Flat panel satellite with precision temperature controlled components for navigation augmentation payload and method of temperature control

Abstract

The present application relates to a flat plate satellite with navigation enhanced load precision temperature control assembly and its temperature control method, the flat plate satellite includes satellite body, rubidium clock and multiplexer, the multiplexer is installed on the satellite body mounting surface through the multiplexer phase change energy storage plate, the outer surface of the multiplexer is covered with multilayer first heat insulation assembly, the rubidium clock is installed on the mounting surface of satellite body through the rubidium clock phase change energy storage plate, and the outer surface of the rubidium clock is covered with multilayer second heat insulation assembly;The satellite body is embedded with the first heat pipe for the heat dissipation of the multiplexer and the second heat pipe for the heat dissipation of the rubidium clock;The outer surface of the multiplexer is fixed with the first thermistor and the first heater that are electrically connected with each other, and the outer surface of the rubidium clock is fixed with the second thermistor and the second heater that are electrically connected with each other;The mounting surface of the satellite body is fixed with the third thermistor and the third heater that are electrically connected with each other, and the mounting surface of the satellite body is fixed with the fourth thermistor and the fourth heater that are electrically connected with each other, and the third heater is connected with the multiplexer phase change energy storage plate.

Description

Technical Field

[0001] This invention relates to the field of satellite-related technologies, specifically to a flat-panel satellite with a precision temperature control component for navigation enhancement payloads and its temperature control method. Background Technology

[0002] In navigation augmentation payloads, the highly stable rubidium clock and multiplexer are two of the most critical core components, together forming the "heart" and "throat" of the high-precision signal generation and transmission link. With the rapid development of satellites, navigation augmentation payloads require more precise time references to meet the demands of high-precision navigation and positioning. This places high-precision temperature control requirements on high-precision devices such as rubidium clocks and multiplexers. To improve the navigation and positioning capabilities of navigation augmentation payloads, it is necessary to control the temperature of the rubidium clock and multiplexer at appropriate levels and reduce temperature fluctuations. For example, for some devices located inside the satellite cabin... The mounting surface of the rubidium clock and multiplexer requires a wide temperature control range, with temperature fluctuations per orbit less than ±2℃ / orbit. However, for flat-panel satellites, all onboard equipment is installed outside the cabin. At the same time, the annual β angle (the β angle of a satellite orbit refers to the angle between the sunlight vector and the satellite orbital plane, which is a crucial parameter in satellite thermal control design because it directly affects two key factors: direct solar heat flux density and Earth's reflected heat flux density) of the low Earth orbit inclined orbit fluctuates greatly, and the external heat flux changes drastically. Reasonable temperature control measures are needed to ensure the temperature control indicators of the navigation enhancement payload.

[0003] Conventional rubidium clocks and multiplexers typically experience significant temperature fluctuations, generally requiring a temperature variation of less than ±2 to ±3℃ per track. Therefore, a simple thermal control scheme can meet these temperature requirements. However, for high-precision rubidium clocks and multiplexers, such as those used in flat-panel satellites, the demanding temperature requirements are much higher. Drastic changes in external heat flux significantly complicate thermal control design. Furthermore, the temperature control specifications for rubidium clocks and multiplexers require a temperature fluctuation of less than ±1℃ per 24 hours. To achieve these high-precision temperature control requirements, a combination of passive and active temperature control methods is employed to maintain the temperature of the navigation enhancement payload's rubidium clock and multiplexer within a suitable range. Summary of the Invention

[0004] In order to solve one or more technical problems existing in the prior art, the present invention provides a flat-panel satellite with a precision temperature control component for navigation enhancement payload and a temperature control method thereof.

[0005] The technical solution of this invention to solve the above-mentioned technical problems is as follows: This invention provides a flat-panel satellite with a precision temperature control component for navigation enhancement payload, including a satellite body, a rubidium clock, and a multiplexer. The front of the satellite body is a mounting surface. The multiplexer is mounted on the mounting surface of the satellite body via a multiplexer phase change energy storage plate. The outer surface of the multiplexer is covered with multiple layers of first heat insulation components. The rubidium clock is mounted on the mounting surface of the satellite body via a rubidium clock phase change energy storage plate. The outer surface of the rubidium clock is covered with multiple layers of second heat insulation components. The satellite body is embedded with a first heat pipe for dissipating heat from the multiplexer and a second heat pipe for dissipating heat from the rubidium clock.

[0006] The outer surface of the multiplexer is fixed with a first thermistor and a first heater that are electrically connected to each other. The outer surface of the rubidium clock is fixed with a second thermistor and a second heater that are electrically connected to each other. The mounting surface of the satellite body is fixed with a third thermistor and a third heater that are electrically connected to each other. The mounting surface of the satellite body is also fixed with a fourth thermistor and a fourth heater that are electrically connected to each other. The third heater is connected to the phase change energy storage plate of the multiplexer, and the fourth heater is connected to the phase change energy storage plate of the rubidium clock.

[0007] The beneficial effects of the present invention are: the flat-panel satellite with a precision temperature control component for navigation enhancement payload can reduce the temperature fluctuation of the rubidium clock and multiplexer of the navigation enhancement payload to less than ±1℃ / 24h during orbit by combining passive temperature control (heat insulation component, phase change energy storage plate and heat pipe) and active temperature control (thermometer and heater).

[0008] Based on the above technical solution, the present invention can be further improved as follows.

[0009] Furthermore, a fifth thermistor and a fifth heater, which are electrically connected to each other, are fixed on the back of the satellite body, and the fifth thermistor and the fifth heater are arranged corresponding to the multiplexer; a sixth thermistor and a sixth heater, which are electrically connected to each other, are also fixed on the back of the satellite body, and the sixth thermistor and the sixth heater are arranged corresponding to the rubidium clock.

[0010] The beneficial effect of adopting the above-mentioned further scheme is that by setting a fifth thermistor, a fifth heater, a sixth thermistor, and a sixth heater, active temperature control can be performed on the back of the multiplexer and the rubidium clock.

[0011] Furthermore, the fifth heater consists of two spaced-apart heaters, both of which are electrically connected to the fifth thermistor, and the sixth heater consists of two spaced-apart heaters, both of which are electrically connected to the sixth thermistor.

[0012] The beneficial effect of adopting the above-mentioned further scheme is that by setting two fifth heaters and two sixth heaters, active temperature control can be performed on the area where the load is located.

[0013] Furthermore, multiple sets of the first thermistor and the first heater are provided and are respectively fixed on the side of the multiplexer; multiple sets of the second thermistor and the second heater are provided and are respectively fixed on different sides of the rubidium clock.

[0014] Furthermore, the middle part of the first heat pipe is arranged corresponding to the multiplexer, and both ends of the first heat pipe extend to the peripheral edge of the satellite body; one end of the second heat pipe extends to the peripheral edge of the satellite body, and the other end of the second heat pipe is located on one side of the rubidium clock.

[0015] Furthermore, thermally conductive silicone grease is coated between the multiplexer and the multiplexer phase change energy storage plate, and thermally conductive silicone grease is coated between the rubidium clock and the rubidium clock phase change energy storage plate.

[0016] The beneficial effect of adopting the above-mentioned further solution is that by setting thermal grease, heat can be effectively conducted and the heat transfer effect is good.

[0017] Furthermore, thermally conductive silicone grease is applied between the multiplexer phase change energy storage plate and the satellite body, and thermally conductive silicone grease is applied between the rubidium clock phase change energy storage plate and the satellite body.

[0018] Furthermore, both the front and back of the satellite body are coated with thermal control white paint.

[0019] The beneficial effect of adopting the above-mentioned further solution is that by spraying thermal control white paint on the satellite body, effective heat dissipation can be provided for the satellite.

[0020] This invention provides a temperature control method for the above-mentioned flat-panel satellite with a precision temperature control component for navigation enhancement payload, comprising:

[0021] Under high-temperature conditions, the multiplexer is passively cooled by the first heat insulation component, the multiplexer phase change energy storage plate and the first heat pipe, and the rubidium clock is passively cooled by the second heat insulation component, the rubidium clock phase change energy storage plate and the second heat pipe.

[0022] Under low-temperature conditions, the first thermistor and the first heater achieve closed-loop temperature control through a satellite system, with a closed-loop temperature control threshold of 23.8℃~24.2℃; the second thermistor and the second heater achieve closed-loop temperature control through a satellite system, with a closed-loop temperature control threshold of 23.8℃~24.2℃.

[0023] The third thermistor and the third heater achieve closed-loop temperature control through the satellite system, and the closed-loop temperature control threshold of the third thermistor and the third heater is 19.8℃~20.2℃; the fourth thermistor and the fourth heater achieve closed-loop temperature control through the satellite system, and the closed-loop temperature control threshold of the fourth thermistor and the fourth heater is 19.8℃~20.2℃.

[0024] The beneficial effects of the present invention are: the temperature control method of the present invention adopts a combination of passive and active temperature control, which can make the temperature fluctuation of the navigation enhancement payload rubidium clock and multiplexer less than ±1℃ / 24h when on a low-orbit inclined track.

[0025] This invention provides a temperature control method for a flat-panel satellite with a precision temperature control component for navigation enhancement payload as described above, comprising:

[0026] Under high-temperature conditions, the multiplexer is passively cooled by the first heat insulation component, the multiplexer phase change energy storage plate and the first heat pipe, and the rubidium clock is passively cooled by the second heat insulation component, the rubidium clock phase change energy storage plate and the second heat pipe.

[0027] Under low-temperature conditions, the first thermistor and the first heater achieve closed-loop temperature control through a satellite system, with a closed-loop temperature control threshold of 23.8℃~24.2℃; the second thermistor and the second heater achieve closed-loop temperature control through a satellite system, with a closed-loop temperature control threshold of 23.8℃~24.2℃.

[0028] The third thermistor and the third heater achieve closed-loop temperature control via a satellite system, with a closed-loop temperature control threshold of 19.8℃~20.2℃; the fourth thermistor and the fourth heater achieve closed-loop temperature control via a satellite system, with a closed-loop temperature control threshold of 19.8℃~20.2℃; the fifth thermistor and the fifth heater achieve closed-loop temperature control via a satellite system, with a closed-loop temperature control threshold of 19.8℃~20.2℃; the sixth thermistor and the sixth heater achieve closed-loop temperature control via a satellite system, with a closed-loop temperature control threshold of 19.8℃~20.2℃.

[0029] The beneficial effects of the present invention are: the temperature control method of the present invention adopts a combination of passive and active temperature control, which can make the temperature fluctuation of the navigation enhancement payload rubidium clock and multiplexer less than ±1℃ / 24h when on a low-orbit inclined track.

[0030] In this invention, the electrical connection between the thermistor and the heater can be either a direct wire connection or a communication connection. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of the front structure of the flat-panel satellite with a precision temperature control component for navigation enhancement payload according to the present invention. Figure 1 ;

[0032] Figure 2 This is a schematic diagram of the front structure of the flat-panel satellite with a precision temperature control component for navigation enhancement payload according to the present invention. Figure 2 ;

[0033] Figure 3 This is a schematic diagram of the rear structure of the flat-panel satellite with a precision temperature control component for navigation enhancement payload according to the present invention.

[0034] The attached diagram lists the components represented by each number as follows:

[0035] 1. Satellite body; 11. First heat pipe; 12. Second heat pipe; 13. Third thermistor; 14. Third heater; 15. Fourth thermistor; 16. Fourth heater; 17. Fifth thermistor; 18. Fifth heater; 19. Sixth thermistor; 190. Sixth heater;

[0036] 2. Multiplexer; 21. Multiplexer phase change energy storage plate; 23. First thermistor; 24. First heater;

[0037] 3. Rubidium clock; 31. Rubidium clock phase change energy storage plate; 33. Second thermistor; 34. Second heater. Detailed Implementation

[0038] The principles and features of the present invention are described below. The examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0039] Example 1

[0040] like Figures 1-3As shown, this embodiment of a flat-panel satellite with a precision temperature control component for navigation enhancement payload includes a satellite body 1, a rubidium clock 3, and a multiplexer 2. The front of the satellite body 1 is the mounting surface. The multiplexer 2 is mounted on the mounting surface of the satellite body 1 via a multiplexer phase change energy storage plate 21. The outer surface of the multiplexer 2 is covered with multiple layers of first heat insulation components. The rubidium clock 3 is mounted on the mounting surface of the satellite body 1 via a rubidium clock phase change energy storage plate 31. The outer surface of the rubidium clock 3 is covered with multiple layers of second heat insulation components. The satellite body 1 is embedded with a first heat pipe 11 for dissipating heat from the multiplexer 2 and a second heat pipe 12 for dissipating heat from the rubidium clock 3. The first and second heat insulation components respectively cover the outer surfaces of the multiplexer 2 and the rubidium clock 3, except for the area of ​​the mounting surface. In addition to the mounting surfaces of the multiplexer phase change energy storage plate 21 and the rubidium clock phase change energy storage plate 31 on the satellite body 1, the docking surface between the multiplexer phase change energy storage plate 21 and the multiplexer, and the docking surface between the rubidium clock phase change energy storage plate 31 and the rubidium clock, the outer surface of the multiplexer phase change energy storage plate 21 is also covered with multiple layers of first heat insulation components, and the outer surface of the rubidium clock phase change energy storage plate 31 is also covered with multiple layers of second heat insulation components.

[0041] The outer surface of the multiplexer 2 is fixed with a first thermistor 23 and a first heater 24 that are electrically connected to each other. The outer surface of the rubidium clock 3 is fixed with a second thermistor 33 and a second heater 34 that are electrically connected to each other. The mounting surface of the satellite body 1 is fixed with a third thermistor 13 and a third heater 14 that are electrically connected to each other. The mounting surface of the satellite body 1 is also fixed with a fourth thermistor 15 and a fourth heater 16 that are electrically connected to each other. The third heater 14 is connected to the phase change energy storage plate 21 of the multiplexer, and the fourth heater 16 is connected to the phase change energy storage plate 31 of the rubidium clock.

[0042] like Figure 1 and Figure 2 As shown, in this embodiment, multiple sets of the first thermistor 23 and the first heater 24 are provided and fixed on the side of the multiplexer 2, respectively. Multiple sets of the first thermistor 23 and the first heater 24 can be installed on the same side of the multiplexer 2, or a set of the first thermistor 23 and the first heater 24 can be installed on different sides of the multiplexer 2, respectively. Multiple sets of the second thermistor 33 and the second heater 34 are provided and fixed on different sides of the rubidium clock 3, respectively.

[0043] like Figure 1 and Figure 2 As shown, preferably, the middle part of the first heat pipe 11 is arranged corresponding to the multiplexer 2, and both ends of the first heat pipe 11 extend to the peripheral edge of the satellite body 1; one end of the second heat pipe 12 extends to the peripheral edge of the satellite body 1, and the other end of the second heat pipe 12 is located on one side of the rubidium clock 3.

[0044] This embodiment achieves active heat dissipation by setting up multiple thermistors in conjunction with the heater and designing multiple heating and temperature control loops.

[0045] Furthermore, thermally conductive silicone grease is applied between the multiplexer 2 and the multiplexer phase change energy storage plate 21, and between the rubidium clock 3 and the rubidium clock phase change energy storage plate 31. The thermally conductive silicone grease used is RKTL-DRZ-1. By applying the thermally conductive silicone grease, effective heat conduction and good heat dissipation can be achieved. Thermally conductive silicone grease is applied between the multiplexer phase change energy storage plate and the satellite body, and between the rubidium clock phase change energy storage plate and the satellite body.

[0046] Preferably, the front and back of the satellite body 1 in this embodiment are coated with thermal control white paint (KS-ZA thermal control white paint). By coating the satellite body with thermal control white paint, effective heat dissipation can be provided for the satellite.

[0047] In this embodiment, the phase change temperature of the multiplexer phase change energy storage plate 21 and the rubidium clock phase change energy storage plate 31 is 25°C, and the latent heat of phase change is 235kJ / kg. Under high-temperature conditions, the temperature fluctuation of the navigation enhancement load can be less than 25±1°C / 24h.

[0048] Specifically, in this embodiment, the satellite body 1 adopts an aluminum honeycomb panel structure. The multiplexer phase change energy storage plate 21 and the rubidium clock phase change energy storage plate 31 are both made of paraffin wax. Both the first and second heat insulation components use F46 silver-plated secondary surface mirrors. The first and second heat insulation components enclose the heaters and thermistors of the payload. In this embodiment, the satellite body 1 itself has only one panel. The navigation enhancement payload is installed on the Z-plane of the panel. During on-orbit operation, the external heat flow changes drastically. The rubidium clock and multiplexer of the navigation enhancement payload are insulated by the heat insulation components. The outer surface of the satellite body 1 is coated with thermal control white paint to provide a heat dissipation surface. Pre-embedded heat pipes inside the satellite body 1 can dissipate heat from the navigation enhancement payload.

[0049] This embodiment features a flat-panel satellite with a precision temperature control component for navigation enhancement payloads. By combining passive temperature control (insulation components, phase change energy storage plates, and heat pipes) with active temperature control (thermometers and heaters), the temperature fluctuation of the rubidium clock and multiplexer in the navigation enhancement payload can be kept to less than ±1℃ / 24h during orbit.

[0050] Example 2

[0051] Based on Example 1, this example also provides a preferred passive heat dissipation method. For example... Figure 3As shown, in this embodiment, a fifth thermistor 17 and a fifth heater 18, electrically connected to each other, are fixed to the back of the satellite body 1. Both the fifth thermistor 17 and the fifth heater 18 are arranged correspondingly to the multiplexer 2. A sixth thermistor 19 and a sixth heater 190, electrically connected to each other, are also fixed to the back of the satellite body 1. Both the sixth thermistor 19 and the sixth heater 190 are arranged correspondingly to the rubidium clock 3. By setting the fifth thermistor, the fifth heater, the sixth thermistor, and the sixth heater, active temperature control can be achieved on the back of the multiplexer and the rubidium clock.

[0052] Preferred, such as Figure 3 As shown, in this embodiment, the fifth heater 18 consists of two spaced-apart units, both electrically connected to the fifth thermistor 17, and the sixth heater 190 consists of two spaced-apart units, both electrically connected to the sixth thermistor 19. By providing two fifth heaters and two sixth heaters, active temperature control can be achieved in the area where the load is located.

[0053] This embodiment is the first to be applied to a flat-panel satellite. The external heat flow changes drastically when a flat-panel satellite is in orbit, and the temperature control requirements for the rubidium clock and multiplexer of the navigation enhancement payload are higher than those of ordinary satellites. This application uses passive temperature control (multi-layer thermal insulation components, thermal control white paint KS-ZA, phase change energy storage plate, aluminum ammonia heat pipe, thermal conductive silicone grease) and active temperature control (heater thermistor MF501) to keep the temperature fluctuation of the rubidium clock and multiplexer of the navigation enhancement payload in orbit less than ±1℃ / 24h.

[0054] Example 3

[0055] This embodiment provides a temperature control method for a flat-panel satellite with a navigation enhancement payload precision temperature control component as described in Embodiment 1 above, including:

[0056] Under high-temperature conditions, the multiplexer 2 is passively cooled by the first heat insulation component, the multiplexer phase change energy storage plate 21 and the first heat pipe 11, and the rubidium clock 3 is passively cooled by the second heat insulation component, the rubidium clock phase change energy storage plate 31 and the second heat pipe 12.

[0057] Under low-temperature conditions, the first thermistor 23 and the first heater 24 achieve closed-loop temperature control through a satellite system, and the closed-loop temperature control threshold of the first thermistor 23 and the first heater 24 is 23.8℃~24.2℃; the second thermistor 33 and the second heater 34 achieve closed-loop temperature control through a satellite system, and the closed-loop temperature control threshold of the second thermistor 33 and the second heater 34 is 23.8℃~24.2℃.

[0058] The third thermistor 13 and the third heater 14 achieve closed-loop temperature control through the satellite system, and the closed-loop temperature control threshold of the third thermistor 13 and the third heater 14 is 19.8℃~20.2℃; the fourth thermistor 15 and the fourth heater 16 achieve closed-loop temperature control through the satellite system, and the closed-loop temperature control threshold of the fourth thermistor 15 and the fourth heater 16 is 19.8℃~20.2℃.

[0059] Specifically, the power of the first heater 24, the second heater 34, the third heater 14, and the fourth heater 16 is all 25W. The satellite service system can be implemented using service software. During closed-loop temperature control, when the temperature detected by the thermistor is lower than the minimum value of the closed-loop temperature control threshold, the heater corresponding to that thermistor in that loop is turned on; when the temperature detected by the thermistor is higher than the maximum value of the closed-loop temperature control threshold, the heater corresponding to that thermistor in that loop is turned off. This allows for temperature control of the rubidium clock and multiplexer within a range of 24±0.2℃ under low-temperature conditions, and temperature control of the mounting surface temperature of the rubidium clock and multiplexer within a range of 20±0.2℃, with temperature fluctuations less than ±0.2℃ / 24h.

[0060] The temperature control method in this embodiment combines passive and active temperature control, which can reduce the temperature fluctuation of the navigation enhancement payload rubidium clock and multiplexer to less than ±1℃ / 24h on low-orbit inclined tracks.

[0061] Example 4

[0062] This embodiment provides a temperature control method for a flat-panel satellite with a precision temperature control component for navigation enhancement payload as described in Embodiment 2 above, including:

[0063] Under high-temperature conditions, the multiplexer 2 is passively cooled by the first heat insulation component, the multiplexer phase change energy storage plate 21 and the first heat pipe 11, and the rubidium clock 3 is passively cooled by the second heat insulation component, the rubidium clock phase change energy storage plate 31 and the second heat pipe 12.

[0064] Under low-temperature conditions, the first thermistor 23 and the first heater 24 achieve closed-loop temperature control through a satellite system, and the closed-loop temperature control threshold of the first thermistor 23 and the first heater 24 is 23.8℃~24.2℃; the second thermistor 33 and the second heater 34 achieve closed-loop temperature control through a satellite system, and the closed-loop temperature control threshold of the second thermistor 33 and the second heater 34 is 23.8℃~24.2℃.

[0065] The third thermistor 13 and the third heater 14 achieve closed-loop temperature control through a satellite system, with a closed-loop temperature control threshold of 19.8℃~20.2℃. The fourth thermistor 15 and the fourth heater 16 achieve closed-loop temperature control through a satellite system, with a closed-loop temperature control threshold of 19.8℃~20.2℃. The fifth thermistor 17 and the fifth heater 18 achieve closed-loop temperature control through a satellite system, with a closed-loop temperature control threshold of 19.8℃~20.2℃. The sixth thermistor 19 and the sixth heater 190 achieve closed-loop temperature control through a satellite system, with a closed-loop temperature control threshold of 19.8℃~20.2℃.

[0066] Specifically, the power of the first heater 24, the second heater 34, the third heater 14, the fourth heater 16, the fifth heater 18, and the sixth heater 190 is all 25W. The satellite service system can be implemented using service software. During closed-loop temperature control, when the temperature detected by the thermistor is lower than the minimum value of the closed-loop temperature control threshold, the heater corresponding to that thermistor in that loop is turned on; when the temperature detected by the thermistor is higher than the maximum value of the closed-loop temperature control threshold, the heater corresponding to that thermistor in that loop is turned off. This allows for temperature control of the rubidium clock and multiplexer within a range of 24±0.2℃ under low-temperature conditions, and temperature control of the mounting surface temperature of the rubidium clock and multiplexer within a range of 20±0.2℃, with temperature fluctuations less than ±0.2℃ / 24h.

[0067] The temperature control method in this embodiment combines passive and active temperature control, which can reduce the temperature fluctuation of the navigation enhancement payload rubidium clock and multiplexer to less than ±1℃ / 24h on low-orbit inclined tracks.

[0068] In the description of this invention, it should be understood that the terms "inner" and "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing this invention and simplifying the description, 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, and therefore should not be construed as a limitation of this invention.

[0069] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0070] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., 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, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0071] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0072] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," 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 present 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. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0073] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A flat panel satellite having a navigation-enhanced payload precision temperature control assembly, characterized by, The satellite body, the rubidium clock and the multiplexer, the front of the satellite body is the installation surface, the multiplexer is installed on the installation surface of the satellite body through the multiplexer phase change energy storage plate, the outer surface of the multiplexer is covered with a plurality of first heat insulation components, the rubidium clock is installed on the installation surface of the satellite body through the rubidium clock phase change energy storage plate, and the outer surface of the rubidium clock is covered with a plurality of second heat insulation components; the satellite body is embedded with a first heat pipe for dissipating heat of the multiplexer and a second heat pipe for dissipating heat of the rubidium clock; The outer surface of the multiplexer is fixed with a first thermistor and a first heater which are electrically connected with each other, the outer surface of the rubidium clock is fixed with a second thermistor and a second heater which are electrically connected with each other, the installation surface of the satellite body is fixed with a third thermistor and a third heater which are electrically connected with each other, and the installation surface of the satellite body is further fixed with a fourth thermistor and a fourth heater which are electrically connected with each other, the third heater is connected with the multiplexer phase change energy storage plate, and the fourth heater is connected with the rubidium clock phase change energy storage plate; The back surface of the satellite body is fixed with a fifth thermistor and a fifth heater which are electrically connected with each other, the fifth thermistor and the fifth heater are correspondingly arranged with the multiplexer, the back surface of the satellite body is further fixed with a sixth thermistor and a sixth heater which are electrically connected with each other, the sixth thermistor and the sixth heater are correspondingly arranged with the rubidium clock, the fifth heater is two and is electrically connected with the fifth thermistor, and the sixth heater is two and is electrically connected with the sixth thermistor; Under high-temperature working conditions, the multiplexer is passively cooled through the first heat insulation component, the multiplexer phase change energy storage plate and the first heat pipe, and the rubidium clock is passively cooled through the second heat insulation component, the rubidium clock phase change energy storage plate and the second heat pipe; Under low-temperature working conditions, the first thermistor and the first heater realize closed-loop temperature control through the satellite service system, the closed-loop temperature control threshold of the first thermistor and the first heater is 23.8-24.2 DEG C, the second thermistor and the second heater realize closed-loop temperature control through the satellite service system, the closed-loop temperature control threshold of the second thermistor and the second heater is 23.8-24.2 DEG C; The third thermistor and the third heater realize closed-loop temperature control through the satellite service system, the closed-loop temperature control threshold of the third thermistor and the third heater is 19.8-20.2 DEG C, the fourth thermistor and the fourth heater realize closed-loop temperature control through the satellite service system, the closed-loop temperature control threshold of the fourth thermistor and the fourth heater is 19.8-20.2 DEG C, the fifth thermistor and the fifth heater realize closed-loop temperature control through the satellite service system, the closed-loop temperature control threshold of the fifth thermistor and the fifth heater is 19.8-20.2 DEG C, and the sixth thermistor and the sixth heater realize closed-loop temperature control through the satellite service system, the closed-loop temperature control threshold of the sixth thermistor and the sixth heater is 19.8-20.2 DEG C.

2. The flat panel satellite with enhanced payload precision temperature control assembly for navigation according to claim 1, wherein, The first thermistor and the first heater are provided with multiple groups and are fixed on the side of the multiplexer respectively; the second thermistor and the second heater are provided with multiple groups and are fixed on different sides of the rubidium clock respectively.

3. The flat panel satellite with enhanced payload precision temperature control assembly for navigation according to claim 1, wherein, The middle part of the first heat pipe corresponds to the multiplexer, and the two ends of the first heat pipe extend to the edge position of the satellite body respectively; one end of the second heat pipe extends to the edge position of the satellite body, and the other end of the second heat pipe is located on one side of the rubidium clock.

4. The flat panel satellite with enhanced payload precision temperature control assembly for navigation according to claim 1, wherein, Thermal conductive silicone grease is coated between the multiplexer and the multiplexer phase change energy storage plate, and between the rubidium clock and the rubidium clock phase change energy storage plate.

5. The flat panel satellite with enhanced payload precision temperature control assembly for navigation according to claim 1, wherein, Thermal conductive silicone grease is coated between the multiplexer phase change energy storage plate and the satellite body, and between the rubidium clock phase change energy storage plate and the satellite body.

6. The flat panel satellite having a precision temperature controlled assembly with navigation enhanced payload of claim 1, wherein, The front and back surfaces of the satellite body are sprayed with thermal control white paint.

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