A solar cell array for a satellite-borne relay terminal

Abstract

The present invention discloses a solar cell array for a satellite-borne relay terminal, wherein the solar cell array is mounted on a box having a rotating shaft. One end of the solar cell is fixed to a plane of the box, and the other end of the solar cell array drives the solar cell array to unfold with the rotating shaft as the center of a circle and is locked to an adjacent surface of the box plane where one end of the solar cell array is located. The unfolded plane of the solar cell array is parallel to or coplanar with one of the planes of the box. The solar cell array of the present application has a high storage ratio and a smaller envelope when folded, making full use of the structural configuration of the satellite-borne relay terminal, maximizing the occupied minimum envelope to obtain the maximum unfolded area, and helping to meet the on-orbit energy needs of the satellite-borne relay terminal.

Description

Technical Field

[0001] The invention belongs to the technical field of satellite energy, and in particular relates to a solar cell array for a satellite-borne relay terminal. Background Art

[0002] With the advancement of technology, the real-time nature of satellite data is becoming increasingly important. LEO (Low Earth Orbit) satellites equipped with onboard phased array terminals will relay data to GEO (Geostationary Earth Orbit) satellites, which will be the mainstream solution in the future. The distance between LEO and GEO satellites is approximately 40,000 kilometers. Onboard relay terminals require high transmission power to compensate for the link transmission losses caused by long distances. Traditional onboard relay terminals draw their energy from the satellite bus, significantly impacting satellite energy consumption. Solar cells convert solar energy into electrical energy. The larger their solar-facing area, the more energy they can collect, and the more autonomous the onboard terminal. However, due to limitations in satellite installation space, launch envelope, and interference from surrounding equipment, onboard terminals cannot be equipped with overly large solar arrays.

[0003] Currently, satellite-borne phased array relay terminals generally lack power equipment; their power is derived from the satellite itself. Some technologies employ a co-array design with solar cells and antenna elements, but this design significantly impacts solar energy capture and unit radiation efficiency. Furthermore, the solar cells have a limited usable area, resulting in limited energy capture. Furthermore, deployable solar cells are typically circular or rectangular, resulting in a large footprint and significant obstruction to other onboard equipment. Summary of the Invention

[0004] In order to solve the above-mentioned problems existing in the prior art, the present application provides a solar cell array for a satellite-borne relay terminal. The foldable and expandable high-storage ratio solar cell array designed in the present application can be installed on the satellite-borne terminal, so that the satellite-borne terminal can independently complete energy supply, reduce the impact and dependence on satellite energy, and overcome the shortcomings of the above-mentioned prior art.

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

[0006] According to a first aspect of the present invention, a solar cell array for a satellite-borne relay terminal is provided. The solar cell array is mounted on a housing having a rotating shaft. One end of the solar cell array is fixed to a plane of the housing. The other end of the solar cell array drives the solar cell array to unfold about the rotating shaft and is locked to a plane adjacent to the plane of the housing where the one end of the solar cell array is located. The plane in which the solar cell array is unfolded is parallel to or coplanar with one of the planes of the housing. The solar cell array of the present application has a compact structure. By unfolding in an arc shape on both sides, the solar cell array can maximize the unfolded area while occupies a minimum envelope, thereby maximizing solar energy.

[0007] Preferably, the solar array also includes multiple support arms supporting the solar cell array. When the solar cell array is folded, the solar cell array is folded between the multiple support arms. One end of the multiple support arms is hinged and connected to a rotating shaft. When the solar cell array is unfolded, the angle between the support arms continuously increases. Because the solar cell array is subject to various forces in space, the multiple support arms can disperse these forces and provide uniform and stable support, preventing deformation and distortion of the solar cell array and ensuring its normal operation. In the folded state, the solar cell array can be stored within the support arms. This design can effectively save space during satellite launch and provide protection.

[0008] Further preferably, the box further includes rails for guiding the solar cell array during deployment, the rails being located beneath the solar cell array. The rails provide guidance and structural support for the solar cell array during deployment. Furthermore, the rails limit the trajectory of the solar cell array during deployment and folding, ensuring that it deploys along a predetermined path. This ensures the precision and consistency of the solar cell array deployment, ensuring that the solar cell array accurately reaches the locked position when deployed and closely adheres to adjacent surfaces of the box, providing a protective barrier against the solar cell array deviating from its deployment path due to unexpected factors, such as external impact or vibration.

[0009] Further preferably, the case further includes a compression release mechanism and a limit locking mechanism. When the solar cell array is folded, the end of the solar cell array away from the rotating shaft engages with the compression release mechanism provided on the edge of the case for compression and locking. When the compression release mechanism is unlocked, the solar cell array unfolds along the slide rails. When the solar cell array is fully unfolded, the solar cell array engages with the limit locking mechanism provided on the contact surface of the case to lock and secure it. The compression release mechanism tightly compresses the solar cell array folded within the support arm, effectively preventing the solar cell array from accidentally unfolding or shaking due to external forces such as vibration and impact during launch. When the solar cell array unfolds, the slide rails provide precise guidance for the unfolding of the solar cell array, ensuring consistency and reliability of the unfolding process. When the support arm contacts the limit locking mechanism, the limit locking mechanism quickly locks the solar cell array to prevent displacement or shaking. The coordinated operation of the compression release mechanism and the limit locking mechanism ensures stable operation of the solar cell array and efficient solar energy collection.

[0010] Further preferably, the rotating shaft is provided at the vertex of the housing, the housing is a satellite-borne phased array relay terminal, the satellite-borne phased array relay terminal is provided with an antenna, the array plane of the solar cell array after unfolding is parallel to the array plane of the antenna, the satellite-borne phased array relay terminal is provided with two solar cell arrays, and the unfolding angle of the solar cell array when unfolded to contact the limit locking mechanism is 270°. Assembling the solar cell arrays at both ends of the satellite-borne phased array relay terminal allows the solar cell arrays to have a smaller envelope when folded, fully utilizing the structural configuration of the satellite-borne relay terminal and further improving the utilization rate of the solar cell arrays. The solar cell arrays are parallel to the antenna array plane, allowing the solar cell arrays to better receive sunlight after unfolding without being blocked by the antenna or other components, thereby improving the power generation efficiency of the solar cell arrays and providing more sufficient power for the satellite.

[0011] Further preferably, each solar cell array includes six support arms, and when the solar cell array is unfolded to contact the limit locking mechanism, the angle between two adjacent support arms is 45°, thereby improving the stability of the solar cell array structure.

[0012] Further preferably, the solar cell array between the two support arms is shaped like an isosceles triangle, with the waist of the isosceles triangle equal to the side length of the satellite-borne phased array relay terminal. Each solar cell array is composed of six connected isosceles triangles. This improves the structural stability of the solar cell array while maximizing the area facing the sun, generating more energy and enabling self-sufficient energy for the satellite-borne terminal. The isosceles triangle design further enhances the solar cell array's resistance to deformation.

[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 unfolding and folding 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 support arm is made of carbon fiber, and the solar cell array uses flexible solar cells, making the solar cell array structure 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 present invention has the following advantages:

[0017] (1) High integration with the satellite terminal structure, making full use of the structural characteristics of the satellite phased array relay terminal, assembling the solar cell array at both ends of the satellite 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 and saving space;

[0018] (2) By assembling the solar cell array of the present application, the onboard terminal can be self-sufficient in energy, and the largest solar-facing area can be achieved within a limited space. This maximizes the use of the solar energy resources on the satellite's surface, collects more energy, and reduces 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 degree of safety protection is provided to ensure that the solar cell array can work stably and collect solar energy efficiently. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The accompanying drawings provide further illustration of the embodiments and are incorporated into and constitute a part of this specification. The accompanying drawings illustrate the embodiments and, together with the description, serve to explain the principles of the invention. Other embodiments and many of the intended advantages of the embodiments will be readily apparent 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 folded from another perspective according to a specific embodiment of the present invention;

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

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

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

[0026] Figure 6 FIG. 1 is another schematic diagram of a satellite-borne relay terminal with a solar cell array installed on a satellite according to a specific embodiment of the present invention.

[0027] The meaning of the numbers in the figure are: 1-box, 2-solar cell array, 3-support arm, 4-slide rail, 5-pressing and releasing mechanism, 6-limiting and locking mechanism, 7-rotating shaft, 8-solar cell panel. DETAILED DESCRIPTION

[0028] The present application will be further described in detail below with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are merely for the purpose of explaining the relevant invention and are not intended to limit the invention. It should also be noted that, for ease of description, only portions relevant to the relevant invention are shown in the accompanying drawings.

[0029] In the description of the present invention, it should be noted that the terms "comprises," "includes," or any other variations thereof are intended to encompass non-exclusive inclusion, such that a process, method, article, or apparatus comprising a series of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus. The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features.

[0030] In the description of the present invention, it should be noted that, unless otherwise clearly stipulated and limited, the terms "installed", "provided with", "sleeved / connected", "connected", etc. should be understood in a broad sense. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection. It can be a mechanical connection or an electrical connection. It can be a direct connection or an indirect connection through an intermediate medium. It can be the internal connection of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0031] To facilitate understanding by those skilled in the art, the present invention is further described in detail below with reference to the accompanying drawings and embodiments.

[0032] Figure 1 The figure shows a schematic structural diagram of a solar cell array in a folded state according to a specific embodiment of the present application. Figure 2 FIG. 1 shows a schematic structural diagram of a solar cell array of a specific embodiment of the present application when folded from another perspective, as shown in FIG. Figure 1 and Figure 2 As shown, the solar cell array 2 is mounted in a box 1. A rotating shaft 7 is provided at the top of the box 1. One end of the solar cell array 2 is fixed to a plane of the box 1. The other end of the solar cell array 2 drives the solar cell array 2 to unfold around the rotating shaft 7 and is locked to the adjacent surface of the box 1 where the one end of the solar cell array 2 is located. The plane in which the solar cell array 2 is unfolded is parallel to or coplanar with one of the planes of the box 1.

[0033] In a specific embodiment, a rotating shaft 7 is provided at a diagonal position of a plane of the box body 1, and the solar cell array 2 is connected to the rotating shaft. Two solar cell arrays 2 are provided on the box body 1. When the two solar cell arrays 2 are folded, they are located on opposite sides of the box body 1, and the solar cell arrays are folded between a plurality of 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 compression and release mechanism 5. When folded, the solar cell array 2 is compressed by the compression and release mechanism 5.

[0034] Optionally, the plurality of support arms 3 are locked and compressed by a hot knife to release the mechanism 5 .

[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 1 where the solar cell array 2 is located when folded, and the other end of the slide rail 4 is located on an adjacent plane to the plane of the box 1, forming a 270° fan ring structure.

[0036] In this specific embodiment, two corresponding slide rails 4 below the two solar cell arrays 2 are located at diagonal positions of the housing 1. The compression and release mechanism 5 of one solar cell array 2 and the limit locking mechanism 6 of the other solar cell array 2 are located on the same plane of the housing 1. The end of the solar cell array 2 away from the rotating shaft 7 is compressed and locked with the compression and release mechanism 5 located at the edge of the housing 1.

[0037] In a specific embodiment, the support arm 3 is made of carbon fiber, and the solar cell array 2 uses flexible solar cells, making the solar cell array structure stable and lightweight.

[0038] Figure 3 FIG2 shows a schematic structural diagram of a solar cell array of a specific embodiment of the present application when it is unfolded. Figure 4 FIG. 1 shows a schematic structural diagram of a solar cell array of a specific embodiment of the present application when unfolded from another perspective, as shown in FIG. Figure 3 and Figure 4 As shown, the solar cell array 2 is connected to the slide rail 4 via a transmission mechanism. When an expansion command is received, the compression release mechanism 5 is unlocked by a hot knife, and the solar cell array 2 is expanded along the slide rail 4 via the rotating shaft 7, driving the support arms 3 to expand into an arc-shaped array surface. As the expansion proceeds, the angle between the support arms 3 continues to expand. When the support arms 3 contact the limit locking mechanism 6, the limit locking mechanism 6 locks the solar cell array 2. The compression release mechanism 5 and the limit locking mechanism 6 of the same solar cell array are located on two opposite surfaces of the box body 1.

[0039] In a specific embodiment, the housing 1 comprises six rectangular surfaces, and each solar cell array 2 can be expanded up to 270°. That is, when the solar cell array 2 is fully expanded, the limiting locking mechanism 5 provided on the contact surface of the housing 1 engages and locks the solar cell array 2 in place. The solar cell array 2 comprises six support arms. When the solar cell array 2 is expanded to contact the limiting locking mechanism 6, the angle between two adjacent support arms 3 is 45°. The solar cell array 2 between two support arms 3 forms an isosceles triangle, with the waist of the isosceles triangle equal to the side length of the housing 1. Each solar cell array is composed of six connected isosceles triangles. This maximizes the area facing the sun, enhancing the deformation resistance and stability of the solar cell array 2.

[0040] In a specific embodiment, the box 1 is a satellite-borne phased array relay terminal, which is equipped with a phased array antenna. When the solar cell array 2 is unfolded, the unfolded array surface of the solar cell array 2 is parallel to the phased array antenna, both facing the sun and not obstructed by the antenna. The solar cell array 2 is unfolded along the guide rail 4 with the rotating shaft 7 at the diagonal position of the satellite-borne phased array relay terminal as the fulcrum, forming an arc-shaped surround solar cell array 2 relying on both sides of the satellite-borne phased array relay terminal antenna surface, which serves as the basis for the design of the self-energy-supply solar cell of the satellite-borne terminal.

[0041] Figure 5 FIG. 1 shows a schematic diagram of a satellite-borne relay terminal with a solar cell array installed on a satellite according to a specific embodiment of the present application. The solar cell array 2 and the solar cell panel 8 of the satellite are both in a folded state. Figure 5 As shown, a box 1 with a solar cell array 2 is installed on the satellite. The solar cell array 2 is installed on the upper side of the box 1 away from the satellite and does not directly contact the satellite. In a specific embodiment, the box 1 is a satellite-borne phased array relay terminal. At this time, the satellite is in the launch state, and the solar cell array 2 is folded, which effectively reduces the space occupied by the solar cell array 2 in the launch state. The satellite-borne phased array relay terminal is installed on the solar side of the satellite, which not only meets the beam pointing requirements of the satellite-borne terminal antenna to the GEO relay satellite, but also effectively utilizes the solar energy of the satellite's solar side.

[0042] Figure 6 FIG. 1 shows a schematic diagram of a satellite-borne relay terminal with a solar cell array installed on a satellite according to a specific embodiment of the present application. The solar cell array 2 and the satellite solar cell panel 8 are both in an unfolded state. Figure 6 As shown, the box 1 is a satellite-borne phased array relay terminal, which is in the unfolded state after the satellite enters orbit. The two unfolded solar cell arrays 2 are parallel to the antenna array surface on the satellite-borne phased array relay terminal. The unfolded solar cell arrays 2, antennas and the satellite's solar panels 8 are all located on the sun-facing side. After unfolding, the solar cell arrays 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 cell array for a satellite-borne relay terminal, which effectively utilizes the structural characteristics of the satellite-borne phased array relay terminal so that the solar cell array 2 has a smaller envelope when folded, and the design of the solar cell array 2 when unfolded can obtain a maximum unfolding area under the conditions of the satellite environment. This not only solves the problems of traditional solar cells, but also further improves the performance of solar cells, effectively solving the on-orbit energy needs of the satellite-borne relay terminal. At the same time, the coordinated cooperation of the support arm 3, the slide rail 4, the clamping and releasing mechanism 5 and the said limit locking mechanism 6 enables the solar cell array of the present application to operate stably in the space environment, efficiently collect solar energy, and effectively prevent the solar cell array 2 from being accidentally damaged or shaken due to external forces such as vibration and impact.

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

Claims

1. A solar cell array for a satellite-borne relay terminal, characterized in that: The solar cell array is mounted on a box body, the box body is provided with a rotating shaft, one end of the solar cell array is fixed on a plane of the box body, the other end of the solar cell array drives the solar cell array to unfold with the rotating shaft as the center of a circle, and is locked to an adjacent surface of the box body plane where one end of the solar cell array is located, and the unfolded plane of the solar cell array is parallel to or coplanar with one of the planes of the box body; the box body also includes a slide rail for guiding the solar cell array to unfold, the slide rail is provided below the solar cell array; the box body also includes a pressing and releasing mechanism and a limiting locking mechanism, when the solar cell array is folded, the end of the solar cell array away from the rotating shaft cooperates with the pressing and releasing mechanism provided on the edge of the box body to press and lock, when the pressing and releasing mechanism is unlocked, the solar cell array unfolds along the slide rail, and when the solar cell array is fully unfolded, the solar cell array is locked and fixed with the limiting locking mechanism provided on the contact surface of the box body.

2. The solar cell array according to claim 1, wherein: It also includes multiple support arms supporting the solar cell array. When the solar cell array is folded, the solar cell 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 cell array is unfolded, the angle between the support arms continues to expand.

3. The solar cell array according to claim 2, characterized in that: The rotating shaft is set at the vertex of the box. The box is a satellite-borne phased array relay terminal. The satellite-borne phased array relay terminal is provided with an antenna. The array plane of the solar cell array after deployment is parallel to the array plane of the antenna. The satellite-borne phased array relay terminal is provided with two solar cell arrays. The deployment angle of the solar cell array when deployed to contact the limit locking mechanism is 270°.

4. The solar cell array according to claim 3, characterized in that: Each solar cell array includes six support arms. When the solar cell array is unfolded to contact the limit locking mechanism, the angle between two adjacent support arms is 45°.

5. The solar cell array according to claim 4, characterized in that: The solar cell array between the two support arms is in the shape of an isosceles triangle, the waist of the isosceles triangle is equal to the side length of the satellite-borne phased array relay terminal, and each solar cell array is connected by 6 isosceles triangle array surfaces.

6. The solar cell array according to claim 1, wherein: The slide rail is a 270° fan ring.

7. The solar cell array according to claim 2, characterized in that: The locking and unlocking of the compression release mechanism are achieved by a hot knife. The support arm is made of carbon fiber, and the solar cell array uses flexible solar cell sheets.

8. A satellite, provided with a solar cell array according to any one of claims 1 to 7.

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