CN103662088A - Thermal control distribution method for star sensors of GEO (geostationary earth orbit) satellite - Google Patents
Thermal control distribution method for star sensors of GEO (geostationary earth orbit) satellite Download PDFInfo
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- CN103662088A CN103662088A CN201310612040.7A CN201310612040A CN103662088A CN 103662088 A CN103662088 A CN 103662088A CN 201310612040 A CN201310612040 A CN 201310612040A CN 103662088 A CN103662088 A CN 103662088A
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Abstract
A thermal control distribution method for star sensors of a GEO (geostationary earth orbit) satellite comprises the following steps of (A) respectively mounting an ASTRO10 star sensor support (2) and an APS star sensor support (3) at a left lower corner and a right lower corner of an outer surface of a west board of a deck of the satellite, and mounting a thermal insulation pad between mounting surfaces; (B) mounting an ASTRO10 star sensor (5) on the ASTRO10 star sensor support (2), mounting an APS star sensor (6) on the APS star sensor support (3), and coating heat-conduction silicon grease between mounting surfaces; (C) sleeving an ASTRO10 star sensor thermal control cabin (1) on the outer sides of the ASTRO10 star sensor (5) and the ASTRO10 star sensor support (2), sleeving an APS star sensor thermal control cabin (4) on the outer sides of the APS star sensor (6) and the APS star sensor support (3), and mounting a thermal insulation pad between mounting surfaces; and (D) mounting aluminum plates on the outer surfaces of the two thermal control cabins, and then adhering secondary surface mirrors to the aluminum plates.
Description
Technical field
The present invention relates to a kind of layout method of Satellite sensor, can and configure on the satellite of star sensor at all GEO orbiters and apply.
Background technology
Star sensor is high-precision spacecraft attitude Sensitive Apparatus, on low orbit satellite, is widely applied.Along with high rail satellite is to the proposition requiring from master control in-orbit, GEO orbiter is controlled subsystem and is started progressively to require to configure star sensor as attitude measurement device.
Sun-synchronous orbit satellite star sensor is arranged in the shade, substantially do not shined upon, and GEO orbiter in-orbit life cycle star sensor long and that be arranged on outside celestial body all can be subject to the impact of the outer hot-fluid of alternation every day, therefore on GEO satellite the working environment of star sensor than sun-synchronous orbit satellite complexity many, therefore the layout method of low orbit satellite star sensor does not possess reference value on GEO orbiter.The application of the GEO orbiter star sensor of the countries such as USA and Europe has had successful experience, as the APSTAR VI based on the development of SB4000 platform has configured 2 star sensors, be arranged on respectively thing plate outside face, every star sensor is connected with cabin plate by complicated secondary structure.Secondary structure is comprised of connecting bottom board, star sensor stay bearing plate and thermal diffusion plate, star sensor stay bearing plate and thermal diffusion plate are connected with connecting bottom board by screw, between star sensor stay bearing plate and thermal diffusion plate, heat pipe is installed, the hear rate that star sensor work produces is passed to heat radiator by curved hot pipe, design is comparatively complicated, simultaneously due to SB4000 platform and domestic GEO orbiter platform configuration difference larger, therefore it is very large to apply limitation on GEO satellite at home.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, provide that a kind of configuration is simple, reliability is high and with domestic GEO orbiter platform compatible star sensor thermal control layout method mutually, can meet the severe thermal environment of high rail satellite, for the general assembly of satellite and thermal control design create good conditions.
Technical solution of the present invention is: a kind of star sensor thermal control layout method of GEO orbiter, and step is as follows:
(A) in the lower left corner of the outside face of the western plate of satellite capsule plate, ASTRO10 star sensor support is installed, heat insulating mattress is installed between attachment face; In the lower right corner of the outside face of the western plate of satellite capsule plate, APS star sensor support is installed, heat insulating mattress is installed between attachment face;
(B) ASTRO10 star sensor is arranged on ASTRO10 star sensor support, between attachment face, smears heat-conducting silicone grease; APS star sensor is arranged on APS star sensor support, between attachment face, smears heat-conducting silicone grease;
(C) in suit ASTRO10 star sensor thermal control cabin, the outside of ASTRO10 star sensor and ASTRO10 star sensor support, in suit APS star sensor thermal control cabin, the outside of APS star sensor and APS star sensor support; Between described ASTRO10 star sensor thermal control cabin or APS star sensor thermal control cabin and the attachment face of the western plate of satellite capsule plate, heat insulating mattress is installed;
(D) on the outside face in described ASTRO10 star sensor thermal control cabin or APS star sensor thermal control cabin, aluminium sheet is installed, then on the outside face of aluminium sheet, is pasted the silver-plated second surface mirror of cerium glass.
The shell spider form that described star sensor support or APS star sensor support are magnesium alloy materials.
The tower structure form that described APS star sensor thermal control cabin or ASTRO10 star sensor thermal control cabin are magnesium alloy materials, tower structure form is useful on the opening of dodging the quick probe of star visual field in a side of star sensor probe.
The visual field optical axis of described ASTRO10 star sensor and the angle of satellite X-axis be 97.34 °, with the angle of satellite Y-axis be 31.50 °, with the angle of satellite Z axis be 120.44 °; The positive dirction of described satellite X-axis is pointed to satellite east plate, and the positive dirction of satellite Y-axis is pointed to the southern plate of satellite, and the positive dirction of satellite Z axis is pointed to floor.
The visual field optical axis of described APS star sensor and the angle of satellite X-axis be 97.92 °, with the angle of satellite Y-axis be 148.50 °, with the angle of satellite Z axis be 120.27 °; The positive dirction of described satellite X-axis is pointed to satellite east plate, and the positive dirction of satellite Y-axis is pointed to the southern plate of satellite, and the positive dirction of satellite Z axis is pointed to floor.
The present invention's advantage is compared with prior art:
(1) star sensor thermal control layout method of the present invention and domestic large-scale long life geostationary orbit satellite platform compatibility are good, can be all based on this platform and configure on the GEO orbiter of similar model star sensor and apply;
(2) the inventive method is used the heat dissipation design that the heat radiation of star sensitive stent conduction-type and thermal control cabin radial-type heat dissipating combine, through the examination of evaluation level thermal balance test, under each operating mode, the temperature of star sensor end of lifetime is 29 ℃, surplus apart from 11 ℃ of existences in operating temperature, can be applied in the device layout of configuration complexity;
(3) in the inventive method, the shell triangle posture casting magnesium bracket using is lightweight, be only 0.57Kg, APSTAR VI star sensor weight support frame is about 4.5Kg, at double alleviated weight, stiffness of support and precision hold facility be through evaluation after level mechanical test, star sensor all directions precision changes and is all less than 0.01 °, can meet the requirement of DFH-4 platform satellite mechanical environment, can be used as the design reference of relevant device support;
(4) in the inventive method, the star sensor thermal control cabin weight of using is 3.76Kg, adopt heat loss through radiation mode to substitute heat pipe for conductive heat dissipation mode completely, configuration is simple, easy for installation, solved that heat pipe for conductive heat dissipation mode cost is high, setting accuracy require high, assemble complicated shortcoming, through identifying after level mechanical test, can meet the requirement of DFH-4 platform satellite mechanical environment.
Accompanying drawing explanation
Fig. 1 is APS star sensor of the present invention and ASTRO10 star sensor schematic layout pattern;
Fig. 2 is APS star sensor of the present invention and support scheme of installation;
Fig. 3 is ASTRO10 star sensor of the present invention and support scheme of installation;
Fig. 4 is that schematic diagram is analyzed in APS star sensor of the present invention and ASTRO10 star sensor visual field;
Fig. 5 is APS star sensor of the present invention and ASTRO10 star sensor field of view axis Orientation schematic diagram.
The specific embodiment
As shown in Fig. 1 (a), Fig. 1 (b), the star sensor layout method of GEO orbiter of the present invention, the hardware device relating to mainly comprises ASTRO10 star sensor 5, APS star sensor 6, ASTRO10 star sensor support 2, APS star sensor support 3, ASTRO10 star sensor thermal control cabin 1, APS star sensor thermal control cabin 4, heat insulating mattress, heat-conducting silicone grease.
Wherein, ASTRO10 star sensor 5 is arranged on ASTRO10 star sensor support 2, between attachment face, smear heat-conducting silicone grease, ASTRO10 star sensor support 2 is arranged on the lower left corner (western plate and northern plate, the intersection location to floor) of the outside face of the western plate of satellite capsule plate, heat insulating mattress is installed between attachment face, ASTRO10 star sensor 5 and ASTRO10 star sensor support 2 are co-located in ASTRO10 star sensor thermal control cabin 1, between ASTRO10 star sensor thermal control cabin 1 and cabin plate (western plate) outside face, heat insulating mattress are installed.
As shown in Figure 2 and Figure 3.APS star sensor support 3 and ASTRO10 star sensor support 2 all adopt shell spider form, and material is that (trade mark: casting magnesium ZMAL8ZnQJ168-85), processing mode is casting, act as the quick installation of Spanning Star, guarantees the quick sensing of star magnesium alloy.Star sensor is contacted with star sensor attachment face and is carried out hot conduction-type heat radiation by support.APS star sensor thermal control cabin 4 and ASTRO10 star sensor thermal control cabin 1 all adopt tower structure form, and framework size needs star sensor and support thereof to be installed in inside, thermal control cabin.There is opening in thermal control cabin in star sensor probe one side, for dodging the quick probe of star visual field.Thermal control cabin receptacle material is the magnesium alloy (trade mark: casting magnesium ZMAL8ZnQJ168-85), processing mode is casting, framework outside face is installed thin aluminum sheet, and aluminium sheet outside face is pasted the silver-plated second surface mirror of cerium glass (OSR), and star sensor carries out heat radiation type heat radiation by star sensor thermal control cabin.
As shown in Figure 4, Figure 5, take ASTRO10 star sensor visual field is example, in the time of in-orbit, solar motion scope is at first point of Capricornus and between the first point of cancer, and definition satellite east side is satellite X-direction, satellite southern side is satellite Y direction, satellite is satellite Z-direction to ground direction in-orbit time, from satellite, and sunshine and XZ plane (plane normal orientation is Y-axis) ° interval, angle ± 23.5, take into account satellite attitude and setover after 2 °, be increased to ± 25.5 °.Consider that star sensor carries 30 ° of scopes of semi-cone angle of shade, and celestial body and the sun wing can not block star sensor and block, should not surpass Y-axis, the axial angular range in star sensor visual field is becoming 30 °～34.5 ° intervals with Y-axis, consider in sun visual angle (0.3 ° of half cone), Satellite Attitude control precision the axis of rolling ± 0.06 °, general assembly, test, satellite attitude equal error, star sensor field of view axis direction scope need to further narrow.
By analyzing above and considering satellite practical layout situation, determine that the visual field optical axis of two star sensors and satellite XYZ axle clamp angle are as shown in the table:
| ? | X | Y | Z |
| ASTRO10 star sensor optical axis | 97.34° | 31.50° | 120.44° |
| APS star sensor optical axis | 97.92° | 148.50° | 120.27° |
Satellite is star sensor start work during GEO track, and the hear rate of generation is delivered to star sensor thermal control cabin by star sensor and star sensor support assembly in thermal radiation mode, then is distributed in thermal radiation mode by star sensor thermal control cabin.
The content not being described in detail in specification sheets of the present invention belongs to those skilled in the art's known technology.
Claims (5)
1. a star sensor thermal control layout method for GEO orbiter, is characterized in that step is as follows:
(A) in the lower left corner of the outside face of the western plate of satellite capsule plate, ASTRO10 star sensor support (2) is installed, heat insulating mattress is installed between attachment face; APS star sensor support (3) is installed in the lower right corner at the outside face of the western plate of satellite capsule plate, and heat insulating mattress is installed between attachment face;
(B) ASTRO10 star sensor (5) is arranged on to ASTRO10 star sensor support (2) above, between attachment face, smears heat-conducting silicone grease; APS star sensor (6) is arranged on to APS star sensor support (3) upper, between attachment face, smears heat-conducting silicone grease;
(C) in suit ASTRO10 star sensor thermal control cabin (1), the outside of ASTRO10 star sensor (5) and ASTRO10 star sensor support (2), in suit APS star sensor thermal control cabin (4), the outside of APS star sensor (6) and APS star sensor support (3); Between described ASTRO10 star sensor thermal control cabin (1) or APS star sensor thermal control cabin (4) and the attachment face of the western plate of satellite capsule plate, heat insulating mattress is installed;
(D) on the outside face in described ASTRO10 star sensor thermal control cabin (1) or APS star sensor thermal control cabin (4), aluminium sheet is installed, then on the outside face of aluminium sheet, is pasted the silver-plated second surface mirror of cerium glass.
2. the star sensor thermal control layout method of a kind of GEO orbiter according to claim 1, is characterized in that: described star sensor support (2) or APS star sensor support (3) are the shell spider form of magnesium alloy materials.
3. the star sensor thermal control layout method of a kind of GEO orbiter according to claim 1, it is characterized in that: described APS star sensor thermal control cabin (4) or ASTRO10 star sensor thermal control cabin (1) are the tower structure form of magnesium alloy materials, tower structure form is useful on the opening of dodging the quick probe of star visual field in a side of star sensor probe.
4. the star sensor thermal control layout method of a kind of GEO orbiter according to claim 1, is characterized in that: the described visual field optical axis of ASTRO10 star sensor (5) and the angle of satellite X-axis be 97.34 °, with the angle of satellite Y-axis be 31.50 °, with the angle of satellite Z axis be 120.44 °; The positive dirction of described satellite X-axis is pointed to satellite east plate, and the positive dirction of satellite Y-axis is pointed to the southern plate of satellite, and the positive dirction of satellite Z axis is pointed to floor.
5. the star sensor thermal control layout method of a kind of GEO orbiter according to claim 1, is characterized in that: the described visual field optical axis of APS star sensor (6) and the angle of satellite X-axis be 97.92 °, with the angle of satellite Y-axis be 148.50 °, with the angle of satellite Z axis be 120.27 °; The positive dirction of described satellite X-axis is pointed to satellite east plate, and the positive dirction of satellite Y-axis is pointed to the southern plate of satellite, and the positive dirction of satellite Z axis is pointed to floor.
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103984192A (en) * | 2014-05-29 | 2014-08-13 | 中国科学院光电技术研究所 | Space camera and achieving method thereof suitable for deep space exploration high-temperature work environment |
| 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 |
| CN104443435A (en) * | 2014-11-21 | 2015-03-25 | 上海卫星工程研究所 | Star sensor mounting structure for thermal deformation isolation and control |
| CN104729503A (en) * | 2015-03-17 | 2015-06-24 | 中国空间技术研究院 | Rod-type supporting structure earth sensor support |
| CN107600460A (en) * | 2017-07-27 | 2018-01-19 | 上海卫星工程研究所 | A kind of cryogenic opticses satellite configuration being applied under the conditions of big oval Frozen Orbit complex illumination |
| CN108489481A (en) * | 2018-03-29 | 2018-09-04 | 北京航天控制仪器研究所 | A kind of photo sensitive device refrigeration cool-down align structures for star sensor |
| CN108759821A (en) * | 2018-06-14 | 2018-11-06 | 上海卫星工程研究所 | A kind of multiple star sensor configurations of GEO satellite |
| CN108791958A (en) * | 2018-06-15 | 2018-11-13 | 上海卫星工程研究所 | Star sensor illumination adapts to heat control device entirely |
| CN108820259A (en) * | 2018-06-25 | 2018-11-16 | 上海卫星工程研究所 | A kind of whole temperature barrier being adapted to the outer rotating mechanism multi-dimensional movement of star |
| CN109413964A (en) * | 2018-12-14 | 2019-03-01 | 北京无线电测量研究所 | A kind of and integrated spaceborne phase array radar load of satellite platform structure thermal control |
| CN111301718A (en) * | 2020-03-10 | 2020-06-19 | 上海卫星工程研究所 | Storage battery pack insulation installation and implementation method for spacecraft |
| CN114408221A (en) * | 2022-01-19 | 2022-04-29 | 上海卫星工程研究所 | Satellite-used satellite-sensitive temperature control system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN104443441B (en) * | 2014-10-31 | 2016-07-27 | 上海卫星工程研究所 | Orbit transfer vehicle star sensor the is on the low side independent thermal controls apparatus of temperature |
| CN104443435A (en) * | 2014-11-21 | 2015-03-25 | 上海卫星工程研究所 | Star sensor mounting structure for thermal deformation isolation and control |
| CN104443435B (en) * | 2014-11-21 | 2016-06-29 | 上海卫星工程研究所 | For the star sensor mounting structure being thermomechanically separated and control |
| CN104729503A (en) * | 2015-03-17 | 2015-06-24 | 中国空间技术研究院 | Rod-type supporting structure earth sensor support |
| CN104729503B (en) * | 2015-03-17 | 2017-11-07 | 中国空间技术研究院 | A kind of flow resistance of rod-support structure earth sensor support |
| CN107600460A (en) * | 2017-07-27 | 2018-01-19 | 上海卫星工程研究所 | A kind of cryogenic opticses satellite configuration being applied under the conditions of big oval Frozen Orbit complex illumination |
| CN108489481A (en) * | 2018-03-29 | 2018-09-04 | 北京航天控制仪器研究所 | A kind of photo sensitive device refrigeration cool-down align structures for star sensor |
| CN108759821A (en) * | 2018-06-14 | 2018-11-06 | 上海卫星工程研究所 | A kind of multiple star sensor configurations of GEO satellite |
| CN108791958A (en) * | 2018-06-15 | 2018-11-13 | 上海卫星工程研究所 | Star sensor illumination adapts to heat control device entirely |
| CN108820259A (en) * | 2018-06-25 | 2018-11-16 | 上海卫星工程研究所 | A kind of whole temperature barrier being adapted to the outer rotating mechanism multi-dimensional movement of star |
| CN109413964A (en) * | 2018-12-14 | 2019-03-01 | 北京无线电测量研究所 | A kind of and integrated spaceborne phase array radar load of satellite platform structure thermal control |
| CN111301718A (en) * | 2020-03-10 | 2020-06-19 | 上海卫星工程研究所 | Storage battery pack insulation installation and implementation method for spacecraft |
| CN114408221A (en) * | 2022-01-19 | 2022-04-29 | 上海卫星工程研究所 | Satellite-used satellite-sensitive temperature control system |
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