CN105549306A - Light-weight robust thermal control apparatus used for carbon fiber main supporting structure camera - Google Patents
Light-weight robust thermal control apparatus used for carbon fiber main supporting structure camera Download PDFInfo
- Publication number
- CN105549306A CN105549306A CN201510962302.1A CN201510962302A CN105549306A CN 105549306 A CN105549306 A CN 105549306A CN 201510962302 A CN201510962302 A CN 201510962302A CN 105549306 A CN105549306 A CN 105549306A
- Authority
- CN
- China
- Prior art keywords
- camera
- supporting structure
- main supporting
- carbon fiber
- light
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- G—PHYSICS
- G03—PHOTOGRAPHY; CINEMATOGRAPHY; ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ELECTROGRAPHY; HOLOGRAPHY
- G03B—APPARATUS OR ARRANGEMENTS FOR TAKING PHOTOGRAPHS OR FOR PROJECTING OR VIEWING THEM; APPARATUS OR ARRANGEMENTS EMPLOYING ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ACCESSORIES THEREFOR
- G03B17/00—Details of cameras or camera bodies; Accessories therefor
- G03B17/55—Details of cameras or camera bodies; Accessories therefor with provision for heating or cooling, e.g. in aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Carbon And Carbon Compounds (AREA)
Abstract
The invention relates to a light-weight robust thermal control apparatus used for a carbon fiber main supporting structure camera. The light-weight robust thermal control apparatus comprises a camera supporting truss, a thin-film type electric heater, multiple (pyrolytic highly oriented graphite sheet) PGS thin films, and a two-sided pressure sensitive adhesive tape, wherein the thin-film type electric heater is arranged on the outermost layer of the camera supporting truss; and the multiple high-thermal-conductivity flexible thin films are adhered to the camera supporting truss through the two-sided pressure sensitive adhesive tape in a splicing manner. According to the light-weight robust thermal control apparatus used for the carbon fiber main supporting structure camera, an existing mature thermal control technology and the PGS thin films having the characteristic of extremely high thermal conductivity are fully utilized; a space camera main supporting structure is adhered to the PGS thin films, so that the equivalent thermal conductivity of the carbon fiber structure is effectively improved; and the technical problem of relatively high temperature gradient of the main supporting structure under influences of outside-track thermal flow and the heater caused by relatively low thermal conductivity of an all-carbon structure camera is solved.
Description
Technical field:
The invention belongs to space optical remote technical field, particularly relate to a kind of light-duty robust thermal controls apparatus for carbon fiber main supporting structure camera.
Background technology:
In space optical remote sensor, main supporting structure is the critical component of space camera imaging, and the image quality for camera has direct impact.Along with carbon fibre material is more and more applied in space camera, bring the full carbonization of camera support structure (being called for short full carbon structure camera), carbon fibre material temperature conductivity due to current domestic use is general lower, simultaneously space camera On orbit thermal environment is complicated, brings supporting construction to form larger thermograde in process in orbit.Main supporting structure, under uneven temperature field condition, forms uncontrollable temperature deformation, thus affects optical interval and reflecting mirror surface shape, causes the aberrations such as out of focus, causes camera imaging Quality Down.
Fig. 1 is the conventional thermal controls apparatus of truss-like main supporting structure, it comprises: camera support truss 1, film type electrical heater 2, because carbon fiber structural self temperature conductivity is lower, the thermograde that as easy as rolling off a log generation is larger in orbit, reduce temperature-controlled precision, therefore heating plate is generally designed to multiple heating circuit.On star, resource is nervous on the other hand, and along with the change of space camera yardstick is large, the drawback of this control mode is more and more obvious.So pass through the equivalent temperature conductivity of raising structure thus reduce heating circuit quantity, it is the key point solving problems.
The prior art the most close with the present invention is the application of carbon/carbon composite in space optical remote sensor heat control that the Wu Qingwen of Changchun Institute of Optics, Fine Mechanics and Physics, CAS " optical precision engineering " periodical of equaling to publish in Changchun Inst. of Optics and Fine Mechanics, Chinese Academy of Sciences for 2012 proposes.This design as shown in Figure 2, comprises the quick erecting frame 3 of star, carbon/carbon composite 4.Titanium alloy star sensor'support 3 because the heat of the quick generation of star is comparatively large, forms larger thermograde in work operational process, causes star sensor'support to produce temperature deformation, affects attitude measurement accuracy.By using the thick carbon/carbon composite 4 of 0.5mm, greatly improving the equivalent temperature conductivity of star sensor'support 3, reducing the thermograde of the quick erecting frame 3 of star, before and after using, thermograde is reduced to 5 DEG C from 28 DEG C, meets designing requirement.The shortcoming of this thermal control design method is: carbon/carbon composite 4 is thicker, belongs to semirigid structure, for the space camera of construction profile more complicated, especially columniform truss-frame structure, cannot implement, sole mass is comparatively large simultaneously, is not well positioned to meet the qualitative restrain of Lightweight Space camera.
Summary of the invention:
In order to overcome the defect that prior art exists, the object of the invention is to the equivalent temperature conductivity improving the fine structure of carbon, thus reduce the thermograde of camera support structure, improve the image quality of space camera particularly high-resolution space camera, a kind of light-duty robust thermal controls apparatus for carbon fiber main supporting structure camera of ad hoc meter.
In order to solve the problems of the technologies described above, technical scheme of the present invention is specific as follows:
For a light-duty robust thermal controls apparatus for carbon fiber main supporting structure camera, comprising: camera support truss, film type electrical heater, multiple high thermal conductivity fexible film, double-sided pressure-sensitive adhesive tape;
Described film type electrical heater is arranged on the outermost layer of described camera support truss;
Multiple high thermal conductivity fexible film, by splicing, is pasted on camera support truss with double-sided pressure-sensitive adhesive tape.
In technique scheme, be filled with single-component room-temperature-vulsilicone silicone rubber in the junction of high thermal conductivity fexible film splicing.
In technique scheme, the thickness of described high thermal conductivity fexible film is 25 μm ~ 100 μm.
In technique scheme, multiple described high thermal conductivity fexible film superposition is arranged on camera support truss.
The present invention has following beneficial effect:
Light-duty robust thermal controls apparatus for carbon fiber main supporting structure camera of the present invention, make full use of existing ripe thermal control technology and the high feature of PGS thermal conductivity of film, by pasting PGS film at space camera main supporting structure, effectively raise the equivalent temperature conductivity of the fine structure of carbon, overcome the lower main supporting structure brought of full carbon structure camera temperature conductivity in-orbit Orbital heat flux and well heater impact under, the technical barrier that thermograde is larger.The uneven Space Heat Flux that the hot-fluid produced by electric heater of PGS film and structure absorb diffuses to total main body, thus reduces the susceptibility of the internal Orbital heat flux of full carbon structure camera, improves the robustness of thermal design.
The present invention effectively reduces full carbon structure camera thermograde in-orbit, camera main supporting structure can be coordinated to carry out modularized production and assembling simultaneously, be particularly useful for, to the heat control system of the quick response satellite that camera robustness has higher requirements, providing a kind of technical foundation for space camera full carbon structure application raising simultaneously.
Accompanying drawing illustrates:
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail.
Fig. 1 is the low heat conductivity thermal control structural representation of existing truss-like main supporting structure;
Fig. 2 is another existing low heat conductivity structure thermal control structural representation;
Fig. 3 is the structural representation of the light-duty robust thermal controls apparatus for carbon fiber main supporting structure camera of the present invention;
Fig. 4 is the cross section structure schematic diagram of the light-duty robust thermal controls apparatus for carbon fiber main supporting structure camera shown in Fig. 3.
Embodiment:
Below in conjunction with accompanying drawing, the present invention is described in detail.
Light-duty robust thermal controls apparatus for carbon fiber main supporting structure camera of the present invention as shown in Figure 3, Figure 4, comprising: camera support truss 1, film type electrical heater 2, high thermal conductivity fexible film 5 (PyrolyticHighlyOrientedGraphiteSheet highly oriented pyrolytic graphite film) (hereinafter referred to as PGS film), double-sided pressure-sensitive adhesive tape 6, single-component room-temperature-vulsilicone silicone rubber 7.PGS film 5 is pasted on camera support truss 1 by double-sided pressure-sensitive adhesive tape 6, by the splicing of PGS film, complete the enforcement of camera main supporting structure, at the junction filled silicon rubber 7 of splicing, improve strength of joint, avoid limit, after silicon rubber 7 solidifies, film type electrical heater 2 can have been implemented by operation steps.
Principle of work illustrates: the thickness of PGS film 5 is 25 μm ~ 100 μm.Camera support truss 1 in orbit in process because diverse location absorbs hot-fluid difference that Orbital heat flux difference and electric heater 2 skewness cause by high thermal conductivity PGS film 5 and the thermal diffusion of himself, effectively improve the equivalent temperature conductivity of structure, thus the impact that reduction hot-fluid unevenness causes, also reduce the temperature fluctuation that it produces in operational process, because the thermal control scheme adopted is based on fexible film, can reduce the impact of Space Heat Flux variable effect and active heated device, therefore design has higher robustness simultaneously; The temperature conductivity of PGS film 5 is far above carbon fibre material on the other hand, and therefore, overall quality increase is less, is a kind of light-duty thermal control solution.
In other embodiment, PGS film also can stackablely use, to promote effect.
Obviously, above-described embodiment is only for clearly example being described, and the restriction not to embodiment.For those of ordinary skill in the field, can also make other changes in different forms on the basis of the above description.Here exhaustive without the need to also giving all embodiments.And thus the apparent change of extending out or variation be still among the protection domain of the invention.
Claims (4)
1. the light-duty robust thermal controls apparatus for carbon fiber main supporting structure camera, it is characterized in that, comprising: camera support truss (1), film type electrical heater (2), multiple high thermal conductivity fexible film (5), double-sided pressure-sensitive adhesive tape (6);
Described film type electrical heater (2) is arranged on the outermost layer of described camera support truss (1);
Multiple high thermal conductivity fexible film (5), by splicing, is pasted on camera support truss (1) with double-sided pressure-sensitive adhesive tape (6).
2. the light-duty robust thermal controls apparatus for carbon fiber main supporting structure camera according to claim 1, is characterized in that, be filled with single-component room-temperature-vulsilicone silicone rubber (7) in the junction that high thermal conductivity fexible film (5) splices.
3. the light-duty robust thermal controls apparatus for carbon fiber main supporting structure camera according to claim 1, is characterized in that, the thickness of described high thermal conductivity fexible film (5) is 25 μm ~ 100 μm.
4. the light-duty robust thermal controls apparatus for carbon fiber main supporting structure camera according to claim 1, is characterized in that, multiple described high thermal conductivity fexible film (5) superposition is arranged on camera support truss (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510962302.1A CN105549306A (en) | 2015-12-21 | 2015-12-21 | Light-weight robust thermal control apparatus used for carbon fiber main supporting structure camera |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510962302.1A CN105549306A (en) | 2015-12-21 | 2015-12-21 | Light-weight robust thermal control apparatus used for carbon fiber main supporting structure camera |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105549306A true CN105549306A (en) | 2016-05-04 |
Family
ID=55828580
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510962302.1A Pending CN105549306A (en) | 2015-12-21 | 2015-12-21 | Light-weight robust thermal control apparatus used for carbon fiber main supporting structure camera |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105549306A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109287010A (en) * | 2018-10-26 | 2019-01-29 | 中国科学院长春光学精密机械与物理研究所 | The heating means of carbon fibre composite support construction |
| CN110395411A (en) * | 2019-08-13 | 2019-11-01 | 中国科学院微小卫星创新研究院 | A kind of low rail remote sensing micro-nano satellite and its Thermal design |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2743875Y (en) * | 2004-10-28 | 2005-11-30 | 中国科学院长春光学精密机械与物理研究所 | Strucure of optical remote sensing camera frame |
| EP2530366A1 (en) * | 2011-06-01 | 2012-12-05 | Astrium SAS | Thermally insulating mattress and fixing process for such a blanket to a support |
| 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 |
| CN104210673A (en) * | 2014-09-19 | 2014-12-17 | 航天东方红卫星有限公司 | Thermal control method for star sensor assembly |
| CN104260899A (en) * | 2014-09-17 | 2015-01-07 | 上海卫星工程研究所 | High-adaptation truss temperature control method |
| 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 |
-
2015
- 2015-12-21 CN CN201510962302.1A patent/CN105549306A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2743875Y (en) * | 2004-10-28 | 2005-11-30 | 中国科学院长春光学精密机械与物理研究所 | Strucure of optical remote sensing camera frame |
| EP2530366A1 (en) * | 2011-06-01 | 2012-12-05 | Astrium SAS | Thermally insulating mattress and fixing process for such a blanket to a support |
| 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 |
| CN104260899A (en) * | 2014-09-17 | 2015-01-07 | 上海卫星工程研究所 | High-adaptation truss temperature control method |
| CN104210673A (en) * | 2014-09-19 | 2014-12-17 | 航天东方红卫星有限公司 | Thermal control method for star sensor assembly |
| 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 |
Non-Patent Citations (2)
| Title |
|---|
| 吴清文 等: "炭／炭复合材料在空间光学遥感器热控制中的应用", 《光学 精密工程》 * |
| 孔林 等: "轻型空间相机支撑桁架的精确控温", 《光学 精密工程》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109287010A (en) * | 2018-10-26 | 2019-01-29 | 中国科学院长春光学精密机械与物理研究所 | The heating means of carbon fibre composite support construction |
| CN110395411A (en) * | 2019-08-13 | 2019-11-01 | 中国科学院微小卫星创新研究院 | A kind of low rail remote sensing micro-nano satellite and its Thermal design |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104210673B (en) | A kind of thermal control method of the quick molectron of star | |
| CN103448920B (en) | The precise temperature control device of spaceborne star sensor | |
| Selvakumar et al. | Carbon nanotube-based tandem absorber with tunable spectral selectivity: transition from near-perfect blackbody absorber to solar selective absorber. | |
| CN104443441B (en) | Orbit transfer vehicle star sensor the is on the low side independent thermal controls apparatus of temperature | |
| CN103863581B (en) | A kind of indirect thermal controls apparatus for high-resolution optical remote sensing device precise temperature control | |
| CN106114912A (en) | GEO track Rotating Platform for High Precision Star Sensor high stable in-orbit points to ensuring method | |
| CN105301761B (en) | Two-dimensional deflection device and its deflection method based on thick piezoelectric fibre composite material | |
| CN102092487A (en) | Heat flow compensation method for ground simulation test on infrared heating cage of spacecraft | |
| CN103662088A (en) | Thermal control distribution method for star sensors of GEO (geostationary earth orbit) satellite | |
| CN105549306A (en) | Light-weight robust thermal control apparatus used for carbon fiber main supporting structure camera | |
| US20160109303A1 (en) | Honeycomb sandwich structure and method of manufacturing honeycomb sandwich structure | |
| CN107310756A (en) | A kind of infrared cage of skin Nano satellite hot-fluid | |
| US20110168231A1 (en) | Photovoltaic cell array with mechanical uncoupling of the cells from the carrier thereof | |
| Ding et al. | High-precision resin layer polishing of carbon fiber mirror based on optimized ion beam figuring process | |
| CN108528760A (en) | A kind of satellite top plate fining thermal design device | |
| Wang et al. | Investigations on the temperature warnings of the Alpha Magnetic Spectrometer on the International Space Station | |
| Steeves et al. | Ultra-thin highly deformable composite mirrors | |
| CN108531091B (en) | Hot melt adhesive film hot-pressing method for manufacturing large-area Micromegas detector | |
| CN107444677A (en) | The heating integrated structure of ray machine for multi-load high-precision joining | |
| CN110108272B (en) | Thermal design method of star sensor with stable temperature | |
| Silva et al. | Development of a real‐scale cooling module for a PV power plant | |
| Pepato et al. | The mechanics and cooling system of the ALICE silicon pixel detector | |
| Yang et al. | Thermal control of primary mirror of Space Solar Telescope | |
| CN104048991B (en) | A kind of radiant heater heat flow density transmission method | |
| Li et al. | Thermal design of detector for the solar X-Ray and extreme ultraviolet imager |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160504 |
|
| WD01 | Invention patent application deemed withdrawn after publication |