A solar synchronous orbit radiation cooler

Abstract

The invention relates to the technical field of refrigerators, and discloses a solar synchronous orbit radiation refrigerator, comprising a carbon fiber frame, on which a reflection screen, a cold block and a globe screen are arranged; the carbon fiber frame comprises a bottom column, a vertical column and a top column connected to each other; a diagonal support rod for installing the reflection screen is arranged obliquely on the top column, and a plane support plate for installing the cold block is arranged on the side wall of the vertical column; the reflection screen comprises a panel, a first reflection screen, a second reflection screen and a third reflection screen connected in sequence, and side panels are arranged on the sides of the first reflection screen, the second reflection screen and the third reflection screen; screen fixing parts and screen heat insulation supports are arranged at one end of the first reflection screen, the second reflection screen and the third reflection screen close to the diagonal support rod; the cold block comprises a first cold block and a second cold block arranged adjacently, the edge of the first cold block is connected to the globe screen, and the edge of the second cold block is connected to the reflection screen. Under the action of the globe screen and the reflection screen, the device provides an on-orbit environment without external heat flow for the cold block.

Description

Technical Field

[0001] The present invention relates to the technical field of refrigerators, and in particular to a sun-synchronous orbit radiation refrigerator. Background Art

[0002] The sun-synchronous orbit radiant cooler is a radiant cooling technology for sun-synchronous orbit environments. It uses special materials and designs to achieve extremely low temperature environments under sun-synchronous orbit conditions to meet the needs of some special applications. The sun-synchronous orbit is a special satellite orbit. Its main feature is that the satellite orbits the earth at a fixed position relative to the earth, which can ensure that the satellite always operates under similar sunlight. Since the satellite is exposed to a large amount of radiation from the sun and the earth in this orbit, the ambient temperature in orbit is relatively high, which is a challenge for some applications that require extremely low temperature environments. Therefore, it is of great significance to develop a technology that can achieve refrigeration in a sun-synchronous orbit.

[0003] In traditional refrigeration technology, commonly used refrigeration methods include mechanical refrigeration, chemical refrigeration and radiation refrigeration. Mechanical refrigeration mainly relies on equipment such as compressors to cool the air, but this method requires a lot of electricity and equipment, which is not suitable for satellites in sun-synchronous orbits. Chemical refrigeration mainly relies on chemical reactions to achieve refrigeration, but it requires periodic replacement of chemicals and equipment, and is not suitable for satellites in sun-synchronous orbits. Radiative refrigeration technology is a method of using extremely low temperatures in outer space to achieve refrigeration. It uses the radiation of objects to achieve cooling. In sun-synchronous orbits, radiative refrigeration technology is an ideal refrigeration method that does not require external energy input and large equipment, and can achieve a long-term stable low-temperature environment. Summary of the invention

[0004] In view of the above-mentioned deficiencies in the prior art, a sun-synchronous orbit radiation refrigerator provided by the present invention solves the problem in the prior art that refrigeration requires external energy input and large-scale equipment.

[0005] In order to achieve the above-mentioned invention object, the technical solution adopted by the present invention is: a sun-synchronous orbit radiation refrigerator, characterized in that it includes a carbon fiber frame, on which a reflection screen, a cold block and a globe screen are arranged;

[0006] The carbon fiber frame includes a bottom column, a vertical column and a top column which are connected to each other; wherein the bottom column is horizontally arranged at the bottom end of the vertical column, the top column is horizontally arranged at the top end of the vertical column, and the bottom column and the top column are located on opposite sides of the vertical column; a diagonal support rod for installing a reflective screen is extended upwardly and tilted on one side of the top column close to the vertical column, and a flat support plate for installing a cold block is arranged on the side wall of the vertical column;

[0007] The reflective screen comprises a panel, a first reflective screen, a second reflective screen and a third reflective screen connected in sequence, and side panels are arranged on the sides of the first reflective screen, the second reflective screen and the third reflective screen; screen fixing parts and screen heat insulation supports are arranged on the surfaces of one side of the first reflective screen, the second reflective screen and the third reflective screen close to the diagonal support rod;

[0008] The cold block comprises a first cold block and a second cold block which are adjacently arranged. The edge of the first cold block is connected to the earth screen, and the edge of the second cold block is connected to the reflection screen.

[0009] The beneficial effects of the present invention are as follows: the carbon fiber frame is lightweight, high-strength and corrosion-resistant, and can withstand radiation and temperature changes in a space environment. It also has good structural stability and can effectively support and install the reflective screen, cold block and earth screen, thereby ensuring the stability and reliability of the entire refrigerator. The earth screen is used to shield the external heat flow from the earth, and the reflective screen is used to reflect the external heat flow from the earth. Under the joint action of the earth screen and the reflective screen, an on-orbit environment with almost no external heat flow is provided to the cold block. The cold energy provided by the cold block can be used to achieve low temperatures for cryogenic optics and detectors.

[0010] Furthermore, in the above-mentioned sun-synchronous orbit radiation cooler, the first reflection screen, the second reflection screen and the third reflection screen are aluminum honeycomb panels, and a high-reflectivity mirror aluminum layer is arranged on one side of the first reflection screen, the second reflection screen and the third reflection screen away from the carbon fiber frame.

[0011] The beneficial effects of adopting the above further scheme are: the aluminum honeycomb panel is light, high-strength and has good thermal conductivity, which can not only provide good structural support, but also effectively conduct and disperse heat, which helps to reduce the temperature of the entire system. The aluminum honeycomb panel also has excellent sound absorption performance, which also has a positive effect on reducing noise, vibration and other environmental interference. The high-reflectivity mirror aluminum layer has a high reflectivity, ensuring that all external heat flows from the earth are reflected and not reflected to the second cold block.

[0012] Furthermore, in the above-mentioned sun-synchronous orbit radiation cooler, the angle between the first reflection screen and the second reflection screen is 169°, and the angle between the second reflection screen and the third reflection screen is 168°.

[0013] The beneficial effect of adopting the above further solution is: for the sun-synchronous orbit with an orbital altitude of 830-840 km, the angle between the first reflector and the second reflector is 169°, and the angle between the second reflector and the third reflector is 168°. Reasonable angle adjustment can make the reflector reflect solar radiation more accurately, avoiding the problem of radiation energy leakage or uneven reflection caused by improper angle.

[0014] Furthermore, in the above-mentioned sun-synchronous orbit radiation cooler, the panel and the side panels are thermally connected to the first reflection screen.

[0015] Furthermore, in the above-mentioned sun-synchronous orbit radiation cooler, a white paint layer is provided on the surface of the panel and the side panels.

[0016] The beneficial effect of adopting the above further solution is that the white paint layer is used to cool the spliced ​​reflective screen assembly, which can reduce the radiation heat exchange of the reflective screen to the second cold block.

[0017] Furthermore, in the above-mentioned sun-synchronous orbit radiation cooler, auxiliary diagonal braces are arranged to connect the sides of the bottom column and the vertical column.

[0018] The beneficial effect of adopting the above further solution is that the auxiliary diagonal bracing rods are used to enhance the mechanical strength of the entire frame.

[0019] Furthermore, in the above-mentioned sun-synchronous orbit radiation cooler, the screen insulation support is made of non-metallic material.

[0020] The beneficial effect of adopting the above further solution is that non-metallic materials usually have lower thermal conductivity and can better isolate heat and reduce heat energy transmission in a sun-synchronous orbit.

[0021] Furthermore, in the above-mentioned sun-synchronous orbit radiation cooler, the material of the screen insulation support is epoxy fiberglass.

[0022] The beneficial effects of adopting the above further scheme are: Epoxy FRP has a low thermal expansion coefficient, and its dimensions are stable and not easily deformed under extreme temperature changes. The temperature range in space is large, and the use of epoxy FRP can reduce the structural stress and deformation caused by temperature fluctuations, ensuring the long-term stable operation of the refrigerator. Epoxy FRP itself has good thermal insulation performance. As a screen insulation support, it can further reduce the risk of heat being transferred to the cold block through the support part, thereby improving the overall thermal insulation effect of the refrigerator.

[0023] The beneficial effects of the present invention are as follows: the use of the carbon fiber frame not only significantly reduces the weight of the equipment and reduces the launch cost, but also provides sufficient structural strength and stability to ensure reliability during launch and on-orbit operation. The use of aluminum honeycomb panels and the setting of high-reflectivity mirror aluminum layers greatly enhance the reflective ability of the reflective screen to sunlight and earth radiation, thereby enhancing the cooling effect. The angle setting between the reflective screens is carefully adjusted to more accurately control the reflection path of sunlight and earth radiation and reduce the heat load on the cold block. The thermal conductive connection of the panel and side panels to the first reflective screen and the surface treatment of the white paint layer are conducive to reducing the solar absorption rate and further enhancing the cooling effect. The screen insulation support uses non-metallic material epoxy fiberglass as the material of the screen insulation support, which has excellent thermal insulation performance and helps prevent heat from being transferred to the cold block through the support part, thereby maintaining the low temperature state of the cold block. Epoxy fiberglass also has a low thermal expansion coefficient, which ensures the dimensional stability of the screen insulation support under extreme temperature changes and reduces the structural stress and deformation caused by temperature fluctuations. Aluminum honeycomb panels and epoxy fiberglass have good tolerance to space environment, and can resist the erosion of ultraviolet rays, atomic oxygen, high-energy particles, etc., and extend the service life of the refrigerator. Under the joint action of the earth screen and the reflective screen, this device provides the cold block with an on-orbit environment with almost no external heat flow. The cold energy provided by the cold block can be used to achieve low temperature for cryogenic optics and detectors. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 is a schematic diagram of the structure of the refrigerator;

[0025] Figure 2 is a structural schematic diagram of a carbon fiber frame;

[0026] Figure 3 It is a structural schematic diagram of a reflective screen;

[0027] Figure 4 It is a structural schematic diagram of a reflective screen;

[0028] Among them: 1. Carbon fiber frame; 2. Reflection screen; 3. Earth screen; 4. Bottom column; 5. Vertical column; 6. Top column; 7. Diagonal support rod; 8. Plane support plate; 9. Panel; 10. First reflection screen; 11. Second reflection screen; 12. Third reflection screen; 13. Side panel; 14. Screen fixings; 15. Screen insulation support; 16. First cold block; 17. Second cold block; 18. Auxiliary diagonal support rod. DETAILED DESCRIPTION

[0029] The specific implementation modes of the present invention are described below so that those skilled in the art can understand the present invention. However, it should be clear that the present invention is not limited to the scope of the specific implementation modes. For those of ordinary skill in the art, as long as various changes are within the spirit and scope of the present invention as defined and determined by the attached claims, these changes are obvious, and all inventions and creations utilizing the concept of the present invention are protected.

[0030] like Figure 1 As shown, this embodiment provides a sun-synchronous orbit radiation cooler, including a carbon fiber frame 1, on which a reflection screen 2, a cold block and a globe screen 3 are arranged.

[0031] The carbon fiber frame 1 is formed by splicing rods and joints. Carbon fiber has become one of the commonly used materials in the aerospace field due to its light weight and high strength. The carbon fiber frame 1 includes three parts: a bottom column 4, a vertical column 5 and a top column 6. The three parts are interconnected through joints to form a stable three-dimensional structure. Auxiliary diagonal braces 18 are provided on the sides of the bottom column 4 and the vertical column 5 to enhance the mechanical strength of the entire frame. A diagonal brace 7 is obliquely provided on the top column 6 for installing the reflective screen 2; and a flat support plate 8 is provided on the side wall of the vertical column 5 for installing a cold block.

[0032] The reflective screen 2 is composed of a panel 9, a first reflective screen 10, a second reflective screen 11 and a third reflective screen 12 connected in sequence. Side panels 13 are provided on the sides of the reflective screen 2 to enhance the stability of the structure. The first reflective screen 10, the second reflective screen 11 and the third reflective screen 12 are made of aluminum honeycomb panel materials, which have good structural stability and light weight. The reflective screen 2 is coated with a high-reflectivity mirror aluminum layer on the side away from the carbon fiber frame 1 to ensure that all external heat flows from the earth are reflected instead of being reflected to the second cold block 17. For the sun-synchronous orbit with an orbital altitude of 830 to 840 km, the angle between the first reflective screen 10 and the second reflective screen 11 is designed to be 169°, and the angle between the second reflective screen 11 and the third reflective screen 12 is 168°. Such a design can minimize the absorption of solar radiation, thereby improving the cooling efficiency.

[0033] In order to further improve the reflection efficiency and protection structure of the reflective screen 2, a layer of white paint is also coated on the surface of the panel 9 and the side panel 13. The white paint layer can effectively reflect sunlight and reduce the absorption of heat, which is used to cool the reflective screen 2 and reduce the radiation heat exchange of the reflective screen 2 to the second cold block 17.

[0034] The first reflective screen 10, the second reflective screen 11 and the third reflective screen 12 are provided with a screen fixing part 14 and a screen heat insulation support 15 at one end close to the diagonal support rod 7. The screen heat insulation support 15 is made of non-metallic material, preferably epoxy glass fiber reinforced plastic, and is used to fix the reflective screen 2 on the carbon fiber frame 1 and realize heat insulation connection to reduce heat conduction and heat leakage of the spliced ​​reflective screen 2 to the carbon fiber frame 1. This material not only has good heat insulation performance, but also ensures structural stability under extreme temperature differences, thereby effectively preventing the deformation of the reflective screen 2 caused by temperature changes.

[0035] The radiant cooler has three temperature zones, namely normal temperature zone (carbon fiber frame is -30℃~20℃), medium temperature zone (reflection screen is -60℃~-40℃), and low temperature zone (first cold block and second cold block are -100℃~-80℃).

[0036] The earth shield 3 is used to shield the external heat flow from the earth, and the reflective screen 2 is used to reflect the external heat flow from the earth. Under the joint action of the earth shield 3 and the reflective screen 2, an on-orbit environment with almost no external heat flow is provided to the cold block. The cold energy provided by the cold block can be used to achieve low temperature for low-temperature optics and detectors.

[0037] The sun-synchronous orbit radiation cooler provided in this embodiment can achieve efficient and stable cooling effect in the space environment through a carefully designed structural form, efficient reflective screen configuration and optimized thermal isolation measures. The design of the cooler fully considers the particularity of the space environment, adopts a variety of high-performance materials and advanced manufacturing technologies, and ensures its reliability and effectiveness under extreme conditions.

Claims

1. A solar synchronous orbit radiation cooler, characterized in that: It comprises a carbon fiber frame (1), on which a reflection screen (2), a cold block and a globe screen (3) are arranged; The carbon fiber frame (1) comprises a bottom column (4), a vertical column (5) and a top column (6) which are connected to each other; wherein the bottom column (4) is horizontally arranged at the bottom end of the vertical column (5), the top column (6) is horizontally arranged at the top end of the vertical column (5), and the bottom column (4) and the top column (6) are located on opposite sides of the vertical column (5); a diagonal support rod (7) for mounting a reflective screen (2) is arranged on a side of the top column (6) close to the vertical column (5) and extending upwardly, and the side wall of the vertical column (5) is provided with a flat support plate (8) for mounting a cold block; The reflection screen (2) comprises a panel (9), a first reflection screen (10), a second reflection screen (11) and a third reflection screen (12) which are connected in sequence, and side panels (13) are arranged on the sides of the first reflection screen (10), the second reflection screen (11) and the third reflection screen (12); and screen fixing parts (14) and screen heat insulation supports (15) are arranged on the surfaces of one side of the first reflection screen (10), the second reflection screen (11) and the third reflection screen (12) close to the diagonal support rod (7); The cold block comprises a first cold block (16) and a second cold block (17) which are adjacently arranged, wherein the edge of the first cold block (16) is connected to the earth screen (3), and the edge of the second cold block (17) is connected to the reflection screen (2).

2. The sun-synchronous orbit radiation cooler according to claim 1, characterized in that: The first reflection screen (10), the second reflection screen (11) and the third reflection screen (12) are aluminum honeycomb panels, and a high-reflectivity mirror aluminum layer is provided on one side of the first reflection screen (10), the second reflection screen (11) and the third reflection screen away from the carbon fiber frame (1).

3. The sun-synchronous orbit radiation cooler according to claim 1, characterized in that: The angle between the first reflection screen (10) and the second reflection screen (11) is 169°, and the angle between the second reflection screen (11) and the third reflection screen (12) is 168°.

4. The sun-synchronous orbit radiation cooler according to claim 1, characterized in that: The panel (9) and the side panel (13) are thermally connected to the first reflection screen (10).

5. The sun-synchronous orbit radiation cooler according to claim 1, characterized in that: A white paint layer is provided on the surfaces of the panel (9) and the side panels (13).

6. The sun-synchronous orbit radiation cooler according to claim 1, characterized in that: Auxiliary diagonal bracing rods (18) are connected to the sides of the bottom column (4) and the vertical column (5).

7. The sun-synchronous orbit radiation cooler according to claim 1, characterized in that: The screen heat insulation support (15) is made of non-metallic material.

8. The sun-synchronous orbit radiation cooler according to claim 1, characterized in that: The material of the screen heat insulation support (15) is epoxy glass fiber reinforced plastic.

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