Parabolic cylinder condensation type energy system for space

Abstract

The invention relates to a parabolic cylinder condensation type energy system for space. The parabolic cylinder condensation type energy system comprises a primary mirror, a secondary mirror, a solar cell and a heat dissipation assembly. The primary mirror is a paraboloid type concave reflector, and the secondary mirror is a hyperboloid type convex reflector; the area of the primary mirror is larger than that of the secondary mirror. A first coating is arranged on the concave surface of the primary mirror, a second coating is arranged outside the first coating, and a third coating 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 dissipation assembly is located on the convex face of the primary mirror and the back face of the solar cell. Heat generated by 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 carry out radiation heat dissipation 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 of the solar cell is improved.

Description

Technical Field

[0001] The present invention relates to the field of solar power generation, and particularly to a parabolic cylindrical concentrating energy system for space use. Background Art

[0002] In today's aerospace field, the space energy system is the key support for the normal operation of spacecraft. Among them, rigid solar wings and flexible solar wings are two of the most common space energy acquisition devices, which play important roles in different space missions. Rigid solar wings usually use high-strength materials such as aluminum plates and carbon fiber as substrates, and solar cells are firmly installed on these rigid substrates. The main feature of flexible solar wings is their good flexibility and foldability. They use thin and flexible substrate materials such as fiberglass boards and polyimide films, and solar cells are integrated on this flexible substrate. Most of the existing solar cells use triple-junction gallium arsenide solar cells. In order to reduce the large-area use of solar cells, sunlight is usually reflected and concentrated twice. Since solar cells in space cannot dissipate heat through convection, but solar cells generate a large amount of heat during operation, there is an urgent need for an energy system with good heat dissipation ability. Summary of the Invention

[0003] (1) Technical Problems to be Solved

[0004] The present invention provides a parabolic cylindrical concentrating energy system for space use, aiming to improve the heat dissipation ability of solar cells in space on the premise of ensuring the power generation.

[0005] (2) Technical Solutions

[0006] To solve the above problems, the present invention provides a parabolic cylindrical concentrating energy system for space use, which includes: a primary mirror, a secondary mirror, a solar cell, and a heat dissipation component;

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

[0008] A first coating is provided on the concave surface of the primary mirror, and a second coating is provided outside the first coating. A third coating is provided on the convex surface of the primary mirror. The primary mirror can concentrate and reflect sunlight onto the secondary mirror;

[0009] The convex surface of the secondary mirror faces the concave surface of the primary mirror;

[0010] The solar cell faces the convex surface of the secondary mirror, and the secondary mirror can reflect the sunlight reflected by the primary mirror onto the solar cell again;

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

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

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

[0014] On the primary mirror, the main heat dissipation pipes are respectively arranged on both sides along the radial direction of the primary mirror;

[0015] A plurality of the heat dissipation branch pipes are arranged on the back surfaces of the primary mirror and the solar cell. The heat dissipation branch pipes are located between the two main heat dissipation pipes, and the ends of the heat dissipation branch pipes are communicated with the main heat dissipation pipes.

[0016] Preferably, coolant is arranged in both the main heat dissipation pipes and the heat dissipation branch pipes; 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 can enter one main heat dissipation pipe from the heat dissipation inlet, then flow into the other main heat dissipation pipe through the heat dissipation branch pipes, and finally flow out from the heat dissipation outlet.

[0018] Preferably, the parabolic cylindrical surface concentrating energy system in the space further includes a satellite body;

[0019] The primary mirror and the solar cell are both arranged on the satellite body. A strip-shaped hole matching the shape of the solar cell is arranged on the primary mirror, and sunlight can shine on the solar cell through the strip-shaped hole.

[0020] Preferably, a radiation cooling plate is further arranged on the satellite body, and the radiation cooling plate is located on one side of the convex surface of the primary mirror.

[0021] Preferably, a support rod extending towards the concave side of the primary mirror is arranged on the satellite body, and the secondary mirror is arranged 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 radiation layer.

[0024] (III) Beneficial effects

[0025] In the present invention, the primary mirror is responsible for reflecting sunlight for the first time and converging it to the convex surface of the secondary mirror. The secondary mirror is responsible for reflecting the sunlight converged by the primary mirror a second time onto the solar cell. The solar cell is used to convert the sunlight energy converged by the primary mirror and the secondary mirror into electrical energy. By setting the primary mirror and the secondary mirror to focus sunlight onto the solar cell, while ensuring the power generation, the large-area use of the battery panel is reduced, and the cost is lowered. Additionally, by providing a second coating on the concave surface of the primary mirror and a third coating on the convex surface, the heat generated on the solar cell can be transferred to the second coating provided on the concave surface of the primary mirror and the third coating provided on the convex surface. The second coating and the third coating dissipate heat through radiation, enabling both the concave surface and the convex surface of the primary mirror to achieve radiative heat dissipation, increasing the heat dissipation area and improving the heat dissipation efficiency of the solar cell. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 FIG. is a schematic diagram of the overall structure of the parabolic cylindrical concentrating energy system for space use according to the present invention;

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

[0028] DESCRIPTION OF THE REFERENCE NUMERALS

[0029] 1: primary mirror; 2: secondary mirror; 3: solar cell; 4: heat dissipation assembly; 41: main heat dissipation pipe; 42: heat dissipation branch pipe; 5: satellite body; 51: radiation cooling plate; 52: support rod. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0030] In order to better explain the present invention for easier understanding, the present invention will be described in detail below with reference to the accompanying drawings and through specific embodiments.

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

[0032] In addition, in the present invention, descriptions such as "first" and "second" are only for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the quantity of the indicated technical features. Thus, features defined as "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present invention, "a plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0033] In the present invention, unless otherwise clearly specified and defined, terms such as "connection" and "fixation" shall be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components or the interaction relationship between two components, unless otherwise clearly defined. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0034] The present invention provides a parabolic cylindrical concentrating energy system for space. The parabolic cylindrical concentrating energy system for space 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 reflecting mirror, and the secondary mirror 2 is a hyperbolic convex reflecting mirror. The area of the primary mirror 1 is larger than that of the secondary mirror 2. The shapes of both the primary mirror 1 and the secondary mirror 2 can be regarded as formed by bending a rectangular sheet. And 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 converge and reflect sunlight onto the secondary mirror 2. The first coating is a reflective layer, and its optical properties are high solar light reflectivity and high infrared emissivity. As much sunlight as possible is reflected and converged onto the solar cell, and at the same time, efficient infrared radiation heat dissipation can also be carried out on the sunny side (i.e., the concave surface of the primary mirror 1) facing the sun direction. Specifically, the first coating includes silver plating, aluminum plating, dielectric film coating, etc. The second coating and the third coating are radiation layers, and their optical properties are high infrared emissivity, and efficient infrared radiation heat dissipation is carried out facing the cold black direction. Specifically, the second coating includes organic or inorganic materials. The organic ones include F46, PI, polyurethane, etc.; the inorganic ones include silicon dioxide, transparent ceramics, etc. The third coating includes thermal control paint and a thin film with high infrared emissivity of the material itself.

[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. The secondary mirror 2 can reflect the sunlight reflected by the primary mirror 1 onto the solar cell 3 again. The heat dissipation component 4 is located on the convex surface of the primary mirror 1 and the back surface of the solar cell 3. The heat generated on the battery panel of the solar cell 3 can be transferred to the convex surface of the primary mirror 1 through the heat dissipation component 4, and efficient radiation heat dissipation is achieved by using the second coating.

[0037] In the technical solution of the present invention, the primary mirror 1 is responsible for reflecting the sunlight for the first time and converging it to the convex surface of the secondary mirror 2. The secondary mirror 2 is responsible for reflecting the sunlight converged by the primary mirror 1 a second time onto the solar cell 3. The solar cell 3 is used to convert the sunlight energy converged by the primary mirror 1 and the secondary mirror 2 into electric energy. Currently, the highest photoelectric conversion efficiency achievable by a concentrating solar cell has reached 47%. In this application, by arranging the primary mirror 1 and the secondary mirror 2 to focus sunlight onto the solar cell 3, while ensuring the power generation power, the large-area use of the battery panel is reduced, and the cost is lowered. In addition, by providing 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 and the third coating on the convex surface of the primary mirror 1. The second coating and the third coating 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] Further, the heat dissipation assembly 4 includes a pair of main heat dissipation pipes 41 and a plurality of heat dissipation branch pipes 42. On the primary mirror 1, main heat dissipation pipes 41 are respectively arranged on both sides in the radial direction of the primary mirror 1. A plurality of heat dissipation branch pipes 42 are arranged on the back surfaces of the primary mirror 1 and the solar cell 3. The heat dissipation branch pipes 42 are located between the two main heat dissipation pipes 41, and the ends of the heat dissipation branch pipes 42 are communicated with the main heat dissipation pipes 41. Coolant is provided in both the main heat dissipation pipes 41 and the heat dissipation branch 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 into the other main heat dissipation pipe 41 through the heat dissipation branch pipes 42, and finally flow out from the heat dissipation outlet.

[0039] In the above solution, the material of the primary mirror 1 is a lightweight thin film, which has excellent planar heat conduction ability. The thin film mirror surface is pasted on the surfaces of the main heat dissipation pipe 41 and the branch heat dissipation pipes 42. The heat generated by the solar cell is transferred to the main heat dissipation pipe 41 through the branch heat dissipation pipes 42, and then conducted into the branch heat dissipation pipes 42 on the entire primary mirror 1. The branch heat dissipation pipes transfer heat to the second coating and the third coating on the primary mirror through heat transfer. The second coating and the third coating dissipate heat to the cold black space through radiation. The forms of heat dissipation mainly include radiative heat dissipation, conductive heat dissipation, convective heat dissipation, and evaporative heat dissipation. Since there is no air in space when the satellite body in this application operates in space, convective heat dissipation cannot be carried out, and evaporative heat dissipation will make the structure complex. In this application, branch heat dissipation pipes are arranged on the back of the solar cell. The heat generated by the solar cell during operation can be transferred to the coolant through conductive heat dissipation. The coolant then flows through the main heat dissipation pipe into the branch heat dissipation pipes on the convex surface of the primary mirror. The branch heat dissipation pipes 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 makes the primary mirror in this application not only play the role of converging sunlight but also play the role of increasing the heat dissipation efficiency. The second coating and the third coating on the convex surface of the primary mirror have a high infrared emissivity and perform efficient infrared radiative heat dissipation facing the cold black direction, thereby realizing efficient heat dissipation of the solar cell and ensuring the normal operation of the solar cell.

[0040] Furthermore, the space parabolic cylindrical concentrator energy system further includes a satellite body 5. The primary mirror 1 and the solar cell 3 are both arranged on the satellite body 5. The primary mirror 1 is provided with strip-shaped holes matching the shape of the solar cell 3, and sunlight can shine on the solar cell 3 through the strip-shaped holes. In this embodiment, the shape of the solar cell 3 is a rectangular plate. After the sunlight is reflected twice by the primary mirror 1 and the secondary mirror 2, it is in a strip shape and is completely located on the solar cell 3.

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

[0042] It should be understood that the above description of the specific embodiments of the present invention is only for explaining the technical route and features of the present invention, and its purpose is 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 above specific embodiments. Any changes or modifications made within the scope of the claims of the present invention should be covered by the protection scope of the present invention.

Claims

1. A parabolic cylindrical concentrating energy system for space, characterized in that: The parabolic cylindrical concentrating energy system for space comprises: 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 hyperbolic convex reflector; the area of ​​the primary mirror (1) is larger than the area of ​​the secondary mirror (2); A first coating layer is arranged on the concave surface of the primary mirror (1), and a second coating layer is arranged outside the first coating layer, and a third coating layer is arranged on the convex surface of the primary mirror (1), and the primary mirror (1) is capable of converging sunlight and reflecting 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) is capable of reflecting the sunlight reflected by the primary mirror (1) back onto the solar cell (3); The heat dissipation component (4) is located on the convex surface of the primary mirror (1) and on the back surface of the solar cell (3).

2. The parabolic concentrating energy system for space use according to claim 1, characterized in that: The first coating layer is a reflective layer, and the second coating layer and the third coating layer are both radiation layers.

3. The parabolic concentrating energy system for space use according to claim 2, characterized in that: The heat dissipation assembly (4) comprises a pair of heat dissipation main pipes (41) and a plurality of heat dissipation branch pipes (42); The main heat dissipation pipes (41) are respectively arranged on both sides of the main mirror (1) in the radial direction of the main mirror (1); A plurality of heat dissipation branch pipes (42) are arranged on the back of the primary mirror (1) and the solar cell (3); the heat dissipation branch pipes (42) are located between two heat dissipation main pipes (41), and the ends of the heat dissipation branch pipes (42) are connected to the heat dissipation main pipes (41).

4. The parabolic concentrating energy system for space use according to claim 3, characterized in that: Cooling liquid is provided in both the heat dissipation main pipe (41) and the heat dissipation branch pipe (42); one end of one of the heat dissipation main pipes (41) is a heat dissipation inlet, and one end of the other heat dissipation main pipe (41) is a heat dissipation outlet; The coolant can enter one of the heat dissipation main pipes (41) through the heat dissipation inlet, then flow into another of the heat dissipation main pipes (41) through the heat dissipation branch pipe (42), and finally flow out from the heat dissipation outlet.

5. The parabolic concentrating energy system for space use according to any one of claims 1 to 4, characterized in that: The space parabolic cylindrical concentrating energy system also includes a satellite body (5); The primary mirror (1) and the solar cell (3) are both arranged on the satellite body (5); the primary mirror (1) is provided with a strip-shaped hole matching the shape of the solar cell (3), and sunlight can be projected onto the solar cell (3) through the strip-shaped hole.

6. The parabolic concentrating energy system for space use according to claim 5, characterized in that: The satellite body (5) is also provided with a radiation cooling plate (51), and the radiation cooling plate (51) is located on one side of the convex surface of the primary mirror (1).

7. The parabolic concentrating energy system for space use according to claim 6, 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 arranged on the support rod (52).

8. The parabolic concentrating energy system for space use according to any one of claims 1 to 4, characterized in that: The secondary mirror (2) is located at the focus of the primary mirror (1).

9. The parabolic concentrating energy system for space use according to any one of claims 1 to 4, characterized in that: The first coating layer is a reflective layer, and the second coating layer is a radiation layer.

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