spacecraft double-cylinder parallel structure bearing design method based on multi-constraint condition |
| 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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| EP0629033A2 (en) * | 1993-06-11 | 1994-12-14 | Canon Kabushiki Kaisha | Equipment using solar battery |
| CN102495515A (en) * | 2011-12-12 | 2012-06-13 | 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 |
| CN102530267A (en) * | 2010-12-10 | 2012-07-04 | 上海卫星工程研究所 | Common platform for satellite |
| CN103448920A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Precise temperature control device for spaceborne star sensors |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0629033A2 (en) * | 1993-06-11 | 1994-12-14 | Canon Kabushiki Kaisha | Equipment using solar battery |
| CN102530267A (en) * | 2010-12-10 | 2012-07-04 | 上海卫星工程研究所 | Common platform for satellite |
| CN102495515A (en) * | 2011-12-12 | 2012-06-13 | 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 |
| CN103448920A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Precise temperature control device for spaceborne star sensors |
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