CN114180104A - High-precision temperature control device of space optical remote sensing satellite star sensor - Google Patents
High-precision temperature control device of space optical remote sensing satellite star sensor Download PDFInfo
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- CN114180104A CN114180104A CN202111658327.4A CN202111658327A CN114180104A CN 114180104 A CN114180104 A CN 114180104A CN 202111658327 A CN202111658327 A CN 202111658327A CN 114180104 A CN114180104 A CN 114180104A
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- 239000004642 Polyimide Substances 0.000 claims description 8
- 230000017525 heat dissipation Effects 0.000 claims description 8
- 229920001721 polyimide Polymers 0.000 claims description 8
- 239000003973 paint Substances 0.000 claims description 5
- 239000004519 grease Substances 0.000 claims description 4
- 229920001296 polysiloxane Polymers 0.000 claims description 4
- 230000005855 radiation Effects 0.000 claims description 4
- 230000003647 oxidation Effects 0.000 claims description 3
- 238000007254 oxidation reaction Methods 0.000 claims description 3
- 229920000728 polyester Polymers 0.000 claims description 3
- 229920006267 polyester film Polymers 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims 1
- 229910052782 aluminium Inorganic materials 0.000 claims 1
- 238000000034 method Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 3
- 238000005265 energy consumption Methods 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
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- 238000004381 surface treatment Methods 0.000 description 2
- 238000002076 thermal analysis method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000003384 imaging method Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 229920002379 silicone rubber Polymers 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/36—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors
- B64G1/361—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors using star sensors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
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Abstract
The invention relates to the technical field of aerospace thermal control, in particular to a high-efficiency and high-precision temperature control device for a space optical remote sensing satellite star sensor, which is used for effectively solving the problem of temperature stability of the high-precision star sensor carried on a space optical remote sensing load. The star sensor component bracket can be connected with the space optical remote sensing load main body frame; the star sensor bases are connected to the star sensor component support, and the extending direction of the star sensor bases is determined according to the direction of the optical axis of each star sensor; each star sensor base is mechanically connected with a star sensor support in a heat insulation mode so as to reduce the thermal disturbance of the temperature change of the star sensor support to the star sensor base; the high-precision control of the star sensor flange can be realized, the complexity of a thermal control system is greatly simplified, and the method is safe and reliable.
Description
Technical Field
The invention relates to the technical field of aerospace thermal control, in particular to a high-efficiency and high-precision temperature control device for a space optical remote sensing satellite star sensor.
Background
In the existing mode, a star sensor is a key component for controlling the attitude of a satellite and provides important data for correcting the attitude of the satellite. When the star sensor works on the track, the star sensor faces violent external heat flow change, the heat deformation of an optical system can generate defocusing amount change, the pointing stability of the star sensor is influenced, and for a high-precision star sensor, effective measures must be taken to control the heat deformation of the star sensor.
The pointing stability and the attitude stability of the space optical remote sensing satellite have extremely important influence on the imaging quality. At present, the performance index of the space optical remote sensing load is continuously improved, the requirement on the accuracy of attitude control is more severe, and the star sensor is gradually changed from being carried on a satellite platform to being directly carried on the space optical remote sensing load. Because the temperature control precision requirement of the space optical remote sensing load is very high, the temperature level of the star sensor is effectively controlled, and simultaneously, the temperature level and the temperature change of the star sensor need to be controlled to thermally disturb the optical remote sensor.
In addition, the energy supply capacity of the loads of the medium and small satellites is limited, the thermal control system is a system which works in orbit for a long time and needs continuous and stable energy supply, particularly when the satellites run to a shadow area, the solar panels of the satellites are not input with energy, and the power consumption required by the thermal control system is remarkably increased, so that the realization of the thermal control with high efficiency and low energy consumption is of great significance.
In conclusion, the high-efficiency and high-precision thermal control of the star sensor component has important application value.
Disclosure of Invention
The technical problems solved by the invention are as follows: the integrated star sensor is characterized in that the integrated star sensor is safer, more reliable and high in integrated thermal control degree, is remarkably different from the common design modes that the existing radiator, a heat pipe and a light shield are provided with radiating surfaces, and the like, and is used for effectively solving the problem of temperature stability of the high-precision star sensor loaded on a space optical remote sensing load, and mainly solving the problem of temperature control of a star sensor flange and simultaneously meeting the requirement of low thermal control energy consumption; therefore, the invention provides a high-efficiency high-precision temperature control device for a space optical remote sensing satellite star sensor.
In order to solve the technical problems, the technical scheme of the invention is as follows:
a space optical remote sensing satellite star sensor high-precision temperature control device comprises:
the star sensor assembly support 11 can be connected with the space optical remote sensing load main body frame;
a plurality of star sensor bases 12 connected to the star sensor module holder 11 and having an extending direction determined according to the optical axis direction of each star sensor 10;
each star sensor base 12 is mechanically connected with a star sensor support 13 in a heat insulation manner so as to reduce the thermal disturbance of the temperature change of the star sensor support 13 on the star sensor base 12;
each star sensor 10 is mounted on a corresponding star sensor support 13, and a mounting surface is formed between the star sensor support 13 and the star sensor support, and the mounting surface is subjected to surface treatment according to preset precision and is coated with heat-conducting silicone grease.
Preferably, the heat insulation mode is as follows: an annular titanium alloy heat insulation pad 14 is arranged between the star sensor support 13 and the star sensor base 12 for heat insulation, and the annular titanium alloy heat insulation pad 14 is provided with a mounting point for mechanical connection.
Preferably, the heat insulation mode is as follows: a plurality of layers of heat insulation components 17 are laid between the star sensor support 13 and the star sensor base 12 at positions between mounting points, so that the thermal disturbance of the temperature change of the star sensor support 13 to the star sensor base 12 is further prevented;
the multi-layer heat insulation assembly 17 is composed of a double-sided aluminum-plated polyester film and a polyester net.
Further, each star sensor 10 is connected with the star sensor support 13 through a flange plate.
Further, the star sensor support 13 is a hollow thin-wall cylinder with a beam inside;
and the top surface and the bottom surface of the beam and the mounting surface of the star sensor support 13 are processed according to a second preset processing precision requirement.
Further, the outer surface of the star sensor holder 13 is coated with white paint so that the outer surface of the star sensor holder 13 can be used as a heat dissipation surface.
Further, the star sensor 10 includes:
and a reserved gap is kept between the star sensor circuit box 24 and the cross beam, and the reserved gap is filled with an insulating heat conduction pad.
Further, black anodic oxidation treatment is carried out on the outer surface of the star sensor circuit box 24 and the inner surface of the star sensor support 13 so as to strengthen mutual radiation heat exchange.
Further, the star sensor 10 includes:
the electric heater 15 is arranged on the bottom surface of the beam inside the star sensor support 13;
and the temperature control point thermistor 16 is connected with the electric heater 15, and the temperature control point thermistor 16 is arranged on the circumferential direction of the flange plate 23 of the star sensor 10.
Further, the star sensor 10 includes:
the star sensor light shield front section 21 and the star sensor light shield rear section 22 are connected in sequence;
the star sensor light shield rear section 22 is connected with the flange plate 23
Polyimide heat insulation pads 25 are respectively arranged between the front section 21 of the star sensor light shield and the rear section 22 of the star sensor light shield, and between the rear section 22 of the star sensor light shield and the flange plate 23.
The invention has the following beneficial effects:
by adopting the technical scheme, the high-precision control of the star sensor flange within the temperature variation range of 10 +/-2 ℃ can be realized; compared with the prior art, the heat dissipation surface can be effectively reduced, the thermal compensation power consumption is reduced, and especially the heat consumption of the star sensor circuit box can be guided to the flange plate in the shadow area to be used as the thermal compensation power consumption, so that the thermal compensation power consumption is further reduced, and the satellite energy is saved; the star sensor support integrates the functions of structural support, heat dissipation, thermal compensation and the like, greatly simplifies the complexity of a thermal control system, and is safe and reliable.
Drawings
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
FIG. 1 is a schematic structural diagram of a high-precision temperature control device for a star sensor provided by the invention;
FIG. 2 is a schematic view of the construction of the star sensor assembly;
FIG. 3 is a schematic structural diagram of a star sensor support;
FIG. 4 is a schematic diagram of the internal structural configuration of the star sensor support.
The reference numerals in the figures denote:
the star sensor assembly comprises a star sensor assembly bracket 11, a star sensor base 12, a star sensor 10 and a star sensor support 13;
an annular titanium alloy heat insulation pad 14, a multi-layer heat insulation assembly 17 and a cross beam 18;
the star sensor circuit box 24;
an electric heater 15, a temperature control point thermistor 16;
the star sensor light shield comprises a front star sensor light shield section 21, a rear star sensor light shield section 22, a flange plate 23 and a polyimide heat insulation pad 25.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments of the present invention without any creative effort belong to the protection scope of the present invention; for convenience of description, in the present application, "left side" is "first end", "right side" is "second end", "upper side" is "first end", and "lower side" is "second end" in the current view, so that the description is for the purpose of clearly expressing the technical solution, and should not be construed as an improper limitation to the technical solution of the present application.
The integrated star sensor is characterized in that the integrated star sensor is safer, more reliable and high in integrated thermal control degree, is remarkably different from the common design modes that the existing radiator, a heat pipe and a light shield are provided with radiating surfaces, and the like, and is used for effectively solving the problem of temperature stability of the high-precision star sensor loaded on a space optical remote sensing load, and mainly solving the problem of temperature control of a star sensor flange and simultaneously meeting the requirement of low thermal control energy consumption; therefore, the invention provides a high-efficiency high-precision temperature control device for a space optical remote sensing satellite star sensor.
Specifically, referring to fig. 1, the high-precision temperature control device for the space optical remote sensing satellite star sensor includes:
the star sensor component support 11 can be connected with a space optical remote sensing load main body frame; the star sensor bases 12 are connected to the star sensor component support 11, and the extending direction of the star sensor bases is determined according to the direction of the optical axis of each star sensor 10; each star sensor base 12 is mechanically connected with a star sensor support 13 in a heat insulation manner so as to reduce the thermal disturbance of the temperature change of the star sensor support 13 to the star sensor base 12; each star sensor 10 is mounted on a corresponding star sensor support 13, and a mounting surface is formed between the star sensor 10 and the corresponding star sensor support 13, and the mounting surface is subjected to surface treatment according to a preset precision and is coated with heat-conducting silicone grease.
In the technical scheme, a star sensor assembly bracket 11 is directly and mechanically connected with a space optical remote sensing load main body frame, wherein a star sensor base 12 is a transition piece and is determined according to the direction of an optical axis of each star sensor, and a star sensor support 13 is mechanically connected with the star sensor base through a titanium alloy heat insulation pad; each star sensor is arranged on a corresponding support through a flange plate, the mounting surface is a high-precision processing surface, and heat-conducting silicone grease is coated on the mounting surface.
In order to reduce the influence of heat flow outside the space and radiation heat flow of the satellite and the camera assembly on the star sensor. The surfaces of the star sensor and the corresponding components are coated with 20 units of multilayer heat insulation components 17 except for a light inlet, a connecting surface and a heat dissipation surface.
An annular titanium alloy heat insulation pad 14 is arranged between the star sensor support 13 and the star sensor base 12 for heat insulation, parts on two sides of the heat insulation pad are mechanically connected through mounting points, and 10 units of multilayer heat insulation assemblies 17 are laid between the star sensor support 13 and the star sensor base 12 except for connecting points so as to further prevent the temperature change of the star sensor support 13 from thermally disturbing the star sensor base 12.
The outer surface of the star sensor support 13 is provided with a radiating surface to dissipate heat loss and absorbed external heat flow in the star sensor, and white paint with low absorptivity and high emissivity is sprayed on the surface of the radiating surface to enhance the radiating effect. The selection of the radiating surface is based on the thermal analysis result, and takes the principle that the sun area comprehensively absorbs the least heat flow when the star sensor operates on the track, and simultaneously considers the shielding relation among the star sensors. By adopting the technical scheme, the high-precision control of the star sensor flange within the temperature variation range of 10 +/-2 ℃ can be realized; compared with the prior art, the heat dissipation surface can be effectively reduced, the thermal compensation power consumption is reduced, and especially the heat consumption of the star sensor circuit box can be guided to the flange plate in the shadow area to be used as the thermal compensation power consumption, so that the thermal compensation power consumption is further reduced, and the satellite energy is saved; the star sensor support integrates the functions of structural support, heat dissipation, thermal compensation and the like, greatly simplifies the complexity of a thermal control system, and is safe and reliable.
In an alternative embodiment, the specific heat insulation manner is as follows: an annular titanium alloy heat insulation pad 14 is arranged between the star sensor support 13 and the star sensor base 12 for heat insulation, and the annular titanium alloy heat insulation pad 14 is provided with a mounting point for mechanical connection.
In an alternative embodiment, the insulation is: a plurality of layers of heat insulation components 17 are laid between the star sensor support 13 and the star sensor base 12 at positions between mounting points, so that the thermal disturbance of the temperature change of the star sensor support 13 to the star sensor base 12 is further prevented;
the multi-layer heat insulation assembly 17 is composed of a double-sided aluminum-plated polyester film and a polyester net.
Further, as shown in fig. 1 to 3, each of the star sensors 10 is connected to the star sensor holder 13 via a flange.
Referring to fig. 1-4, the star sensor support 13 is a hollow thin-walled cylinder with a beam 18 inside;
the top surface and the bottom surface of the beam and the mounting surface of the star sensor support 13 are processed according to a second preset processing precision requirement.
The star sensor support 13 is a hollow thin-wall cylindrical structure with a beam inside, and the top surface and the bottom surface of the beam and the mounting surface of the support are all high-precision processing surfaces. The outer surfaces of the supports are sprayed with white paint with high emissivity and low absorptivity, the exposed surface of each outer surface of the support is used as a radiating surface, and the orientation and the size of the radiating surface are determined according to the finite element simulation thermal analysis result.
In one specific embodiment, referring to fig. 1-3, the outer surface of the star sensor holder 13 is coated with a white paint to enable the outer surface of the star sensor holder 13 to serve as a heat dissipation surface.
In one particular embodiment, the star sensor 10 includes: a reserved gap is kept between the star sensor circuit box 24 and the beam, and the reserved gap is filled with an insulating heat conducting pad.
In one embodiment, the outer surface of the star sensor circuit box 24 and the inner surface of the star sensor support 13 are black anodized to enhance radiative heat transfer therebetween.
In a specific configuration mode, a gap is reserved between the outer bottom surface of the star sensor circuit box 24 and a beam of the star sensor support 13, and an insulating heat conduction pad is filled in the gap; the electric heater 15 is arranged on the bottom surface of the beam in the star sensor support 13, and the temperature control point thermistor 16 is arranged on the star sensor flange. All set up polyimide heat insulating ring between the lens hood anterior segment of star sensor and the back end to and between lens hood back end and the ring flange, for the thermal-insulated effect of reinforcing, polyimide heat insulating ring all thins 0.5mm in the region except that the mounting point.
Referring to fig. 1-3, the star sensor 10 includes: the electric heater 15 is arranged on the bottom surface of the beam inside the star sensor support 13; and the temperature control point thermistor 16 is connected with the electric heater 15, and the temperature control point thermistor 16 is arranged on the circumferential direction of the flange plate 23 of the star sensor 10.
Referring to fig. 1-3, the star sensor 10 includes: the star sensor light shield front section 21 and the star sensor light shield rear section 22 are connected in sequence; the rear section 22 of the star sensor hood is connected with a flange plate 23, and polyimide heat insulation pads 25 are respectively arranged between the front section 21 of the star sensor hood and the rear section 22 of the star sensor hood and between the rear section 22 of the star sensor hood and the flange plate 23.
The star sensor is composed of a light shield front section 21, a light shield rear section 22, a flange 23, a circuit box 24 and a polyimide heat insulation pad 25. And an insulating heat conducting pad is laid between the star sensor circuit box 24 and a cross beam in the star sensor support 13. An appropriate gap is left between the inner transverse surface of the star sensor support 13 and the star sensor circuit box 24, which can be implemented as 0.25mm, so that an insulating heat conducting pad with the thickness of 10mil is laid. The bottom side of the insulating heat conducting pad is pasted on a cross beam in the star sensor support by adopting heat conducting silicon rubber, and the top side of the insulating heat conducting pad is well jointed with the surface of the star sensor circuit box 24.
Black anodic oxidation treatment is carried out on the outer surface of the star sensor circuit box 24 and the inner surface of the star sensor support 13 to strengthen mutual radiation heat exchange, and the infrared emissivity epsilon is more than or equal to 0.8.
An active thermal control heating area is arranged on the bottom side of a cross beam in each star sensor support, each heating area comprises a main backup electric heater 15 and a thermistor 16, the electric heaters 15 are arranged on the cross beam in the star sensor support 13, and the temperature control point thermistor 16 is arranged in the circumferential direction of a star sensor flange 23.
The 3 groups of star sensors are arranged on the shared star sensor support 11, and in order to avoid thermal disturbance of the star sensor assembly to the space optical remote sensor, the star sensor support 11 and the space optical remote sensor are subjected to isothermal control, namely a temperature control target is consistent with a space optical remote sensor frame. An active thermal control heating area is arranged on the star sensor support and comprises a main backup temperature control loop and a backup temperature control loop, and each temperature control loop comprises an electric heater 15 and a thermistor 16. The outer surface of the star sensor support is coated with 20 units of multilayer heat insulation components 17.
In order to prevent the heat flow outside the space from severely disturbing the star sensor, the outer surface of the whole star sensor assembly is coated with a plurality of layers of heat insulation assemblies 17. Since the light inlet is irradiated by the sun in a part of the time during the operation of the star sensor 10 on the track, most of the heat flow entering the light inlet is absorbed by the front section 21 of the star sensor light shield, and polyimide heat insulation pads 25 with the thickness of 5mm are arranged between the front section 21 of the star sensor light shield and the rear section 22 of the star sensor light shield, and between the rear section 22 of the star sensor light shield and the flange 23. The heat absorbed by the front section 21 of the star sensor light shield is greatly weakened to be transferred to the rear section 22 of the star sensor light shield and the flange 23, so that the thermal disturbance to the flange 23 is obviously reduced.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.
Claims (10)
1. A space optical remote sensing satellite star sensor high-precision temperature control device is characterized by comprising:
the star sensor assembly support (11) can be connected with the space optical remote sensing load main body frame;
a plurality of star sensor bases (12) which are connected to the star sensor assembly support (11) and determine the extending direction of each star sensor (10) according to the optical axis direction of the star sensor;
each star sensor base (12) is mechanically connected with a star sensor support (13) in a heat insulation manner so as to reduce the thermal disturbance of the temperature change of the star sensor support (13) to the star sensor base (12);
each star sensor (10) is arranged on a corresponding star sensor support (13), an installation surface is formed between each star sensor (10) and the corresponding star sensor support (13), and the installation surface is processed according to preset precision and coated with heat-conducting silicone grease.
2. The high-precision temperature control device for the space optical remote sensing satellite star sensor as claimed in claim 1, wherein the heat insulation mode is as follows: an annular titanium alloy heat insulation pad (14) is arranged between the star sensor support (13) and the star sensor base (12) for heat insulation, and the annular titanium alloy heat insulation pad (14) is provided with a mounting point for mechanical connection.
3. The high-precision temperature control device for the space optical remote sensing satellite star sensor as claimed in claim 2, wherein the heat insulation mode is as follows: a plurality of layers of heat insulation components (17) are laid between the star sensor support (13) and the star sensor base (12) at positions between mounting points, so that the thermal disturbance of the temperature change of the star sensor support (13) to the star sensor base (12) is further prevented;
the multilayer heat insulation assembly (17) is composed of a double-sided aluminum plated polyester film and a polyester net.
4. The high-precision temperature control device for the space optical remote sensing satellite star sensor according to any one of claims 1 to 3, wherein each star sensor (10) is connected with the star sensor support (13) through a flange plate.
5. The high-precision temperature control device for the space optical remote sensing satellite star sensor according to claim 4, wherein the star sensor support (13) is a hollow thin-wall cylinder with a beam (18) inside;
and the top surface and the bottom surface of the beam and the mounting surface of the star sensor support (13) are processed according to a second preset processing precision requirement.
6. The high-precision temperature control device for the space optical remote sensing satellite star sensor according to claim 4, wherein the outer surface of the star sensor support (13) is coated with white paint so that the outer surface of the star sensor support (13) can be used as a heat dissipation surface.
7. The high-precision temperature control device for the star sensor of the space optical remote sensing satellite according to claim 4, wherein the star sensor (10) comprises:
and a reserved gap is kept between the star sensor circuit box (24) and the beam, and the reserved gap is filled with an insulating heat conduction pad.
8. The high-precision temperature control device for the space optical remote sensing satellite star sensor according to claim 7, wherein black anodic oxidation treatment is performed on the outer surface of the star sensor circuit box (24) and the inner surface of the star sensor support (13) to strengthen mutual radiation heat exchange.
9. The high-precision temperature control device for the star sensor of the space optical remote sensing satellite according to claim 8, wherein the star sensor (10) comprises:
the electric heater (15) is arranged on the bottom surface of the cross beam in the star sensor support (13);
and the temperature control point thermistor (16) is connected with the electric heater (15), and the temperature control point thermistor (16) is arranged in the circumferential direction of a flange plate (23) of the star sensor (10).
10. The high-precision temperature control device for the star sensor of the space optical remote sensing satellite according to claim 9, wherein the star sensor (10) comprises:
a star sensor light shield front section (21) and a star sensor light shield rear section (22) which are connected in sequence;
the star sensor hood rear section (22) is connected with the flange plate (23)
Polyimide heat insulation pads (25) are respectively arranged between the front section (21) of the star sensor light shield and the rear section (22) of the star sensor light shield, and between the rear section (22) of the star sensor light shield and the flange plate (23).
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115649482A (en) * | 2022-10-27 | 2023-01-31 | 长光卫星技术股份有限公司 | High-stability thermal control device and method for star sensor |
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