Solar cell array for satellite-borne relay terminal

Abstract

The invention discloses a solar cell array for a satellite-borne relay terminal, the solar cell array is arranged on a box body, a rotating shaft is arranged on the box body, one end of a solar cell is fixed on a plane of the box body, and the other end of the solar cell is fixed on a plane of the box body. The other end of the solar cell array drives the solar cell array to be unfolded with the rotating shaft as the circle center and is locked to the face adjacent to the plane where one end of the solar cell array is located of the box body, and the unfolded plane of the solar cell array is parallel to or coplanar with one plane of the box body. The solar cell array has a high storage ratio, the folding envelope is smaller when the solar cell array is folded, the satellite-borne relay terminal structure configuration is fully utilized, the minimum envelope is occupied to the maximum extent, the maximum unfolding area is obtained, and the on-orbit energy requirement of the satellite-borne relay terminal can be met.

Description

Technical Field

[0001] The present invention belongs to the technical field of satellite energy, and particularly relates to a solar array for an on-board relay terminal. Background Art

[0002] With the increasing development of technology, the real-time nature of satellite data has become increasingly important. It will be the future mainstream solution for LEO (Low Earth Orbit) satellites equipped with on-board phased array terminals to conduct data relay transmission with GEO (Geostationary Earth Orbit) satellites. The distance between LEO satellites and GEO satellites is about 40,000 kilometers. The on-board relay terminal requires a high transmission power to make up for the link transmission loss caused by the long distance. However, the energy of traditional on-board relay terminals needs to be obtained from the satellite bus, which has a greater impact on satellite energy. A solar cell is a device that converts solar energy into electrical energy. The larger its sun-facing area, the more energy can be collected, and the higher the degree of self-supply of the on-board terminal. However, due to limitations such as satellite installation space, launch envelope, and interference from surrounding equipment, the on-board terminal cannot be equipped with an overly large solar array surface.

[0003] Currently, on-board phased array relay terminals generally do not have energy equipment installed, and the power supply is obtained from the satellite side. In addition, some technologies adopt a co-array design of solar cells and antenna units, but this design has a greater impact on solar energy acquisition and unit radiation efficiency, and the available area of the solar cells is small, resulting in less energy that can be obtained. In addition, the deployed solar cells generally use circular or rectangular deployment, resulting in a large occupied envelope and relatively serious occlusion of other on-board equipment. Summary of the Invention

[0004] In order to solve the above problems existing in the prior art, the present application provides a solar array for an on-board relay terminal. A foldable and deployable solar array with a high storage ratio designed in the present application can be installed on the on-board terminal, enabling the on-board terminal to independently complete energy supply, reducing the impact on and dependence on satellite energy, so as to overcome the deficiencies of the above prior art.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

[0006] According to the first aspect of the present invention, a solar array for a spaceborne relay terminal is provided. The solar array is installed on a box body. A rotating shaft is provided on the box body. One end of the solar array is fixed on a plane of the box body, and the other end of the solar array drives the solar array to unfold with the rotating shaft as the center of a circle and is locked on an adjacent plane of the plane of the box body where one end of the solar array is located. The plane on which the solar array unfolds is parallel or coplanar with one of the planes of the box body. The solar array structure of the present application is compact. The solar array unfolds in an arc shape on both sides, which can maximize the use of the smallest envelope to obtain the largest unfolded area, thereby obtaining more solar energy.

[0007] Preferably, it further includes multiple support arms for supporting the solar array. When the solar array is folded, the solar array is folded between the multiple support arms. One ends of the multiple support arms are hinged and connected to the rotating shaft. When the solar array unfolds, the angle between the support arms continuously expands. Since the solar array will be affected by various forces in space, the multiple support arms can disperse these forces and provide uniform and stable support force to prevent problems such as deformation and distortion of the solar array and ensure its normal operation; in the folded state, the solar array can be accommodated within the support arms. This design can effectively save space during satellite launch and play a protective role.

[0008] More preferably, the box body further includes a slide rail for guiding the unfolding of the solar array, and the slide rail is arranged below the solar array. The slide rail provides a guiding direction for the unfolding of the solar array and provides corresponding structural support. At the same time, the slide rail can limit the movement trajectory of the unfolding and folding and retracting of the solar array, enabling it to unfold along a predetermined path, thereby ensuring the accuracy and consistency of the unfolding of the solar array, ensuring that the solar array can accurately reach the locking position when unfolding and closely fit with the adjacent plane of the box body, playing a certain protective role to prevent the solar array from deviating from the unfolding path due to accidental factors such as external force impact and vibration.

[0009] Further preferably, the box body further includes a pressing and releasing mechanism and a limiting and locking mechanism. When the solar array is folded, the end of the solar array far from the rotating shaft cooperates with the pressing and releasing mechanism arranged at the edge of the box body for pressing and locking. When the pressing and releasing mechanism is unlocked, the solar array unfolds along the slide rail. When the solar array is fully unfolded, the limiting and locking mechanism arranged on the contact surface between the solar array and the box body cooperates for locking and fixing. The pressing and releasing mechanism tightly presses the solar array folded in the support arm, which can effectively prevent the solar array from accidentally unfolding or shaking due to external forces such as vibration and impact during launch. When the solar array unfolds, the slide rail provides an accurate guide for the unfolding of the solar array, ensuring the consistency and reliability of its unfolding process. When the support arm touches the limiting and locking mechanism, the limiting and locking mechanism quickly locks the solar array to prevent the solar array from shifting or shaking. The coordinated work of the pressing and releasing mechanism and the limiting and locking mechanism ensures that the solar array can work stably and collect solar energy efficiently.

[0010] Further preferably, the rotating shaft is arranged at the vertex of the box body. The box body is a spaceborne phased array relay terminal. An antenna is arranged on the spaceborne phased array relay terminal. The array surface of the solar array after unfolding is parallel to the array surface of the antenna. Two solar arrays are arranged on the spaceborne phased array relay terminal. The unfolding angle of the solar array when it unfolds to touch the limiting and locking mechanism is 270°. Assembling the solar arrays at both ends of the spaceborne phased array relay terminal makes the folding envelope of the solar arrays smaller when folded and makes full use of the structural configuration of the spaceborne relay terminal, further improving the utilization rate of the solar arrays. The solar array is parallel to the antenna array surface, which can enable the solar array to receive sunlight better after unfolding without being blocked by the antenna or other components, thereby improving the power generation efficiency of the solar array and providing more sufficient power for the satellite.

[0011] Further preferably, each solar array includes 6 support arms. When the solar array unfolds to touch the limiting and locking mechanism, the included angle between two adjacent support arms is 45°. This improves the structural stability of the solar array.

[0012] Further preferably, the shape of the solar array between two support arms is an isosceles triangle. The waist of the isosceles triangle is equal to the side length of the spaceborne phased array relay terminal. Each solar array is composed of 6 connected isosceles triangle array surfaces. While improving the structural stability of the solar array, it maximally retains the sun-facing area, obtains more energy, realizes the self-supply of energy for the spaceborne terminal, and the design of the isosceles triangle further enhances the anti-deformation ability of the solar array.

[0013] Further preferably, the slide rail is a 270° fan ring. The 270° fan ring structure has strong stability and strength, can fit the movement trajectory of the solar cell array when it is unfolded and folded and play a protective role, and can be compactly installed on the box to save space.

[0014] Further preferably, the locking and unlocking of the compression release mechanism is achieved by a hot knife, the material of the support arm is carbon fiber, and the solar cell array uses a flexible solar cell sheet, so that the structure of the solar cell array is stable and lightweight.

[0015] According to a second aspect of the present invention, a satellite is provided, on which the solar cell array as described above is arranged.

[0016] Compared with the prior art, the beneficial results of the present invention are:

[0017] (1) High integration with the onboard terminal structure, making full use of the structural characteristics of the onboard phased array relay terminal, installing the solar cell array on both ends of the onboard phased array relay terminal, so that the solar cell array has a smaller envelope when folded, achieving a flexible solar cell array folding method with a high storage ratio, saving space;

[0018] (2) By assembling the solar cell array of the present application, the onboard terminal can be self-supplied with energy, and the largest solar-facing area can be achieved within a limited space, thereby making the most of the solar energy resources on the satellite's surface, collecting more energy, and reducing the impact and dependence on satellite energy;

[0019] (3) Through the coordinated work of the compression release mechanism, the limit locking mechanism and the slide rail, the solar cell array is ensured to be stably unfolded and folded, and a certain safety protection is provided to ensure that the solar cell array can work stably and efficiently collect solar energy. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The accompanying drawings provide further description of the embodiments, and the accompanying drawings are incorporated into and constitute a part of this specification. The accompanying drawings illustrate the embodiments and are used together with the description to explain the principles of the present invention. It will be easy to recognize other embodiments and many expected advantages of the embodiments, as they become better understood by reference to the following detailed description. Other features, objects and advantages of the present application will become more apparent by reading the detailed description of the non-limiting embodiments made with reference to the following drawings:

[0021] Figure 1 is a schematic structural diagram of a solar cell array when folded according to a specific embodiment of the present invention;

[0022] Figure 2 is a schematic structural diagram of a solar cell array when it is folded from another viewing angle according to a specific embodiment of the present invention;

[0023] Figure 3 is a schematic structural diagram of a solar cell array when it is deployed according to a specific embodiment of the present invention;

[0024] Figure 4 is a schematic structural diagram of another perspective of a solar cell array when it is deployed according to a specific embodiment of the present invention;

[0025] Figure 5 is a schematic diagram of a spaceborne relay terminal with a solar cell array installed on a satellite according to a specific embodiment of the present invention;

[0026] Figure 6 is another schematic diagram of a spaceborne relay terminal with a solar cell array installed on a satellite according to a specific embodiment of the present invention.

[0027] The meanings of the numbers in the figure: 1 - box body, 2 - solar cell array, 3 - support arm, 4 - slide rail, 5 - compression and release mechanism, 6 - limit and locking mechanism, 7 - rotating shaft, 8 - solar cell panel. Specific embodiments

[0028] The present application will be further described in detail below with reference to the drawings and embodiments. It can be understood that the specific embodiments described herein are only used to explain the related invention and do not limit the invention. In addition, it should be noted that for the convenience of description, only the parts related to the invention are shown in the drawings.

[0029] In the description of the present invention, it should be noted that the terms "include", "comprise" or any other variant thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements not only includes those elements but also includes other elements not expressly listed, or further includes elements inherent to such process, method, article or device. The terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features.

[0030] In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, the terms "installed", "provided with", "sheathed / connected", "connected", etc. should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection, can be a mechanical connection, can be an electrical connection, can be directly connected, or can be indirectly connected through an intermediate medium, and can be the communication inside two elements. 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 situations.

[0031] For the convenience of those skilled in the art to understand, the present invention will be further described in detail below with reference to the drawings and embodiments.

[0032] Figure 1 The schematic structural diagram when the solar array of a specific embodiment of the present application is folded is shown. Figure 2 The schematic structural diagram of another perspective when the solar array of a specific embodiment of the present application is folded is shown, as Figure 1 and Figure 2 shown, including the solar array 2 installed on the box body 1. A rotating shaft 7 is provided at the vertex position of the box body 1. One end of the solar array 2 is fixed to a plane of the box body 1. The other end of the solar array 2 drives the solar array 2 to unfold with the rotating shaft 7 as the center of the circle, and is locked to the adjacent surface of the plane of the box body 1 where one end of the solar array 2 is located. The plane where the solar array 2 unfolds is parallel or coplanar with one of the planes of the box body 1.

[0033] In a specific embodiment, a rotating shaft 7 is provided at the diagonal of a plane of the box body 1. The solar array 2 is connected to the rotating shaft. There are two solar arrays 2 on the box body 1. When the two solar arrays 2 are folded, they are located on opposite surfaces of the box body 1, and the solar arrays are folded between multiple support arms 3. One end of the support arm 3 is connected to the rotating shaft 7, and the other end is connected to the pressing and releasing mechanism 5. When folding, the solar array 2 is pressed by the pressing and releasing mechanism 5.

[0034] Optionally, multiple support arms 3 lock the pressing and releasing mechanism 5 through a hot knife.

[0035] In a specific embodiment, a slide rail 4 is provided below the rotating shaft 7. One end of the slide rail 4 is located on the plane of the box body 1 where the solar array 2 is located when folded, and the other end of the slide rail 4 is located on the adjacent plane of the above-mentioned box body 1 plane, forming a 270° fan-shaped ring structure.

[0036] In a specific embodiment, the two slide rails 4 corresponding to the lower sides of the two solar arrays 2 are located at the diagonal positions of the box body 1. The pressing and releasing mechanism 5 of one solar array 2 and the limiting and locking mechanism 6 of the other solar array 2 are located on the same plane of the box body 1. The end of the solar array 2 far from the rotating shaft 7 cooperates with the pressing and releasing mechanism 5 provided at the edge of the box body 1 to be pressed and locked.

[0037] In a specific embodiment, the material of the support arm 3 is carbon fiber, and the solar array 2 uses flexible solar cell sheets. This makes the structure of the solar array stable and lightweight.

[0038] Figure 3 The schematic structural diagram when the solar array of a specific embodiment of the present application is unfolded is shown. Figure 4 The schematic structural diagram of another perspective when the solar array of a specific embodiment of the present application is unfolded is shown, as Figure 3 andFigure 4 As shown, the solar array 2 is connected to the slide rail 4 through a transmission mechanism. When receiving the deployment instruction, the compression release mechanism 5 is unlocked by a thermal knife. The solar array 2 is deployed along the slide rail 4 through a rotating shaft 7, and the driving support arm 3 is deployed into an arc-shaped array surface. As the deployment progresses, the included angle between the support arms 3 continuously expands. When the support arm 3 contacts the limit locking mechanism 6, the limit locking mechanism 6 locks the solar array 2. The compression release mechanism 5 and the limit locking mechanism 6 of the same solar array are located on two opposite faces of the box body 1.

[0039] In a specific embodiment, the box body 1 includes six rectangular faces. The array surface of each solar array 2 can be deployed up to 270°. That is, when the solar array 2 is fully deployed, the limit locking mechanism 5 provided on the contact surface between the solar array 2 and the box body 1 cooperates to lock and fix. The solar array 2 includes six support arms. When the solar array 2 is deployed to contact the limit locking mechanism 6, the included angle between two adjacent support arms 3 is 45°. The shape of the solar array 2 between the two support arms 3 is an isosceles triangle. The waist of the isosceles triangle is equal to the side length of the box body 1. Each solar array is composed of six isosceles triangle array surfaces connected together. It maximally retains the solar-facing area and enhances the anti-deformation ability and stability of the solar array 2.

[0040] In a specific embodiment, the box body 1 is a spaceborne phased array relay terminal. The spaceborne phased array relay terminal is provided with a phased array antenna. When the solar array 2 is deployed, the deployed array surface of the solar array 2 is parallel to the phased array antenna and jointly faces the solar-facing surface without being blocked by the antenna. The solar array 2 takes the rotating shaft 7 at the diagonal of the spaceborne phased array relay terminal as a fulcrum and unfolds along the guiding slide rail 4 to form an arc-shaped surrounding solar array 2 relying on both sides of the antenna surface of the spaceborne phased array relay terminal, serving as the design basis for the energy self-supply solar cell of the spaceborne terminal.

[0041] Figure 5 The figure shows a schematic diagram of a spaceborne relay terminal with a solar array according to a specific embodiment of the present application installed on a satellite. Both the solar array 2 and the solar panel 8 of the satellite are in a folded state, as Figure 5 shown, the box body 1 with the solar array 2 is installed on the satellite. The solar array 2 is installed on the upper side of the box body 1 away from the satellite and does not directly contact the satellite. In a specific embodiment, the box body 1 is a spaceborne phased array relay terminal. At this time, it is the launch state of the satellite, and the solar array 2 is folded, effectively reducing the space occupied by the solar array 2 in the launch state. The spaceborne phased array relay terminal is installed on the solar-facing surface of the satellite, which not only meets the beam pointing requirements of the spaceborne terminal antenna for the GEO relay satellite but also effectively utilizes the solar energy on the solar-facing surface of the satellite.

[0042] Figure 6 FIG. 2 shows a schematic diagram of an on-orbit relay terminal with a solar array installed on a satellite. Both the solar array 2 and the satellite solar panel 8 are in the deployed state. As Figure 6 shown, the box body 1 is an on-orbit phased array relay terminal, which is in the deployed state after the satellite is in orbit. After deployment, the two solar arrays 2 are parallel to the antenna array surface on the on-orbit phased array relay terminal. The deployed solar arrays 2, the antenna, and the satellite solar panel 8 are all located on the sun-facing side. After deployment, the solar array 2 can better receive sunlight without being blocked by the antenna or other components, providing more sufficient power for the satellite.

[0043] The present application provides a solar array for an on-orbit relay terminal, which effectively utilizes the structural characteristics of the on-orbit phased array relay terminal, so that the solar array 2 has a smaller stowed envelope when folded, and the design of the solar array 2 when deployed can obtain the maximum deployed area under the conditions of the satellite environment. It not only solves the problems of traditional solar cells, but also further improves the performance of solar cells, effectively solving the on-orbit energy demand of the on-orbit relay terminal. At the same time, the coordinated cooperation of the support arm 3, the slide rail 4, the clamp release mechanism 5 and the limit locking mechanism 6 enables the solar array of the present application to work stably in the space environment, efficiently collect solar energy, and effectively prevent the solar array 2 from being accidentally damaged or shaken due to external forces such as vibration and impact.

[0044] The above description is only a preferred embodiment of the present application and an explanation of the applied technical principles. Those skilled in the art should understand that the scope of the invention involved in the present application is not limited to the technical solution formed by the specific combination of the above technical features, and should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the above inventive concept. For example, the technical solutions formed by mutually replacing the above features with the (but not limited to) technical features with similar functions disclosed in the present application.

Claims

1. A solar array for a spaceborne relay terminal, characterized in that, The solar array is installed on the box body. A rotating shaft is provided on the box body. One end of the solar array is fixed on a plane of the box body. The other end of the solar array drives the solar array to unfold with the rotating shaft as the center of the circle and is locked on an adjacent surface of the plane of the box body where one end of the solar array is located. The plane on which the solar array unfolds is parallel or coplanar with one of the planes of the box body.

2. The solar cell array according to claim 1, wherein It further includes multiple support arms for supporting the solar array. When the solar array is folded, the solar array is folded between the multiple support arms. One end of the multiple support arms is hinged and connected to the rotating shaft. When the solar array unfolds, the included angle between the support arms continuously expands.

3. The solar cell array according to claim 2, wherein, The box body further includes a slide rail for guiding the unfolding of the solar array. The slide rail is arranged below the solar array.

4. The solar cell array according to claim 3, wherein, The box body further includes a pressing and releasing mechanism and a limiting and locking mechanism. When the solar array is folded, the end of the solar array far from the rotating shaft cooperates with the pressing and releasing mechanism arranged at the edge of the box body to be pressed and locked. When the pressing and releasing mechanism is unlocked, the solar array unfolds along the slide rail. When the solar array is fully unfolded, the solar array cooperates with the limiting and locking mechanism arranged on the contact surface with the box body to be locked and fixed.

5. The solar cell array according to claim 4, characterized in that, The rotating shaft is arranged at the vertex of the box body. The box body is a spaceborne phased array relay terminal. An antenna is provided on the spaceborne phased array relay terminal. The array surface after the solar array unfolds is parallel to the array surface of the antenna. Two solar arrays are provided on the spaceborne phased array relay terminal. The unfolding angle of the solar array when it unfolds to contact the limiting and locking mechanism is 270°.

6. The solar cell array according to claim 5, wherein Each solar array includes 6 support arms. When the solar array unfolds to contact the limiting and locking mechanism, the included angle between two adjacent support arms is 45°.

7. The solar cell array according to claim 6, wherein, The shape of the solar array between two support arms is an isosceles triangle. The waist of the isosceles triangle is equal to the side length of the spaceborne phased array relay terminal. Each solar array is composed of 6 array surfaces of isosceles triangles connected together.

8. The solar cell array according to claim 3, wherein The slide rail is a 270° sector ring.

9. The solar cell array according to claim 4, wherein, The locking and unlocking of the pressing and releasing mechanism are realized by a thermal knife. The material of the support arm is carbon fiber. The solar array uses flexible solar cells.

10. A satellite, on which the solar array as described in any one of claims 1-9 is provided.

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