Lightweight star sensor precision temperature control device with structural thermal control cooperation

Abstract

The application belongs to the technical field of satellite equipment, and discloses a light-weight star sensor precision temperature control device with structure thermal control cooperation, which comprises multiple satellite cabin plates, a star sensor light shielding plate, star sensor units and a star sensor mounting support. The multiple satellite cabin plates are spliced into a box body, the box body is provided with an opening, the star sensor light shielding plate is arranged below the opening, the star sensor units are arranged in pairs in the opening, the star sensor unit comprises a star sensor heat dissipation plate, a star sensor electronic system and a star sensor light shielding cover, the star sensor mounting support is installed on the opening and is used for supporting the star sensor unit, the star sensor mounting support is provided with a third heating temperature control loop arranged in pairs, and the third heating temperature control loop is arranged correspondingly to the star sensor unit. The light-weight star sensor precision temperature control device is light in weight, can effectively reduce the thermal deformation of the star sensor mounting support while realizing light weight, and thus improves the imaging index of the rocker satellite.

Description

Technical Field

[0001] This invention relates to the field of satellite equipment technology, and in particular to a lightweight star-sensitive precision temperature control device with structural thermal control coordination. Background Technology

[0002] High-performance star sensors are crucial components of high-resolution remote sensing satellites, and their on-orbit pointing accuracy significantly impacts the imaging performance of these satellites. To achieve high-resolution imaging, remote sensing satellites place stringent demands on the temperature control of star sensors, requiring them to possess extremely high temperature stability. Temperature fluctuations in star sensors are influenced not only by their own power consumption but also by changes in external heat flux. Given that remote sensing satellites typically operate in a sun-facing cruising attitude (when flying through shadowed areas, the satellite is in a three-axis stable Earth-facing attitude; when flying through sunlit areas, the -Z-axis hatch is facing the sun), the external heat flux experienced by the satellite and star sensors changes drastically, resulting in significant temperature fluctuations during on-orbit operation. Therefore, to ensure the temperature stability of the star sensors, appropriate temperature control measures are necessary to guarantee their performance specifications.

[0003] To minimize the impact of heat flow outside the sunlit orbital region, conventional star-sensor thermal control designs often employ independent temperature control via heat pipes and heat sinks. Heat pipes transfer the star-sensor's own heat loss and heat generated by sunlight to the heat sinks on the lower-heat-flow-affected compartment. Active heating compensation is then used in the shadowed orbital region to achieve the target temperature control. This approach increases the weight and resources required for the thermal control system. Furthermore, conventional star-sensor thermal control designs typically neglect the temperature control of the star-sensor mounting bracket. Under conditions of drastic changes in external heat flow, the temperature fluctuations of the mounting bracket are also significant. These extreme temperature variations lead to large thermal deformation of the mounting bracket, greatly reducing the star-sensor's accuracy and drastically lowering the imaging performance of the remote sensing satellite. Summary of the Invention

[0004] The purpose of this invention is to provide a lightweight star-sensor precision temperature control device with structural thermal control coordination. This lightweight star-sensor precision temperature control device is lightweight and can effectively reduce the thermal deformation of the star-sensor mounting bracket while achieving weight reduction, thereby improving the imaging performance of the joystick satellite.

[0005] To achieve this objective, the present invention adopts the following technical solution: This invention discloses a lightweight star-sensor precision temperature control device with structural thermal control coordination, comprising: multiple satellite panels, which are spliced ​​together to form a box, the box having an opening; a star-sensor light-shielding plate, which is disposed below the opening; and star-sensor units, which are arranged in pairs within the opening. Each star-sensor unit includes a star-sensor heat sink, a star-sensor electronics system, and a star-sensor light-shielding cover. The star-sensor electronics system is mounted on the star-sensor heat sink, and the star-sensor light-shielding cover is mounted on the star-sensor electronics system away from the star-sensor heat sink. On one side of the board, a first heating temperature control circuit is provided within the star-sensitive electronics system, and a second heating temperature control circuit is provided on the star-sensitive heat sink. A star-sensitive mounting bracket is installed in the opening and is used to support the star-sensitive unit. A third heating temperature control circuit is arranged in pairs on the star-sensitive mounting bracket, and the third heating temperature control circuit is correspondingly arranged with the star-sensitive unit. The surfaces of the star-sensitive light shield, the star-sensitive electronics system, and the star-sensitive heat sink are coated with a thermal control coating, and the star-sensitive mounting bracket is covered with a heat insulation layer.

[0006] In some embodiments, the star-sensitive electronics system is mounted on the star-sensitive heat sink via a first thermal conductive element.

[0007] In some embodiments, a first heat insulation pad is provided between the star-sensor light-shielding plate and the satellite cabin panel, and / or, A second heat insulation pad is provided between the star-sensor heat sink and the star-sensor mounting bracket.

[0008] In some embodiments, the star-sensor heat sink is a U-shaped plate and includes two first heat sinks and one second heat sink. The two first heat sinks are mounted on both sides of the second heat sink. The second heat sink is used to mount the star-sensor electronics system and is connected to the star-sensor mounting bracket.

[0009] In some embodiments, the star-sensitive shield is formed as a cone-shaped shield with a gradually increasing cross-section in the direction away from the star-sensitive electronics system.

[0010] In some embodiments, the star-sensor light-shielding plate includes an integrally formed star-sensor light-shielding bracket, two first light-shielding plates, and a second light-shielding plate. The star-sensor light-shielding bracket is connected to the satellite compartment panel. The second light-shielding plate is arranged parallel to the bottom wall of the opening of the box body. The two first light-shielding plates are respectively connected to both sides of the second light-shielding plate along its length. The first light-shielding plate and the second light-shielding plate are arranged at an angle greater than 90°.

[0011] In some embodiments, the projection of the star-sensor light-shielding plate onto a plane parallel to the bottom wall of the opening overlaps the projection of the star-sensor heat sink onto a plane parallel to the bottom wall of the opening.

[0012] In some embodiments, the star sensor mounting bracket includes an upper frame and a lower frame, the upper frame being fixed to the side wall of the opening, and the lower frame being connected to the upper frame; wherein: the lower frame has a middle plate, the lower frame is a symmetrical structure about the middle plate, and the third heating temperature control circuit is located on the side of the lower frame away from the upper frame.

[0013] In some specific embodiments, the lower frame includes a first support beam, a second support beam, a third support beam, two fourth support beams, and two fifth support beams. The first support beam, the second support beam, and the third support beam are arranged in parallel and spaced apart. The two ends of the middle plate are respectively connected to the second support beam and the third support beam. The two fourth support beams are symmetrically arranged about the middle plate. One end of the fourth support beam is connected to the first support beam, and the other end is connected to the fifth support beam. The middle part of the fourth support beam is connected to the second support beam. The two fifth support beams are symmetrically arranged about the middle plate. The end of the fifth support beam facing away from the fourth support beam is connected to the third support beam. The lower frame also includes two side plates, which are symmetrically arranged about the middle plate, and the side plates are connected to the fourth support beam and the fifth support beam.

[0014] In some specific embodiments, the third heating temperature control circuit includes a first star-sensitive heater, a second star-sensitive heater, a third star-sensitive heater, a fourth star-sensitive heater, a fifth star-sensitive heater, a sixth star-sensitive heater, a seventh star-sensitive heater, and an eighth star-sensitive heater arranged in series; wherein: the first star-sensitive heater is disposed on the first support beam; the second star-sensitive heater is disposed on the fourth support beam and located between the first support beam and the second support beam; the third star-sensitive heater and the fourth star-sensitive heater are spaced apart on the second support beam; the fifth star-sensitive heater is disposed on the fifth support beam; the sixth star-sensitive heater and the seventh star-sensitive heater are disposed on the middle plate, and the heating area of ​​the seventh star-sensitive heater is larger than the heating area of ​​the sixth star-sensitive heater; the eighth star-sensitive heater is disposed on the side plate.

[0015] The beneficial effects of this invention are as follows: The lightweight star-sensor precision temperature control device with structural thermal control coordination disclosed in this invention arranges a star-sensor light-shielding plate on the satellite module and uses a lightweight star-sensor heat sink between the star-sensor electronics system and the star-sensor mounting bracket. Compared with heat pipe cooling, the star-sensor heat sink is lighter and meets the weight reduction requirements. A three-stage heating circuit is used for active temperature control to ensure the temperature stability of the star-sensor electronics system and the star-sensor mounting bracket. This lightweight star-sensor precision temperature control device adopts passive and active temperature control methods, which can achieve lightweight, high stability, and high precision temperature control of the star-sensor electronics system of high-resolution remote sensing satellites. It can control the temperature stability of the star-sensor mounting bracket at 20±0.2℃, reduce the thermal deformation of the star-sensor mounting bracket, and greatly improve the on-orbit performance of the star-sensor electronics system.

[0016] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0017] Figure 1 This is a system architecture diagram of a lightweight star-sensitive precision temperature control device with structural thermal control coordination according to an embodiment of the present invention; Figure 2 This is a structural schematic diagram of a lightweight star-sensitive precision temperature control device with structural thermal control coordination according to an embodiment of the present invention; Figure 3 This is a schematic diagram of the lightweight star-sensitive precision temperature control device with structural thermal control coordination according to an embodiment of the present invention from another perspective; Figure 4 This is a top view of the lightweight star-sensitive precision temperature control device with structural thermal control coordination according to an embodiment of the present invention; Figure 5 This is a partial structural schematic diagram of the lightweight star-sensitive precision temperature control device with structural thermal control coordination according to an embodiment of the present invention; Figure 6 This is a schematic diagram of the structure of the star-sensor mounting bracket and the third heating temperature control circuit according to an embodiment of the present invention; Figure 7 This is a schematic diagram of the star sensor mounting bracket and the third heating temperature control circuit from another direction, according to an embodiment of the present invention.

[0018] Figure label: 100. Satellite panel; 101. Opening; 200. Star-sensor light-shielding plate; 210. Star-sensor light-shielding bracket; 220. First light-shielding plate; 230. Second light-shielding plate; 300. Star-sensor unit; 310. Star-sensor heat sink; 311. First heat sink; 312. Second heat sink; 3101. Second heating temperature control circuit; 320. Star-sensor electronics system; 330. Star-sensor light shield. 400. Star-type mounting bracket; 410. Upper frame; 420. Lower frame; 421. Middle plate; 422. First support beam; 423. Second support beam; 424. Third support beam; 425. Fourth support beam; 426. Fifth support beam; 427. Side plate; 500, Third heating temperature control circuit; 510, First star-sensitive heater; 520, Second star-sensitive heater; 530, Third star-sensitive heater; 540, Fourth star-sensitive heater; 550, Fifth star-sensitive heater; 560, Sixth star-sensitive heater; 570, Seventh star-sensitive heater; 580, Eighth star-sensitive heater. Detailed Implementation

[0019] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, and not all of the structures.

[0020] In the description of this invention, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0021] In the description of this embodiment, the terms "upper," "lower," "left," "right," "front," and "rear," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the present invention. Furthermore, the terms "first" and "second" are used only for distinction in description and have no special meaning.

[0022] This invention discloses a lightweight star-sensitive precision temperature control device with structural thermal control coordination (hereinafter referred to as the temperature control device for ease of description), referenced Figures 1-7As shown, the temperature control device includes multiple satellite panels 100, a star-sensor light-shielding plate 200, a star-sensor unit 300, and a star-sensor mounting bracket 400. The multiple satellite panels 100 are assembled into a box, which has an opening 101. In this embodiment, the box is a cube or cuboid. There are six satellite panels 100, namely, a satellite positive X-plane panel, a satellite negative Y-plane panel, a satellite positive Z-plane panel, a satellite positive Y-plane panel, a satellite positive Z-plane panel, and a satellite negative X-plane panel. The X-axis, Y-axis, and Z-axis directions are referenced... Figure 2 As shown, the arrow points in the positive direction; therefore, in this embodiment, opening 101 is located on the satellite's negative Y-plane panel. A star-sensor shield 200 is located below opening 101. Star-sensor units 300 are arranged in pairs within opening 101. Each star-sensor unit 300 includes a star-sensor heat sink 310, a star-sensor electronics system 320, and a star-sensor shield 330. The star-sensor electronics system 320 is mounted on the star-sensor heat sink 310, and the star-sensor shield 330 is mounted on the side of the star-sensor electronics system 320 facing away from the star-sensor heat sink 310. A first heating temperature control circuit is provided within the star-sensor electronics system 320. A second heating temperature control circuit 3101 is provided on the 10; a star sensor mounting bracket 400 is installed on the opening 101 and is used to support the star sensor unit 300. A third heating temperature control circuit 500 is arranged in pairs on the star sensor mounting bracket 400, and the third heating temperature control circuit 500 is correspondingly arranged with the star sensor unit 300; wherein: the surface of the star sensor light shield 200, the star sensor electronics system 320 and the star sensor heat sink 310 is sprayed with a thermal control coating, and the star sensor mounting bracket 400 is covered with a heat insulation layer.

[0023] Understandably, during actual operation, the star-sensor shield 200 blocks the star-sensor electronics system 320. For remote sensing satellites, the satellite's on-orbit attitude is solar cruise (when the satellite flies through the shadow area, the satellite has a three-axis stable Earth-oriented attitude; when flying through the sunlit area, the -Z-plane is solar-oriented). The -Z plane undergoes drastic changes when the satellite passes through the shadow and sunlit areas. In this embodiment, the star-sensor shield 200 can perfectly block the star-sensor electronics system 320. The surface of the star-sensor shield 200 is a thermal control coating, which can provide stable radiation characteristics for the star-sensor electronics system 320, thereby reducing the impact of drastic changes in external heat flow on the star-sensor electronics system 320 and improving the stability of the operating temperature of the star-sensor electronics system 320. Active temperature control is achieved by setting up a first heating temperature control circuit, a second heating temperature control circuit 3101, and a third heating temperature control circuit 500. The first and second heating temperature control circuits 3101 can ensure that the temperature stability of the star-sensitive electronics system 320 is within a specified range (e.g., 20±0.2℃), and the third heating temperature control circuit 500 can ensure that the temperature stability of the star-sensitive mounting bracket 400 is within a specified range (e.g., 20±0.2℃). This greatly improves the temperature stability of the star-sensitive mounting bracket 400, reduces the thermal deformation of the star-sensitive mounting bracket 400, and greatly improves the performance indicators of the star-sensitive electronics.

[0024] In summary, the temperature control device of the present invention arranges a star-sensor light-shielding plate 200 on the satellite compartment 100 and uses a lightweight star-sensor heat sink 310 between the star-sensor electronics system 320 and the star-sensor mounting bracket 400. Compared with heat pipe heat dissipation, the star-sensor heat sink 310 is lighter and can meet the weight reduction requirements. A three-stage heating circuit is used for active temperature control to ensure the temperature stability of the star-sensor electronics system 320 and the star-sensor mounting bracket 400. This temperature control device adopts passive and active temperature control methods, which can achieve lightweight, high stability, and high precision temperature control of the star-sensor electronics system 320 of the high-resolution remote sensing satellite. It can control the temperature stability of the star-sensor mounting bracket 400 at 20±0.2℃, reduce the thermal deformation of the star-sensor mounting bracket 400, and greatly improve the on-orbit performance of the star-sensor electronics system 320.

[0025] In some embodiments, both the first heating temperature control circuit and the second heating temperature control circuit 3101 consist of a heater and a thermistor. The active heating temperature control logic is implemented in a closed-loop manner by the satellite software. The temperature control threshold of the first heating temperature control circuit is designed to be between 19.8℃ and 20.2℃; the temperature control threshold of the second heating temperature control circuit 3101 is designed to be between 18.8℃ and 19.2℃. The temperature control threshold of the third heating temperature control circuit 500 is designed to be between 19.8℃ and 20.2℃.

[0026] In some embodiments, the thermal control coating is thermal control white paint KS-ZA. Of course, in other embodiments of the present invention, the specific material of the thermal control coating can be selected from other coatings according to actual needs.

[0027] In some embodiments, the star-sensor shield 330 is provided with a multi-layer heat-insulating coating to reduce temperature fluctuations of the star-sensor shield 330.

[0028] In some embodiments, the star-sensitive electronics system 320 is mounted on the star-sensitive heat sink 310 via a thermal pad. It is understood that mounting the star-sensitive electronics system 320 to the star-sensitive heat sink 310 via a thermal pad ensures that the star-sensitive heat sink 310 stably dissipates heat from the star-sensitive electronics system 320.

[0029] In some embodiments, a first heat insulation pad is provided between the star-sensor shielding plate 200 and the satellite module 100. It is understood that providing the first heat insulation pad between the star-sensor shielding plate 200 and the satellite module 100 (satellite negative Y-plane module) can reduce the impact of temperature fluctuations in the satellite negative Y-plane module on the star-sensor shielding plate 200 during on-orbit operation. In embodiments of the present invention, the material of the first heat insulation pad can be selected according to actual needs, and no specific limitations are imposed on the material of the first heat insulation pad here.

[0030] In some embodiments, a second thermal insulation pad is provided between the star-sensor heat sink 310 and the star-sensor mounting bracket 400. It is understood that providing a second thermal insulation pad between the star-sensor heat sink 310 and the star-sensor mounting bracket 400, and their thermally insulated installation, can prevent temperature fluctuations of the star-sensor mounting bracket 400 from affecting the star-sensor electronics system 320. In embodiments of the present invention, the material of the second thermal insulation pad can be selected according to actual needs, and no specific limitations are imposed on the material of the second thermal insulation pad here.

[0031] In some embodiments, a third heat insulation pad is provided between the star-sensor mounting bracket 400 and the satellite module 100 (the satellite's Z-plane module). This heat-insulating installation prevents temperature fluctuations in the Z-plane module from affecting the star-sensor mounting bracket 400. In embodiments of the present invention, the material of the third heat insulation pad can be selected according to actual needs; therefore, no specific limitations are imposed on the material of the third heat insulation pad.

[0032] In some embodiments, the star-sensor heat sink 310 is a U-shaped plate and includes two first heat sinks 311 and one second heat sink 312. The two first heat sinks 311 are mounted on both sides of the second heat sink 312. The second heat sink 312 is used to mount the star-sensor electronics system 320 and is connected to the star-sensor mounting bracket 400. It is understood that the Z-plane will change drastically when the satellite passes through the shadow area and the sunlit area. Using a U-shaped plate as the star-sensor heat sink 310 can ensure that the star-sensor shading plate 200 can perfectly shield the star-sensor electronics system 320, thereby reducing the impact of drastic changes in external heat flow on the star-sensor electronics system 320 and improving the stability of the operating temperature of the star-sensor electronics system 320.

[0033] In one specific embodiment, the second heat sink 312 is fixed to the star sensor mounting bracket 400 by screws, and the second heat insulation pad is sandwiched between the second heat sink 312 and the star sensor mounting bracket 400. Of course, the second heat sink 312 and the star sensor mounting bracket 400 can also be connected in other ways, such as snap-fit ​​connection, and the adhesive connection is not limited to screw connection.

[0034] In some embodiments, the star-sensitive light shield 330 is formed as a cone-shaped shield with a gradually increasing cross-section in the direction away from the star-sensitive electronics system 320. It is understood that setting the star-sensitive light shield 330 as a cone-shaped shield can improve the light-shielding effect, thereby reducing the impact of drastic changes in external heat flow on the star-sensitive electronics system 320 and improving the stability of the operating temperature of the star-sensitive electronics system 320.

[0035] In some embodiments, the star-sensor light shield 200 includes an integrally formed star-sensor light shield bracket 210, two first light shields 220, and a second light shield 230. The star-sensor light shield bracket 210 is connected to the satellite compartment panel 100. The second light shield 230 is arranged parallel to the bottom wall of the opening 101 of the housing. The two first light shields 220 are respectively connected to both sides of the second light shield 230 along its length. The first light shields 220 and the second light shield 230 are arranged at an angle greater than 90°. It is understood that the star-sensor light shield 200 adopts an integrally formed structure, which can ensure its strength. The two first light shields 220 and the second light shield 230 can stably shield the star-sensor electronics system 320 when it is necessary to shield it, thereby reducing the influence of drastic changes in external heat flow on the star-sensor electronics system 320 and improving the stability of the operating temperature of the star-sensor electronics system 320.

[0036] In some embodiments, the projection of the star-sensor light-shielding plate 200 onto a plane parallel to the bottom wall of the opening 101 covers the projection of the star-sensor heat sink 310 onto a plane parallel to the bottom wall of the opening 101. It is understood that, since the projection of the star-sensor light-shielding plate 200 onto a plane parallel to the bottom wall of the opening 101 covers the projection of the star-sensor heat sink 310 onto a plane parallel to the bottom wall of the opening 101, when it is necessary to shield the star-sensor electronics system 320, the star-sensor light-shielding plate 200 can completely shield the star-sensor electronics system 320, thereby reducing the impact of drastic changes in external heat flow on the star-sensor electronics system 320 and improving the stability of the operating temperature of the star-sensor electronics system 320.

[0037] In some embodiments, the star sensor mounting bracket 400 includes an upper frame 410 and a lower frame 420. The upper frame 410 is fixed to the side wall of the opening 101, and the lower frame 420 is connected to the upper frame 410. The lower frame 420 has a middle plate 421 and is a symmetrical structure about the middle plate 421. A third heating temperature control circuit 500 is located on the side of the lower frame 420 opposite to the upper frame 410. It is understood that the symmetrical structure of the lower frame 420 allows for the symmetrical distribution of the two third heating temperature control circuits 500, which can control the temperature stability of the star sensor mounting bracket 400 within a specified range (e.g., 20 ± 0.2 °C), reducing the thermal deformation of the star sensor mounting bracket 400.

[0038] In one specific embodiment, the upper frame 410 and the lower frame 420 are connected by screws.

[0039] In some specific embodiments, the lower frame 420 includes a first support beam 422, a second support beam 423, a third support beam 424, two fourth support beams 425, and two fifth support beams 426. The first support beam 422, the second support beam 423, and the third support beam 424 are arranged in parallel and spaced apart. The two ends of the middle plate 421 are respectively connected to the second support beam 423 and the third support beam 424. The two fourth support beams 425 are symmetrically arranged about the middle plate 421, and one end of the fourth support beam 425 is connected to... The first support beam 422 is connected at one end, and the other end is connected to the fifth support beam 426. The middle part of the fourth support beam 425 is connected to the second support beam 423. The two fifth support beams 426 are symmetrically arranged about the middle plate 421, and the end of the fifth support beam 426 away from the fourth support beam 425 is connected to the third support beam 424. The lower frame 420 also includes two side plates 427, which are symmetrically arranged about the middle plate 421 and connected to the fourth support beam 425 and the fifth support beam 426. It can be understood that the first support beam 422, the second support beam 423, the third support beam 424, the two fourth support beams 425, the two fifth support beams 426, and the side plates 427 are used to install the heater in the third heating temperature control circuit 500, which can ensure the temperature uniformity of the star sensor mounting bracket 400 and reduce the thermal deformation of the star sensor mounting bracket 400.

[0040] In some specific embodiments, the third heating temperature control circuit 500 includes a first star-sensitive heater 510, a second star-sensitive heater 520, a third star-sensitive heater 530, a fourth star-sensitive heater 540, a fifth star-sensitive heater 550, a sixth star-sensitive heater 560, a seventh star-sensitive heater 570, and an eighth star-sensitive heater 580 arranged in series; wherein: the first star-sensitive heater 510 is disposed on the first support beam 422; the second star-sensitive heater 520 is disposed on the fourth support beam 425 and located between the first support beam 422 and the second support beam 423; the third star-sensitive heater 530 and the fourth star-sensitive heater 540 are spaced apart on the second support beam 423; the fifth star-sensitive heater 550 is disposed on the fifth support beam 426; the sixth star-sensitive heater 560 and the seventh star-sensitive heater 570 are disposed on the middle plate 421, and the heating area of ​​the seventh star-sensitive heater 570 is larger than the heating area of ​​the sixth star-sensitive heater 560; and the eighth star-sensitive heater 580 is disposed on the side plate 427. This ensures the uniformity of temperature in the star sensor mounting bracket 400 and reduces its thermal deformation. Of course, in other embodiments of the present invention, the specific composition and distribution of the third heating temperature control circuit 500 can be selected according to actual needs.

[0041] To ensure that the third heating temperature control circuit 500 can stably and uniformly control the temperature of the star sensor mounting bracket 400, thermal grease is provided between the first star sensor heater 510 and the first bracket beam 422; thermal grease is provided between the second star sensor heater 520 and the fourth bracket beam 425; thermal grease is provided between the third star sensor heater 530 and the second bracket beam 423; thermal grease is provided between the fourth star sensor heater 540 and the second bracket beam 423; thermal grease is provided between the fifth star sensor heater 550 and the fifth bracket beam 426; thermal grease is provided between the sixth star sensor heater 560 and the middle plate 421; thermal grease is provided between the seventh star sensor heater 570 and the middle plate 421; and thermal grease is provided between the eighth star sensor heater 580 and the side plate 427.

[0042] It should be noted that the specific wiring diagrams for the first star heater 510, the second star heater 520, the third star heater 530, the fourth star heater 540, the fifth star heater 550, the sixth star heater 560, the seventh star heater 570, and the eighth star heater 580 are not shown. In actual connection, they can be connected in series according to the product's wiring requirements. Even if they are not shown in the diagram, technicians can connect them based on basic circuit knowledge.

[0043] In the description of this specification, references to terms such as "some embodiments," "other embodiments," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0044] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. Those skilled in the art will be able to make various obvious changes, readjustments, and substitutions without departing from the scope of protection of the present invention. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A lightweight star-sensitive precision temperature control device with structural thermal control coordination, characterized in that, include: Multiple satellite modules (100) are assembled into a box, and the box has an opening (101). A star-sensitive light-shielding plate (200) is disposed below the opening (101); A star-sensor unit (300) is arranged in pairs within the opening (101). Each star-sensor unit (300) includes a star-sensor heat sink (310), a star-sensor electronics system (320), and a star-sensor light shield (330). The star-sensor electronics system (320) is mounted on the star-sensor heat sink (310), and the star-sensor light shield (330) is mounted on the side of the star-sensor electronics system (320) facing away from the star-sensor heat sink (310). A first heating temperature control circuit is provided within the star-sensor electronics system (320), and a second heating temperature control circuit (3101) is provided on the star-sensor heat sink (310). A star sensor mounting bracket (400) is installed in the opening (101) and used to support the star sensor unit (300). The star sensor mounting bracket (400) is provided with a pair of third heating temperature control circuits (500), each corresponding to a star sensor unit (300). The surfaces of the star-sensor light shield (200), the star-sensor electronics system (320), and the star-sensor heat sink (310) are coated with a thermal control coating, and the star-sensor mounting bracket (400) is covered with a heat insulation layer.

2. The lightweight star-sensitive precision temperature control device with structural thermal control synergy according to claim 1, characterized in that, The star-sensitive electronics system (320) is mounted on the star-sensitive heat sink (310) via a first heat-conducting component.

3. The lightweight star-sensitive precision temperature control device with structural thermal control synergy according to claim 1, characterized in that, A first heat insulation pad is provided between the star-sensor light-shielding plate (200) and the satellite cabin plate (100), and / or, A second heat insulation pad is provided between the star-sensor heat sink (310) and the star-sensor mounting bracket (400).

4. The lightweight star-sensitive precision temperature control device with structural thermal control synergy according to any one of claims 1-3, characterized in that, The star-sensor heat sink (310) is a U-shaped plate and includes two first heat sinks (311) and one second heat sink (312). The two first heat sinks (311) are installed on both sides of the second heat sink (312). The second heat sink (312) is used to install the star-sensor electronics system (320) and is connected to the star-sensor mounting bracket (400).

5. The lightweight star-sensitive precision temperature control device with structural thermal control synergy according to any one of claims 1-3, characterized in that, The star-sensitive shield (330) is formed as a cone-shaped shield with a gradually increasing cross-section in the direction away from the star-sensitive electronics system (320).

6. The lightweight star-sensitive precision temperature control device with structural thermal control synergy according to any one of claims 1-3, characterized in that, The star-sensor light-shielding plate (200) includes an integrally formed star-sensor light-shielding bracket (210), two first light-shielding plates (220) and one second light-shielding plate (230). The star-sensor light-shielding bracket (210) is connected to the satellite compartment plate (100). The second light-shielding plate (230) is arranged parallel to the bottom wall of the opening (101) of the box body. The two first light-shielding plates (220) are respectively connected to both sides of the second light-shielding plate (230) along its length. The first light-shielding plate (220) and the second light-shielding plate (230) are arranged at an angle greater than 90°.

7. The lightweight star-sensitive precision temperature control device with structural thermal control synergy according to any one of claims 1-3, characterized in that, The projection of the star-sensor shielding plate (200) on a plane parallel to the bottom wall of the opening (101) covers the projection of the star-sensor heat sink plate (310) on a plane parallel to the bottom wall of the opening (101).

8. The lightweight star-sensitive precision temperature control device with structural thermal control synergy according to any one of claims 1-3, characterized in that, The star-sensor mounting bracket (400) includes an upper frame (410) and a lower frame (420). The upper frame (410) is fixed to the side wall of the opening (101), and the lower frame (420) is connected to the upper frame (410). The lower frame (420) has a middle plate (421), and the lower frame (420) is a symmetrical structure about the middle plate (421). The third heating temperature control circuit (500) is located on the side of the lower frame (420) away from the upper frame (410).

9. The lightweight star-sensitive precision temperature control device with structural thermal control synergy according to claim 8, characterized in that, The lower frame (420) includes a first support beam (422), a second support beam (423), a third support beam (424), two fourth support beams (425), and two fifth support beams (426). The first support beam (422), the second support beam (423), and the third support beam (424) are arranged in parallel and spaced apart. The two ends of the middle plate (421) are respectively connected to the second support beam (423) and the third support beam (424), and the two fourth support beams (425) are connected to the third support beam (424). The fourth support beam (425) is symmetrically arranged about the middle plate (421). One end of the fourth support beam (425) is connected to the first support beam (422), and the other end is connected to the fifth support beam (426). The middle part of the fourth support beam (425) is connected to the second support beam (423). The two fifth support beams (426) are symmetrically arranged about the middle plate (421). The end of the fifth support beam (426) away from the fourth support beam (425) is connected to the third support beam (424). The lower frame (420) also includes two side plates (427), which are symmetrically arranged about the middle plate (421). The side plates (427) are connected to the fourth support beam (425) and the fifth support beam (426).

10. The lightweight star-sensitive precision temperature control device with structural thermal control synergy according to claim 9, characterized in that, The third heating temperature control circuit (500) includes a first star-sensitive heater (510), a second star-sensitive heater (520), a third star-sensitive heater (530), a fourth star-sensitive heater (540), a fifth star-sensitive heater (550), a sixth star-sensitive heater (560), a seventh star-sensitive heater (570), and an eighth star-sensitive heater (580) arranged in series; wherein: The first star-sensitive heater (510) is mounted on the first support beam (422); The second star-sensitive heater (520) is disposed on the fourth support beam (425) and located between the first support beam (422) and the second support beam (423); The third star-sensor heater (530) and the fourth star-sensor heater (540) are spaced apart on the second support beam (423); The fifth star-sensitive heater (550) is mounted on the fifth support beam (426); The sixth star heater (560) and the seventh star heater (570) are disposed on the middle plate (421), and the heating area of ​​the seventh star heater (570) is larger than the heating area of ​​the sixth star heater (560). The eighth star-sensitive heater (580) is located on the side plate (427).

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