A parabolic cylindrical concentrator energy system for space

Abstract

The application relates to a parabolic cylindrical light-concentrating energy system for space, which comprises a primary mirror, a secondary mirror, a solar cell and a heat radiating assembly. The primary mirror is a parabolic concave reflector, and the secondary mirror is a hyperboloidal convex reflector; the area of the primary mirror is larger than that of the secondary mirror. A first plating layer is arranged on the concave surface of the primary mirror, a second plating layer is arranged outside the first plating layer, and a third plating layer is arranged on the convex surface of the primary mirror. The convex surface of the secondary mirror is opposite to the concave surface of the primary mirror. The solar cell faces the convex surface of the secondary mirror, and the secondary mirror can reflect the sunlight reflected by the primary mirror to the solar cell again. The heat radiating assembly is arranged on the convex surface of the primary mirror and the back surface of the solar cell. The heat generated on the solar cell can be transmitted to the second plating layer arranged on the concave surface of the primary mirror and the third plating layer arranged on the convex surface of the primary mirror, and the second plating layer and the third plating layer can radiate heat through radiation, so that the concave surface and the convex surface of the primary mirror can realize radiation heat dissipation, the heat dissipation area is increased, and the heat dissipation efficiency on the solar cell is improved.

Description

Technical Field

[0001] This invention relates to the field of solar power generation, and more particularly to a space-based parabolic cylindrical concentrating energy system. Background Technology

[0002] In today's aerospace field, space energy systems are crucial for the normal operation of spacecraft. Rigid solar arrays and flexible solar arrays are two of the most common space energy harvesting devices, playing important roles in various space missions. Rigid solar arrays typically use high-strength materials such as aluminum plates and carbon fiber as substrates, on which solar cells are securely mounted. Flexible solar arrays are characterized by their excellent flexibility and foldability. They utilize thin, flexible substrate materials such as fiberglass boards and polyimide films, on which solar cells are integrated. Most existing solar cells use triple-junction gallium arsenide solar cells. To reduce the large area required for solar cells, secondary reflection and focusing of sunlight are typically employed. Since solar cells in space cannot dissipate heat through convection, yet generate significant amounts of heat during operation, a high-heat-dissipation energy system is urgently needed. Summary of the Invention

[0003] (a) Technical problems to be solved

[0004] This invention provides a space-use parabolic cylindrical concentrating energy system, which aims to improve the heat dissipation capacity of solar cells in space while ensuring power generation.

[0005] (II) Technical Solution

[0006] To address the aforementioned problems, the present invention provides a space-use parabolic cylindrical concentrating energy system, comprising: a primary mirror, a secondary mirror, a solar cell, and a heat dissipation assembly;

[0007] The primary mirror is a parabolic concave reflector, and the secondary mirror is a hyperboloid convex reflector; the area of ​​the primary mirror is larger than the area of ​​the secondary mirror.

[0008] The primary mirror has a first coating on its concave surface and a second coating on the outside of the first coating. The primary mirror has a third coating on its convex surface. The primary mirror can focus sunlight and reflect it onto the secondary mirror.

[0009] The convex surface of the secondary mirror is opposite to the concave surface of the primary mirror;

[0010] The convex surface of the solar cell faces the secondary mirror, and the secondary mirror can reflect the sunlight reflected from the primary mirror back onto the solar cell.

[0011] The heat dissipation assembly is located on the convex surface of the primary mirror and on the back of the solar cell.

[0012] Preferably, the first coating is a reflective layer, and the second and third coatings are both radiative layers.

[0013] Preferably, the heat dissipation assembly includes a pair of main heat dissipation pipes and a plurality of branch heat dissipation pipes;

[0014] The heat dissipation main pipe is provided on both sides along the radial direction of the main mirror.

[0015] Multiple heat dissipation branch pipes are provided on the back of the main mirror and the solar cell. The heat dissipation branch pipes are located between two heat dissipation main pipes, and the ends of the heat dissipation branch pipes are connected to the heat dissipation main pipes.

[0016] Preferably, both the main heat dissipation pipe and the branch heat dissipation pipe are filled with coolant; one end of one main heat dissipation pipe is a heat dissipation inlet, and one end of the other main heat dissipation pipe is a heat dissipation outlet.

[0017] The coolant enters one of the main heat dissipation pipes through the heat dissipation inlet, then flows into another main heat dissipation pipe through the heat dissipation branch pipe, and finally flows out from the heat dissipation outlet.

[0018] Preferably, the space-based parabolic cylindrical concentrating energy system further includes the satellite itself;

[0019] Both the primary mirror and the solar cell are mounted on the satellite body. The primary mirror has a strip-shaped aperture that matches the shape of the solar cell, allowing sunlight to shine onto the solar cell through the strip-shaped aperture.

[0020] Preferably, the satellite body is further provided with a radiant cooling plate, which is located on one side of the convex surface of the primary mirror.

[0021] Preferably, the satellite body is provided with a support rod extending toward one side of the concave surface of the primary mirror, and the secondary mirror is disposed on the support rod.

[0022] Preferably, the secondary mirror is located at the focal point of the primary mirror.

[0023] Preferably, the first coating is a reflective layer and the second coating is a radiative layer.

[0024] (III) Beneficial Effects

[0025] In this invention, the primary mirror is responsible for the first reflection and focusing of sunlight onto the convex surface of the secondary mirror. The secondary mirror then reflects the sunlight focused by the primary mirror onto the solar cell. The solar cell converts the energy of the sunlight focused by the primary and secondary mirrors into electrical energy. By using a primary and secondary mirror to focus sunlight onto the solar cell, the area of ​​the solar panel used is reduced, thus lowering costs while ensuring power generation. Furthermore, by applying a second coating to the concave surface of the primary mirror and a third coating to the convex surface, the heat generated on the solar cell can be transferred to these coatings. The second and third coatings then radiate heat, allowing both the concave and convex surfaces of the primary mirror to dissipate heat, increasing the heat dissipation area and improving the heat dissipation efficiency of the solar cell. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of the overall structure of the space parabolic cylindrical concentrating energy system of the present invention;

[0027] Figure 2 This is a schematic diagram of the overall structure of the space parabolic cylindrical concentrating energy system of the present invention from another perspective.

[0028] [Explanation of Labels in the Attached Image]

[0029] 1: Primary mirror; 2: Secondary mirror; 3: Solar cell; 4: Heat dissipation assembly; 41: Main heat dissipation pipe; 42: Branch heat dissipation pipe; 5: Satellite body; 51: Radiation cooling plate; 52: Support rod. Detailed Implementation

[0030] To better explain and facilitate understanding of the present invention, the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0031] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0032] Furthermore, in this invention, descriptions involving "first," "second," etc., are for descriptive purposes only and should not be construed as indicating or implying their 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.

[0033] In this invention, unless otherwise explicitly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection or an electrical connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean 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.

[0034] This invention provides a space parabolic cylindrical concentrating energy system, which includes: a primary mirror 1, a secondary mirror 2, a solar cell 3, and a heat dissipation component 4;

[0035] The primary mirror 1 is a parabolic concave reflector, and the secondary mirror 2 is a hyperboloid convex reflector. The area of ​​the primary mirror 1 is larger than that of the secondary mirror 2. Both the primary mirror 1 and the secondary mirror 2 can be considered as rectangular sheets bent into shape. The primary mirror 1 can be a thin film. A first coating is provided on the concave surface of the primary mirror 1, and a second coating is provided outside the first coating. A third coating is provided on the convex surface of the primary mirror 1. The primary mirror 1 can focus and reflect sunlight onto the secondary mirror 2. The first coating is a reflective layer with high solar reflectivity and high infrared emissivity. It reflects and focuses sunlight onto the solar cell as much as possible, while the sun-facing side (i.e., the concave surface of the primary mirror 1) can also efficiently dissipate heat through infrared radiation. Specifically, the first coating includes silver plating, aluminum plating, dielectric film plating, etc. The second and third coatings are radiative layers with high infrared emissivity, providing efficient infrared radiation heat dissipation with their surface facing the cool black direction. Specifically, the second coating includes organic or inorganic materials; organic materials include F46, PI, polyurethane, etc.; inorganic materials include silicon dioxide, transparent ceramics, etc. The third coating includes thermal control paint and thin films with intrinsically high infrared emissivity.

[0036] The convex surface of the secondary mirror 2 faces the concave surface of the primary mirror 1, and the secondary mirror 2 is located at the focal point of the primary mirror 1. The solar cell 3 faces the convex surface of the secondary mirror 2, and the secondary mirror 2 can reflect sunlight reflected from the primary mirror 1 back onto the solar cell 3. The heat dissipation assembly 4 is located on the convex surface of the primary mirror 1 and the back of the solar cell 3. The heat generated on the solar cell 3 can be transferred to the convex surface of the primary mirror 1 through the heat dissipation assembly 4, achieving efficient radiative heat dissipation using the second coating.

[0037] In the technical solution of this invention, the primary mirror 1 is responsible for the first reflection and focusing of sunlight onto the convex surface of the secondary mirror 2. The secondary mirror 2 is responsible for the second reflection of the sunlight focused by the primary mirror 1 onto the solar cell 3. The solar cell 3 is used to convert the sunlight energy focused by the primary mirror 1 and the secondary mirror 2 into electrical energy. Currently, the highest photoelectric conversion efficiency achievable by concentrating solar cells has reached 47%. This application focuses sunlight onto the solar cell 3 by setting the primary mirror 1 and the secondary mirror 2, reducing the area of ​​the solar panel used and lowering costs while ensuring power generation. In addition, by setting a second coating on the concave surface of the primary mirror 1 and a third coating on the convex surface, the heat generated on the solar cell 3 can be transferred to the second coating on the concave surface of the primary mirror 1 and the third coating on the convex surface. The second and third coatings dissipate heat through radiation, improving the heat dissipation efficiency of the solar cell 3 and ensuring the normal operation of the solar cell 3 in space.

[0038] Furthermore, the heat dissipation assembly 4 includes a pair of main heat dissipation pipes 41 and multiple branch heat dissipation pipes 42. On the main mirror 1, main heat dissipation pipes 41 are respectively arranged on both sides along the radial direction of the main mirror 1. Multiple branch heat dissipation pipes 42 are arranged on the back of the main mirror 1 and the solar cell 3, with each branch heat dissipation pipe 42 located between two main heat dissipation pipes 41 and its end connected to a main heat dissipation pipe 41. Coolant is contained within both the main heat dissipation pipes 41 and the branch heat dissipation pipes 42; one end of one main heat dissipation pipe 41 is a heat dissipation inlet, and one end of the other main heat dissipation pipe 41 is a heat dissipation outlet. The coolant can enter one main heat dissipation pipe 41 through the heat dissipation inlet, then flow through the branch heat dissipation pipe 42 into the other main heat dissipation pipe 41, and finally flow out from the heat dissipation outlet.

[0039] In the above scheme, the primary mirror 1 is made of a lightweight thin film with excellent planar thermal conductivity. The thin film mirror is attached to the surface of the heat dissipation main pipe 41 and the heat dissipation branch pipe 42. The heat generated by the solar cell is transferred to the heat dissipation main pipe 41 through the heat dissipation branch pipe 42, and then conducted into the heat dissipation branch pipe 42 on the entire primary mirror 1. The heat dissipation branch pipe transfers the heat to the second and third coatings on the primary mirror through heat transfer. The second and third coatings dissipate the heat to the cold black space through radiation. The main forms of heat dissipation are radiation, conduction, convection, and evaporation. Since the satellite in this application operates in space, there is no air, so convection is not possible. Evaporation would complicate the structure. This application solves this problem by installing heat dissipation branches on the back of the solar cells. The heat generated by the solar cells during operation can be transferred to the coolant through conduction. The coolant then flows through the heat dissipation main to the heat dissipation branches on the convex surface of the primary mirror. The heat dissipation branches then conduct the heat to the third coating on the convex surface and the second coating on the concave surface of the primary mirror, greatly increasing the heat dissipation area. This allows the primary mirror in this application to not only concentrate sunlight but also increase heat dissipation efficiency. The second and third coatings on the convex surface of the primary mirror have high infrared emissivity and face the cool black direction for efficient infrared radiation heat dissipation, thereby achieving efficient heat dissipation of the solar cells and ensuring their normal operation.

[0040] Furthermore, the space-based parabolic cylindrical concentrating energy system also includes the satellite body 5. The primary mirror 1 and the solar cell 3 are both mounted on the satellite body 5. The primary mirror 1 has a strip-shaped aperture that matches the shape of the solar cell 3, allowing sunlight to shine onto the solar cell 3 through the aperture. In this embodiment, the solar cell 3 is shaped like a rectangular plate. After secondary reflection by the primary mirror 1 and the secondary mirror 2, the sunlight is arranged in stripes and is completely concentrated on the solar cell 3.

[0041] Finally, a cooling plate 51 is also installed on the satellite body 5, located on one side of the convex surface of the primary mirror 1. A support rod 52 extending towards the concave surface of the primary mirror 1 is also installed on the satellite body 5, and the secondary mirror 2 is mounted on the support rod 52. The support rod 52 is mainly used for the installation and positioning of the secondary mirror, providing sufficient rigidity and strength to ensure the relative positional relationship between the primary and secondary mirrors.

[0042] It should be understood that the above description of specific embodiments of the present invention is only for illustrating the technical approach and features of the present invention, and is intended to enable those skilled in the art to understand the content of the present invention and implement it accordingly. However, the present invention is not limited to the specific embodiments described above. All changes or modifications made within the scope of the claims of the present invention should be covered within the protection scope of the present invention.

Claims

1. A space-based parabolic cylindrical concentrating energy system, characterized in that, The space parabolic cylindrical concentrating energy system includes: a primary mirror (1), a secondary mirror (2), a solar cell (3), and a heat dissipation component (4). The primary mirror (1) is a parabolic concave reflector, and the secondary mirror (2) is a hyperboloid convex reflector; the area of ​​the primary mirror (1) is larger than the area of ​​the secondary mirror (2); The concave surface of the primary mirror (1) is provided with a first coating layer, and a second coating layer is provided outside the first coating layer. The convex surface of the primary mirror (1) is provided with a third coating layer. The primary mirror (1) can focus sunlight and reflect it onto the secondary mirror (2). The convex surface of the secondary mirror (2) is opposite to the concave surface of the primary mirror (1); The solar cell (3) faces the convex surface of the secondary mirror (2), and the secondary mirror (2) can reflect the sunlight reflected from the primary mirror (1) back onto the solar cell (3). The heat dissipation component (4) is located on the convex surface of the main mirror (1) and on the back of the solar cell (3); The heat dissipation assembly (4) includes a pair of heat dissipation main pipes (41) and a plurality of heat dissipation branch pipes (42). On the main mirror (1), heat dissipation main pipes (41) are respectively provided on both sides along the radial direction of the main mirror (1). Multiple heat dissipation pipes (42) are provided on the back of the main mirror (1) and the solar cell (3). The heat dissipation pipes (42) are located between two heat dissipation main pipes (41), and the ends of the heat dissipation pipes (42) are connected to the heat dissipation main pipes (41). The main mirror (1) is in the form of a film, and the main mirror (1) is attached to the surface of the heat dissipation main pipe (41) and the heat dissipation branch pipe (42).

2. The space-use parabolic cylindrical concentrating energy system as described in claim 1, characterized in that, The first coating is a reflective layer, and the second and third coatings are both radiative layers.

3. The space-use parabolic cylindrical concentrating energy system as described in claim 2, characterized in that, Coolant is provided in both the main heat dissipation pipe (41) and the branch heat dissipation pipe (42); one end of the main heat dissipation pipe (41) is a heat dissipation inlet, and one end of the other main heat dissipation pipe (41) is a heat dissipation outlet. The coolant can enter one of the main heat dissipation pipes (41) through the heat dissipation inlet, then flow into another main heat dissipation pipe (41) through the heat dissipation branch pipe (42), and finally flow out from the heat dissipation outlet.

4. The space-use parabolic cylindrical concentrating energy system as described in any one of claims 1-3, characterized in that, The space-use parabolic cylindrical concentrating energy system also includes the satellite body (5); The primary mirror (1) and the solar cell (3) are both mounted on the satellite body (5). The primary mirror (1) has a strip-shaped hole that matches the shape of the solar cell (3), allowing sunlight to shine onto the solar cell (3) through the strip-shaped hole.

5. The space-use parabolic cylindrical concentrating energy system as described in claim 4, characterized in that, The satellite body (5) is also provided with a radiant cooling plate (51), which is located on one side of the convex surface of the main mirror (1).

6. The space-use parabolic cylindrical concentrating energy system as described in claim 5, characterized in that, The satellite body (5) is provided with a support rod (52) extending toward one side of the concave surface of the primary mirror (1), and the secondary mirror (2) is provided on the support rod (52).

7. The space-use parabolic cylindrical concentrating energy system as described in any one of claims 1-3, characterized in that, The secondary mirror (2) is located at the focal point of the primary mirror (1).

8. The space-use parabolic cylindrical concentrating energy system as described in any one of claims 1-3, characterized in that, The first coating is a reflective layer, and the second coating is a radiative layer.

Images