CN103662088B - A kind of star sensor thermal control layout method of GEO orbiter - Google Patents
A kind of star sensor thermal control layout method of GEO orbiter Download PDFInfo
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- CN103662088B CN103662088B CN201310612040.7A CN201310612040A CN103662088B CN 103662088 B CN103662088 B CN 103662088B CN 201310612040 A CN201310612040 A CN 201310612040A CN 103662088 B CN103662088 B CN 103662088B
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Abstract
A kind of star sensor thermal control layout method of GEO orbiter, step is: (A) installs ASTRO10 star sensor support (2) and APS star sensor support (3) respectively in the lower left corner of the outside face of the western plate of satellite capsule plate and the lower right corner, installs heat insulating mattress between attachment face; (B) ASTRO10 star sensor (5) is arranged on ASTRO10 star sensor support (2), APS star sensor (6) is arranged on APS star sensor support (3), between attachment face, smears heat-conducting silicone grease; (C) ASTRO10 star sensor thermal control cabin (1) is set with in the outside of ASTRO10 star sensor (5) and ASTRO10 star sensor support (2), be set with APS star sensor thermal control cabin (4) in the outside of APS star sensor (6) and APS star sensor support (3), between attachment face, heat insulating mattress be installed; (D) on the outside face in two thermal control cabins, aluminium sheet is installed, then on aluminium sheet, pastes second surface mirror.
Description
Technical field
The present invention relates to a kind of layout method of Satellite sensor, at all GEO orbiters the satellite configuring star sensor can apply.
Background technology
Star sensor is high-precision spacecraft attitude Sensitive Apparatus, is widely applied on low orbit satellite.Along with high rail satellite is to the proposition of autonomous control overflow in-orbit, GEO orbiter controls subsystem to start progressively to require that configuration star sensor is 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 the life cycle long and star sensor be arranged on outside celestial body all can be subject to the impact of the Orbital heat flux of alternation every day, therefore on GEO satellite, the working environment of star sensor is much more complicated than sun-synchronous orbit satellite, 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 country such as USA and Europe has had successful experience, APSTAR VI as developed based on SB4000 platform is configured with 2 star sensors, be arranged on thing plate outside face respectively, every platform star sensor is connected with cabin plate by complicated secondary structure.Secondary structure is made up 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 comparatively greatly, therefore it is very large at home GEO satellite to apply limitation.
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 the star sensor thermal control layout method compatible mutually with domestic GEO orbiter platform, the thermal environment that high rail satellite is severe can be met, 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) ASTRO10 star sensor support is installed in the lower left corner of the outside face of the western plate of satellite capsule plate, between attachment face, heat insulating mattress is installed; APS star sensor support is installed in the lower right corner of the outside face of the western plate of satellite capsule plate, between attachment face, heat insulating mattress is installed;
(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) be set with ASTRO10 star sensor thermal control cabin in the outside of ASTRO10 star sensor and ASTRO10 star sensor support, be set with APS star sensor thermal control cabin in the outside of APS star sensor and APS star sensor support; Between the attachment face of described ASTRO10 star sensor thermal control cabin or APS star sensor thermal control cabin and 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, pastes the silver-plated second surface mirror of cerium glass.
Described star sensor support or APS star sensor support are the shell spider form of magnesium alloy materials.
Described APS star sensor thermal control cabin or ASTRO10 star sensor thermal control cabin are the tower structure form of magnesium alloy materials, and tower structure form has the opening for dodging the quick probe visual field of star in the side of star sensor probe.
The optical-axis of described ASTRO10 star sensor and the angle of satellite X-axis be 97.34 °, be 31.50 ° with the angle of satellite Y-axis, be 120.44 ° with the angle of satellite Z axis; The positive dirction of described satellite X-axis points to satellite east plate, and the positive dirction of satellite Y-axis points to the southern plate of satellite, and the positive dirction of satellite Z axis is pointed to floor.
The optical-axis of described APS star sensor and the angle of satellite X-axis be 97.92 °, be 148.50 ° with the angle of satellite Y-axis, be 120.27 ° with the angle of satellite Z axis; The positive dirction of described satellite X-axis points to satellite east plate, and the positive dirction of satellite Y-axis points 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 good, the GEO orbiter configuring similar model star sensor can apply based on this platform all;
(2) the inventive method uses the heat dissipation design that the heat radiation of star sensor'support conduction-type and thermal control cabin radial-type heat dissipating combine, have passed through the examination of qualification level thermal balance test, under each operating mode, the temperature of star sensor end of lifetime is 29 DEG C, in operating temperature, the surplus of existence 11 DEG C, can be applied in the device layout of configuration complexity;
(3) in the inventive method, the shell triangle posture casting magnesium bracket used is lightweight, be only 0.57Kg, APSTAR VI star sensor weight support frame is about 4.5Kg, at double alleviate weight, stiffness of support and precision hold facility are after qualification level mechanical test, and the change of star sensor all directions precision is all less than 0.01 °, the requirement of DFH-4 Platform Satellite mechanical environment can be met, can as the design reference of relevant device support;
(4) in the inventive method, the star sensor thermal control cabin weight used is 3.76Kg, heat loss through radiation mode is adopted to substitute heat pipe for conductive heat dissipation mode completely, configuration is simple, easy for installation, solve the shortcoming that heat pipe for conductive heat dissipation mode cost is high, setting accuracy requirement is high, assembling is complicated, after qualification level mechanical test, the requirement of DFH-4 Platform Satellite mechanical environment can be met.
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 installing schematic diagram;
Fig. 3 is ASTRO10 star sensor of the present invention and support installing schematic diagram;
Fig. 4 is APS star sensor of the present invention and ASTRO10 star sensor blinding analysis schematic diagram;
Fig. 5 is APS star sensor of the present invention and ASTRO10 star sensor field of view axis Orientation schematic diagram.
Detailed description of the invention
As shown in Fig. 1 (a), Fig. 1 (b), the star sensor layout method of GEO orbiter of the present invention, the hardware device related 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, heat-conducting silicone grease is smeared between attachment face, ASTRO10 star sensor support 2 is arranged on the lower left corner (western plate and northern plate, intersection location) to floor of the outside face of the western plate of satellite capsule plate, between attachment face, heat insulating mattress is installed, ASTRO10 star sensor 5 and ASTRO10 star sensor support 2 are co-located in ASTRO10 star sensor thermal control cabin 1, install heat insulating mattress between ASTRO10 star sensor thermal control cabin 1 and cabin plate (western plate) outside face.
APS star sensor 6 is arranged on APS star sensor support 3, heat-conducting silicone grease is smeared between attachment face, APS star sensor support 3 is arranged on the lower right corner (western plate and southern plate, intersection location) to floor of the outside face of the western plate of satellite capsule plate, between attachment face, heat insulating mattress is installed, APS star sensor 6 and APS star sensor support 3 are co-located in APS star sensor thermal control cabin 4, install heat insulating mattress between APS star sensor thermal control cabin 4 and satellite capsule plate (western plate) outside face.
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 magnesium alloy (trade mark: casting magnesium ZMAL8ZnQJ168-85), and processing mode is casting, act as the quick installation of Spanning Star, ensures the quick sensing of star.Star sensor to be contacted with star sensor attachment face by support and carries out thermal conductivity heat radiation.APS star sensor thermal control cabin 4 and ASTRO10 star sensor thermal control cabin 1 all adopt tower structure form, and framework size needs to install star sensor and support thereof in inside, thermal control cabin.There is opening in thermal control cabin in star sensor probe side, for dodging the quick probe visual field of star.Thermal control cabin receptacle material is magnesium alloy (trade mark: casting magnesium ZMAL8ZnQJ168-85), processing mode is casting, framework outside face installs thin aluminum sheet, and aluminium sheet outside face pastes 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, for ASTRO10 star sensor visual field, time in-orbit, solar motion scope is between first point of Capricornus and first point of cancer, and definition satellite east side is satellite X-direction, satellite southern side is satellite Y direction, satellite in-orbit time be satellite Z-direction to direction, ground, from satellite, sunshine and XZ plane (plane normal orientation is Y-axis) ° interval, angle ± 23.5, after taking into account biased 2 ° of satellite attitude, be increased to ± 25.5 °.Consider that star sensor carries semi-cone angle 30 ° of scopes of shade, and celestial body and solar wing can not block star sensor and block, Y-axis should not be exceeded, then the axial angular range in star sensor visual field is becoming 30 ° ~ 34.5 ° intervals with Y-axis, consider sun visual angle (half cone 0.3 °), the axis of rolling ± 0.06 °, general assembly, test, satellite attitude equal error in Satellite Attitude control precision, star sensor field of view axis direction scope needs to narrow further.
By analyzing above and considering satellite practical layout situation, determine the optical-axis of two star sensors and satellite XYZ axle clamp angle 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 be not described in detail in specification sheets of the present invention belongs to the known technology of those skilled in the art.
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 satellite capsule plate western plate, ASTRO10 star sensor support (2) is installed, between attachment face, heat insulating mattress is installed; In the lower right corner of the outside face of satellite capsule plate western plate, APS star sensor support (3) is installed, between attachment face, heat insulating mattress is installed;
(B) ASTRO10 star sensor (5) is arranged on ASTRO10 star sensor support (2), between attachment face, smears heat-conducting silicone grease; APS star sensor (6) is arranged on APS star sensor support (3), between attachment face, smears heat-conducting silicone grease;
(C) be set with ASTRO10 star sensor thermal control cabin (1) in the outside of ASTRO10 star sensor (5) and ASTRO10 star sensor support (2), be set with APS star sensor thermal control cabin (4) in the outside of APS star sensor (6) and APS star sensor support (3); Between described ASTRO10 star sensor thermal control cabin (1) or the attachment face of APS star sensor thermal control cabin (4) and 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, pastes 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: the shell spider form that described ASTRO10 star sensor support (2) or APS star sensor support (3) are 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: the tower structure form that described APS star sensor thermal control cabin (4) or ASTRO10 star sensor thermal control cabin (1) are magnesium alloy materials, tower structure form has the opening for dodging the quick probe visual field of star in the 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 optical-axis of ASTRO10 star sensor (5) and the angle of satellite X-axis be 97.34 °, be 31.50 ° with the angle of satellite Y-axis, be 120.44 ° with the angle of satellite Z axis; The positive dirction of described satellite X-axis points to satellite east plate, and the positive dirction of satellite Y-axis points 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 optical-axis of APS star sensor (6) and the angle of satellite X-axis be 97.92 °, be 148.50 ° with the angle of satellite Y-axis, be 120.27 ° with the angle of satellite Z axis; The positive dirction of described satellite X-axis points to satellite east plate, and the positive dirction of satellite Y-axis points to the southern plate of satellite, and the positive dirction of satellite Z axis is pointed to floor.
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| 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 |
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