Flexible solar panels for satellites and high-orbit satellites

Abstract

The present application discloses a flexible solar wing and a high-orbit satellite applied to a satellite, wherein the flexible solar wing includes: a flexible solar wing array, which is rectangular; a first support frame, which is at least two and respectively located on opposite sides of the flexible solar wing array, and the first support frame is fixedly connected to the flexible solar wing array; a central connecting piece, which is located at the center of the flexible solar wing array; a second support frame, which is four, and the first ends of the four second support frames are respectively connected to the four corners of the central connecting piece, and the second ends thereof extend to the four corners of the flexible solar wing array and are fixedly connected to the flexible solar wing array; the two second support frames on the same diagonal are arranged to be able to be folded and unfolded around the center of the central connecting piece. The present application solves the problems of the solar wing in the related art, such as large folding envelope, high space occupation, heavy weight, and weak structural stability.

Description

Technical Field

[0001] The present application relates to the field of solar wing technology, and in particular to a flexible solar wing applied to a satellite and a high-orbit satellite. Background Art

[0002] High-orbit satellites have information transmission distances of tens of thousands of kilometers, and require high-power energy as the basis for satellites to perform data transmission tasks. During operation, satellites mainly rely on solar panels to provide energy for spacecraft. Solar panels use batteries to convert light energy into electricity required by satellites in orbit. When the satellite is launched, the solar panels are in a retracted state through a compression and deployment device such as pyrotechnics or memory alloy breakers in order to reduce the satellite envelope; after entering orbit after the launch phase, the compression and deployment device unlocks the solar panels, allowing them to unfold and begin to generate electricity in a sun-oriented manner.

[0003] With the continuous development of aerospace technology, highly integrated technology and automation technology are gradually applied to the satellite field, thus realizing the rapid development of satellites towards miniaturization. Small satellites can quickly realize the entire process from design, manufacturing, launch, and in-orbit operation, and the R&D cost is relatively low. They have the advantages of low cost, fast iteration, rapid deployment, and timely response. They can provide services for different application scenarios in the form of constellation networking, and can be quickly and flexibly deployed in specific areas and special periods, making up for the lack of application capabilities and quantity of a single large satellite, and improving the flexibility and robustness of space infrastructure.

[0004] However, the miniaturized high-orbit small satellite can provide less space for the layout of the solar wing outside the cabin because of its reduced size. In the existing technology, the rigid and semi-rigid solar wing design generally adopts the traditional rectangular single-plate folding and unfolding method, which has the disadvantages of large folding envelope, high space occupation, heavy weight, and weak structural stability. In addition, during the satellite's in-orbit flight, if the folding area of ​​the solar wing is too large, it will be affected by more vibrations and overloads, which seriously affects the stability and safety of the satellite. For high-orbit small satellites, the area of ​​the solar wing installation structure is small, and the folding method of the traditional solar wing is limited by the satellite envelope and cannot be effectively stored. Summary of the invention

[0005] The main purpose of the present application is to provide a flexible solar wing for use in satellites, so as to solve the problems of the solar wing in the related art such as large folding envelope, high space occupancy, heavy weight and weak structural stability.

[0006] In order to achieve the above-mentioned object, the present application provides a flexible solar wing applied to a satellite, the flexible solar wing comprising:

[0007] A flexible solar wing array, wherein the flexible solar wing array is rectangular;

[0008] At least two first support frames are provided and are respectively located on two opposite sides of the flexible solar wing array surface, and the first support frames are fixedly connected to the flexible solar wing array surface;

[0009] A central connecting piece, arranged at the center of the flexible solar wing array;

[0010] The second support frames are provided in at least four numbers, the first ends of the four second support frames are respectively connected to the four corners of the central connecting member, and the second ends thereof extend to the four corners of the flexible solar wing array and are fixedly connected to the flexible solar wing array;

[0011] The two second support frames on the same diagonal line are configured to be foldable and unfoldable around the center of the central connecting piece, so that the flexible solar wing array can be folded from a rectangle to a triangle, and unfolded from a triangle to a rectangle.

[0012] Furthermore, the central connecting member is made of elastic material, and after the flexible solar wing array is folded, the central connecting member generates elastic deformation to provide driving force when the flexible solar wing array is unfolded.

[0013] Furthermore, the central connecting member is configured to be cross-shaped, and the four ends of the central connecting member are respectively fixedly connected to the first ends of the four second supporting frames.

[0014] Furthermore, the second end of the second supporting frame is fixedly connected to the end of the first supporting frame.

[0015] Furthermore, the flexible solar wing is provided in plurality, the plurality of the flexible solar wings are distributed in a straight line direction, and adjacent first support frames in the plurality of the flexible solar wings are connected by a first hinge structure so that the adjacent flexible solar wings can be folded and unfolded.

[0016] Furthermore, the first hinge structure includes a first connecting part, a second connecting part and a first elastic member, the first connecting part is fixedly connected to the first supporting frame on one side, the second connecting part is fixedly connected to the first supporting frame on the other side, the first connecting part and the second connecting part are hinged, and both ends of the first elastic member are respectively fixedly connected to the first connecting part and the second connecting part, for providing driving force for the expansion of the first connecting part and the second connecting part.

[0017] Furthermore, the first hinge structure also includes a first limiting portion, and the first limiting portion is used to limit the unfolding rotation angle of the first connecting portion and the second connecting portion.

[0018] According to another aspect of the present application, a high-orbit satellite is provided, comprising a satellite body, a folding and unfolding connecting member, a compression and unfolding device, and the above-mentioned flexible solar wing; wherein:

[0019] The first end of the folding and unfolding connecting piece is connected to the star body, and the second end is connected to the flexible solar wing. After being folded, the flexible solar wing is stacked on the star body through the folding and unfolding connecting piece;

[0020] The compression and expansion device is arranged on the star body, and is used to compress and fix the folded flexible solar wing and release the flexible solar wing when expanding.

[0021] Furthermore, the folding and unfolding connecting member includes a two-fold rigid rod and an unfolding bracket, the first end of the two-fold rigid rod is fixedly connected to the star body, the second end is fixedly connected to the first end of the unfolding bracket, the second end of the unfolding bracket is fixedly connected to the first support frame on one side of the flexible solar wing, and the first end and the second end of the unfolding bracket are hinged.

[0022] Furthermore, a second limit portion is provided in the deployment bracket, and the second limit portion is used to limit the deployment angle between the first end and the second end of the deployment bracket;

[0023] A second elastic member is connected between the first end and the second end of the deployment bracket, and the second elastic member is used to provide a driving force for the deployment of the first end and the second end of the deployment bracket;

[0024] The two-fold rigid rod includes a base, a first rod body and a second rod body, the base is fixedly connected to the star body, the two ends of the first rod body are hinged to the base and the second rod body respectively, the unfolding bracket is arranged on the second rod body, and a third elastic member is arranged between the base and the first rod body and between the first rod body and the second rod body.

[0025] In the embodiment of the present application, by setting a flexible solar wing array, the flexible solar wing array is rectangular; at least two first support frames are provided and are respectively located on opposite sides of the flexible solar wing array, and the first support frames are fixedly connected to the flexible solar wing array; a central connecting member is provided at the center of the flexible solar wing array; at least four second support frames are provided, and the first ends of the four second support frames are respectively connected to the four corners of the central connecting member, and the second ends thereof extend to the four corners of the flexible solar wing array and are fixedly connected to the flexible solar wing array; the two second support frames on the same diagonal are arranged to be able to be folded and unfolded around the center of the central connecting member, so that the flexible solar wing array can be folded from a rectangle to a triangle, and unfolded from a triangle to a rectangle, on the one hand, the four second support frames can be used to fold the rectangular flexible solar wing array into a triangle, so that the solar wing array has a small envelope after folding, a large expansion ratio, and a folding area of ​​only 25% of the folding area of ​​a traditional rectangular single plate, which greatly reduces the installation area required for folding the solar wing, and the compact folding method effectively improves the mechanical resistance of the solar wing during the satellite launch to the orbit entry stage, thereby ensuring the stability and reliability of the solar wing;

[0026] On the other hand, due to the use of flexible solar wing arrays, their weight is lighter than that of rigid or semi-rigid solar wing arrays. When applied to satellites, the lighter weight makes the satellite have a smaller moment of inertia when deployed in orbit, which can improve the maneuverability of the entire satellite's attitude adjustment;

[0027] On the other hand, since the folded solar wing array has a triangular outline, when it is stacked on the square satellite cabin board, more installation space can be left on the satellite cabin board for the layout of other extravehicular units, expanding the spatial position of the entire satellite layout and providing more optimization space for the rationality of the mass distribution of the entire satellite layout. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The drawings constituting a part of this application are used to provide a further understanding of this application, so that other features, purposes and advantages of this application become more obvious. The schematic embodiment drawings and their descriptions of this application are used to explain this application and do not constitute an improper limitation on this application. In the drawings:

[0029] Figure 1 is a schematic diagram of the axonometric structure of the back side of the flexible solar wing after unfolding according to an embodiment of the present application;

[0030] Figure 2 is a schematic diagram of the axonometric structure of the front side of the flexible solar wing after it is unfolded according to an embodiment of the present application;

[0031] Figure 3 is a schematic diagram of the axonometric structure of the flexible solar wing after folding according to an embodiment of the present application;

[0032] Figure 4 is another isometric structural schematic diagram of the flexible solar wing after folding according to an embodiment of the present application;

[0033] Among them, 1 is a flexible solar wing, 2 is a central connecting part, 3 is a first hinge structure, 4 is a first supporting frame, 5 is a second supporting frame, 6 is a flexible solar wing array, 7 is a folding and unfolding connecting part, 70 is an unfolding bracket, 71 is a two-fold rigid rod, 710 is a first rod body, 711 is a second rod body, 712 is a base, 8 is a star body, and 9 is a compression and unfolding device. DETAILED DESCRIPTION

[0034] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present application.

[0035] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so as to describe the embodiments of the present application described herein.

[0036] In this application, the terms "upper", "lower", "inner", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the drawings. These terms are mainly used to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to have a specific orientation, or to be constructed and operated in a specific orientation.

[0037] In addition, some of the above terms may be used to express other meanings in addition to indicating orientation or positional relationship. For example, the term "on" may also be used to express a certain dependency or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in this application can be understood according to specific circumstances.

[0038] In addition, the terms "disposed", "provided with", "connected", "fixed" and the like should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection, or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be an internal connection between two devices, elements or components. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to the specific circumstances.

[0039] In addition, the term "plurality" shall mean two or more.

[0040] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0041] To solve relevant technical problems, such as Figure 1 As shown, an embodiment of the present application provides a flexible solar wing 1 applied to a satellite, and the flexible solar wing 1 includes:

[0042] A flexible solar wing array surface 6, which is rectangular;

[0043] At least two first support frames 4 are provided and are respectively located on two opposite sides of the flexible solar wing array surface 6, and the first support frames 4 are fixedly connected to the flexible solar wing array surface 6;

[0044] The central connecting member 2 is arranged at the center of the flexible solar wing array 6;

[0045] The second support frames 5 are provided in at least four numbers, the first ends of the four second support frames 5 are respectively connected to the four corners of the central connecting member 2, and the second ends thereof extend to the four corners of the flexible solar wing array 6 and are fixedly connected to the flexible solar wing array 6;

[0046] The two second support frames 5 on the same diagonal line are arranged to be foldable and unfoldable around the center of the central connecting member 2, so that the flexible solar wing array 6 can be folded from a rectangle to a triangle, and unfolded from a triangle to a rectangle.

[0047] In this embodiment, the flexible solar wing 1 mainly includes a flexible solar wing array 6, a first support frame 4, a central connector 2 and a second support frame 5. The flexible solar wing array 6 is made of a flexible material so that it has the ability to fold. In order to achieve a higher energy conversion rate, the flexible solar wing array 6 in this embodiment is rectangular after unfolding. Since the flexible solar wing array 6 is a flexible structure, it needs to be properly supported to maintain stability after unfolding. In this embodiment, the flexible solar wing array 6 is supported by the first support frame 4 and the second support frame 5. Specifically, the first support frame 4 is at least two and is fixedly connected to the opposite sides of the flexible solar wing array 6, and the second support frame 5 is arranged on the diagonal of the flexible solar wing array 6. The first support frame 4 and the second support frame 5 form a support structure similar to an hourglass cross-section as a whole, so that the flexible solar wing array 6 can be supported after unfolding.

[0048] In order to reduce the area of ​​the rectangular flexible solar wing array 6 after folding, reduce the folding envelope and improve the storage package ratio. Figure 1 , Figure 3 and Figure 4 As shown, in this embodiment, the rectangular flexible solar wing array 6 is folded into a triangle, so the flexible solar wing array 6 needs to be folded once along the diagonal, and then folded twice along the center line to finally form a triangle. It can be understood that the secondary folding along the center line is essentially a folding process along another diagonal of the flexible solar wing array 6. To this end, in this embodiment, the second support frames 5 arranged on the two diagonals are set to be at least four split parts, wherein two second support frames 5 are located on one diagonal, and another second support frame 5 is located on the other diagonal. The rectangular solar wing array is roughly divided into four triangles of equal area by the four second support frames 5. After folding, the area occupied by the flexible solar wing array 6 is roughly the area corresponding to one triangle.

[0049] The two folding processes of the flexible solar wing array 6 can be understood as the folding process around its center in two diagonal directions. Therefore, in order to enable the flexible solar wing array 6 to be folded around the center, a central connector 2 is further arranged at the center of the flexible solar wing array 6 in this embodiment. The four second support frames 5 are connected at the four corners of the central connector 2. In the folding process, the four second support frames 5 are all folded around the center point of the central connector 2. In one embodiment, when only the folding and unfolding basis of the four second support frames provided by the central connector 2 is considered, the central connector 2 can be a cross hinge, which is formed by two hinges with different rotation directions and has a preset rotation center. When the rotation center coincides with the center of the flexible solar wing array 6, the folding and unfolding process of the flexible solar wing array 6 is a rotation process around its center. In another embodiment, the central connector 2 can also be a flexible connector that can produce elastic deformation, and its elastic deformation capacity can meet the folding process of the four second support frames 5.

[0050] On the one hand, the present embodiment achieves the goal of using four second support frames 5 to fold the rectangular flexible solar wing array 6 into a triangle, so that the solar wing array has a small envelope after folding, a large expansion-contraction ratio, and a folded area of ​​only 25% of the folded area of ​​a traditional rectangular single plate, which greatly reduces the installation area required for folding the solar wing, and the compact folding method effectively improves the mechanical resistance of the solar wing during the satellite launch to orbit entry stage, thereby ensuring the stability and reliability of the solar wing;

[0051] On the other hand, since the flexible solar wing array 6 is adopted, its weight is lighter than that of a rigid or semi-rigid solar wing array. When applied to a satellite, the lighter weight makes the satellite have a smaller moment of inertia when deployed in orbit, which can improve the maneuverability of the entire satellite's attitude adjustment.

[0052] On the other hand, since the folded solar wing array has a triangular outline, when it is stacked on the square satellite cabin board, more installation space can be left on the satellite cabin board for the layout of other extravehicular units, expanding the spatial position of the entire satellite layout and providing more optimization space for the rationality of the mass distribution of the entire satellite layout.

[0053] Moreover, the flexible solar wing array 6 in this embodiment can also be well applied to the existing solar wings with aluminum honeycomb as the substrate, and also has the advantages of higher fundamental frequency and larger aspect ratio.

[0054] Since the unfolding of the flexible solar wing array 6 requires the elastic force of the hinge, in one embodiment of the central connecting member 2, the central connecting member 2 is made of an elastic material. After the flexible solar wing array 6 is folded, the central connecting member 2 produces elastic deformation to provide driving force when the flexible solar wing array 6 is unfolded.

[0055] Specifically, it should be noted that the central connecting member 2 can be a square spring sheet, which can be folded in the same way as the flexible solar wing array 6, that is, the square spring sheet can be folded into a triangle, thereby satisfying the folding process of the flexible solar wing array 6. When the central connecting member 2 is compressed and folded, elastic deformation is generated and elastic potential energy is obtained. When the flexible solar wing array 6 is released, the elastic potential energy of the central connecting member 2 acts on the flexible solar wing array 6, specifically on the second supporting frame 5, driving the flexible solar wing array 6 to unfold from a triangle to a rectangle.

[0056] Since the square central connector 2 has a large stress when deformed, in order to reduce the stress, the central connector 2 in this embodiment is set to a cross shape, and the four ends of the central connector 2 are respectively fixedly connected to the first ends of the four second support frames 5. The specific size and material of the central connector 2 can be determined according to the driving force required for the flexible solar wing array 6 to unfold. This embodiment does not limit it here, and it can be designed according to actual needs.

[0057] Since the first support frame 4 and the second support frame 5 are mainly used to support the flexible solar wing array 6, on this basis, in order to further improve the supporting capacity, such as Figure 1 As shown, both ends of the first support frame 4 in this embodiment extend to positions close to the top corners of the flexible solar wing array 6 , and the second end of the second support frame 5 is fixedly connected to the end of the first support frame 4 .

[0058] In this embodiment, the first support frame 4 is arranged only on two sides of the flexible solar wing array 6, and no additional first support frame 4 is arranged on the other two sides, thereby providing stable support for the flexible solar wing array 6 and further reducing the weight of the entire solar wing.

[0059] In one embodiment, Figure 1 and Figure 2 As shown, the flexible solar wing 1 is provided in plurality, and the plurality of flexible solar wings 1 are distributed in a straight line direction. When the flexible solar wing 1 is only provided with the first support frame 4 on both sides, in order to facilitate the connection of the connected flexible solar wings 1, in this embodiment, the adjacent flexible solar wings 1 are provided with the first support frame 4 on one side adjacent to each other, and the adjacent first support frames 4 in the plurality of flexible solar wings 1 are connected by the first hinge structure 3, so that the adjacent flexible solar wings 1 can be folded and unfolded.

[0060] Specifically, it should be noted that after a single flexible solar wing 1 is folded into a triangle, it can be folded together with adjacent flexible solar wings 1 through the first hinge structure 3 to form an upper and lower stacked distribution. The first hinge structure 3 is used for folding and unfolding adjacent flexible solar wings 1, and it can adopt the hinge structure in the solar wing in the form of a traditional aluminum honeycomb substrate, and this embodiment does not limit its specific structure.

[0061] In one embodiment, the folding process is described by taking the flexible solar wing 1 having three as an example:

[0062] When the three flexible solar wings 1 are fully unfolded and then folded, the far-end flexible solar wing 1 (the end away from the satellite) is folded first to change it from a rectangle to a triangle. Then the triangular flexible solar wing 1 will be folded together with the middle rectangular flexible solar wing 1. After the middle flexible solar wing 1 is folded into a triangle, the triangular flexible solar wing 1 at the far end is folded onto the middle flexible solar wing 1 through the first hinge structure 3. Then the far-end and middle flexible solar wings 1 will be folded together with the near-end flexible solar wing 1. After the near-end flexible solar wing 1 is folded into a triangle, the far-end and middle flexible solar wings 1 are folded as a whole onto the triangular flexible solar wing 1 at the near end through the first hinge structure 3. The unfolding process is similar, and this embodiment will not be described in detail here.

[0063] In one embodiment of the first hinge structure 3, the first hinge structure 3 includes a first connecting part, a second connecting part and a first elastic member, the first connecting part is fixedly connected to the first support frame 4 on one side, the second connecting part is fixedly connected to the first support frame 4 on the other side, the first connecting part and the second connecting part are hinged, and both ends of the first elastic member are fixedly connected to the first connecting part and the second connecting part, respectively, for providing driving force for the expansion of the first connecting part and the second connecting part.

[0064] In this embodiment, the first connection part and the second connection part can be hinged by a rotating shaft, so that the first connection part and the second connection part can rotate relative to each other to realize the folding and unfolding of adjacent flexible solar wings 1. When adjacent flexible solar wings 1 are folded, the first elastic member generates elastic deformation, thereby providing corresponding unfolding force when unfolding. The first elastic member in this embodiment can be a spring, a spring sheet or a torsion spring, etc. Since the first connection part and the second connection part are hinged by a rotating shaft, in order to improve the stability of the structure, the first elastic member is preferably a torsion spring sleeved on the rotating shaft, and the two legs of the torsion spring are respectively fixedly connected to the first connection part and the second connection part.

[0065] After the multiple flexible solar wings 1 are fully unfolded, the flexible solar wings 1 should be in the same plane. To prevent the flexible solar wings 1 from over-expanding, it is necessary to limit the maximum unfolding rotation angle of the first connection part and the second connection part. Therefore, the first hinge structure 3 in this embodiment also includes a first limiter, which is used to limit the unfolding rotation angle of the first connection part and the second connection part.

[0066] In one embodiment, the first connection part and the second connection part are hinged on a substrate through a rotating shaft, and the two sides of the substrate extend toward the two sides of the rotating shaft. When the first connection part and the second connection part are rotated and expanded to a set angle, they abut against the part of the substrate extending from the rotating shaft, and thus cannot rotate further. In this embodiment, the part of the rotating shaft extending from the substrate serves as the first limiting part. In another embodiment, the rotating shaft is optionally fixedly connected to the first connection part and rotationally connected to the second connection part. The area where the rotating shaft is installed in the second connection part has an arc-shaped limiting groove, and the rotating shaft has a limiting protrusion slidably connected to the limiting groove. The maximum rotation position of the limiting protrusion is limited by the closed structure at both ends of the limiting groove, thereby limiting the maximum rotation angle of the rotating shaft, and then limiting the maximum expansion angle of the first connection part and the second connection part.

[0067] According to another aspect of the present application, Figures 1 to 4 As shown, a high-orbit satellite is provided, comprising a satellite body 8, a folding and unfolding connecting member 7, a compression and unfolding device 9 and the above-mentioned flexible solar wing 1; wherein,

[0068] The first end of the folding and unfolding connecting member 7 is connected to the star body 8, and the second end is connected to the flexible solar wing 1. After being folded, the flexible solar wing 1 is stacked on the star body 8 through the folding and unfolding connecting member 7;

[0069] The compression and unfolding device 9 is arranged on the star body 8, and is used to compress and fix the folded flexible solar wing 1 and release the flexible solar wing 1 when unfolding.

[0070] In this embodiment, both sides of the star body 8 are provided with folding and unfolding connecting members 7 (only one side is shown in the figure, and the other side is a symmetrical structure), a compression and unfolding device 9 and a flexible solar wing 1, and the flexible solar wing 1 on one side is arranged as a plurality of mutually hinged ones. The plurality of flexible solar wings 1 on one side are folded into a triangle and then stacked on one side of the star body 8 (such as Figure 3 and Figure 4 As shown), and is pressed against the deck of the star body 8 by the pressing and unfolding device 9. When it needs to be unfolded, the star body 8 sends a solar wing unfolding instruction, and the pressing and unfolding device 9 performs the corresponding action to contact the locking state between the flexible solar wing 1 and the deck. At the same time, the spring in the pressing and unfolding device 9 will provide a part of the solar wing unfolding force, pushing the folding and unfolding connecting member 7 to complete the unfolding action, so that the folded flexible solar wing 1 rotates 90° as a whole, and the first elastic member in the first hinge structure 3 between the flexible solar wings 1 completes the unfolding action, and each flexible solar wing 1 completes the unfolding action through the elastic force of the central connecting member 2, unfolding the flexible solar wing array 6 from a folded triangular state to a rectangular state. After being unfolded into place, it is locked to the set unfolding state through the corresponding limit structure (as shown Figure 1 and Figure 2 shown).

[0071] In this embodiment, the compression and deployment device 9 can adopt the pyrotechnics or the structure with memory alloy breakers applied to the traditional satellite folding solar wing in the related technology. Taking the pyrotechnics as an example, in the folded storage state, the compression part of the compression and deployment device 9 can be compressed on each flexible solar wing 1 and locked by the compression rod. When unfolding, the pyrotechnic cutter in the pyrotechnic is used to cut off the compression rod to release each flexible solar wing 1, and each flexible solar wing 1 will be unfolded under the corresponding elastic force. Since the flexible solar wing 1 in this embodiment is a triangle after folding, in order to make the compression stable, three compression and deployment devices 9 can be arranged on the satellite 8, corresponding to the three vertices of the triangular flexible solar wing 1.

[0072] On the one hand, the present embodiment achieves the goal of using four second support frames 5 to fold the rectangular flexible solar wing array 6 into a triangle, so that the solar wing array has a small envelope after folding, a large expansion-contraction ratio, and a folded area of ​​only 25% of the folded area of ​​a traditional rectangular single plate, which greatly reduces the installation area required for folding the solar wing, and the compact folding method effectively improves the mechanical resistance of the solar wing during the satellite launch to orbit entry stage, thereby ensuring the stability and reliability of the solar wing;

[0073] On the other hand, since the flexible solar wing array 6 is adopted, its weight is lighter than that of a rigid or semi-rigid solar wing array. When applied to a satellite, the lighter weight makes the satellite have a smaller moment of inertia when deployed in orbit, which can improve the maneuverability of the entire satellite's attitude adjustment.

[0074] On the other hand, since the folded solar wing array has a triangular outline, when it is stacked on the square satellite cabin board, more installation space can be left on the satellite cabin board for the layout of other extravehicular units, expanding the spatial position of the entire satellite layout and providing more optimization space for the rationality of the mass distribution of the entire satellite layout.

[0075] In order to enable the folded flexible solar wing 1 to be folded to the side of the star body 8 as a whole, Figure 3 As shown, the folding and unfolding connecting member 7 in this embodiment includes a two-fold rigid rod 71 and an unfolding bracket 70. The first end of the two-fold rigid rod 71 is fixedly connected to the star body 8, and the second end is fixedly connected to the first end of the unfolding bracket 70. The second end of the unfolding bracket 70 is fixedly connected to the first supporting frame 4 on one side of the flexible solar wing 1, and the first end and the second end of the unfolding bracket 70 are hinged.

[0076] In this embodiment, the folded flexible solar wing 1 is rotated 90° by unfolding the bracket 70 , and then folded to one side of the star body 8 by the two-fold rigid rod 71 .

[0077] Since the folded flexible solar wing 1 needs to be rotated 90° by the unfolding bracket 70, in order to control the maximum unfolding angle, a second limiter is provided in the unfolding bracket 70 in this embodiment, and the second limiter is used to limit the unfolding angle between the first end and the second end of the unfolding bracket 70;

[0078] A second elastic member is connected between the first end and the second end of the deployment bracket 70, and the second elastic member is used to provide a driving force for the deployment of the first end and the second end of the deployment bracket 70. A third elastic member is connected between the two sections of the rod body of the double-folded rigid rod 71, and the third elastic member is used to provide a driving force for the deployment of the two sections of the rod body.

[0079] Specifically, it should be noted that the structure of the second limit portion in this embodiment may be similar to the structure of the first limit portion in the above embodiment. The first end and the second end of the deployment bracket 70 are also hinged by a corresponding rotating shaft, and corresponding limit plates may be arranged at specific positions to limit the maximum rotation angle of the two ends of the deployment bracket 70. In order to enable the deployment bracket 70 to provide the deployment force of the flexible solar wing 1, a second elastic member is arranged between the first end and the second end of the deployment bracket 70 in this embodiment. The second elastic member may be a torsion spring sleeved on the rotating shaft, and the two legs are respectively against the two ends of the deployment bracket 70.

[0080] In one embodiment, Figure 2 and Figure 3 As shown, the two-fold rigid rod 71 includes a base 712, a first rod body 710 and a second rod body 711. The base 712 is fixedly connected to the star body 8. The two ends of the first rod body 710 are hinged to the base 712 and the second rod body 711 respectively. The unfolding bracket 70 is arranged on the second rod body 711.

[0081] When the flexible solar wing 1 is folded by the unfolding bracket 70, the second rod 711 rotates around the hinge point between it and the first rod 710 and folds onto the first rod 710, and then the first rod 710 rotates around the hinge point between it and the base 712 and folds onto the star 8. After the folding is completed, the first rod 710 and the second rod 711 are close to the deck of the star 8, and the flexible solar wing 1 is folded on the second rod 711. In order to enable the two-fold rigid rod 71 to provide the corresponding unfolding force, a third elastic member is arranged between the two sections of the two-fold rigid rod 71. A third elastic member is arranged between the base 712 and the first rod 710 and between the first rod 710 and the second rod 711. The third elastic member can also be a torsion spring arranged on the corresponding hinge axis.

[0082] The above description is only the preferred embodiment of the present application and is not intended to limit the present application. For those skilled in the art, the present application may have various modifications and variations. Within the spirit and principle of the present application, any modification, equivalent replacement, improvement, etc. made shall be included in the protection scope of the present application.

Claims

1. A flexible solar wing for use in a satellite, characterized in that: include: A flexible solar wing array, wherein the flexible solar wing array is rectangular; At least two first support frames are provided and are respectively located on two opposite sides of the flexible solar wing array surface, and the first support frames are fixedly connected to the flexible solar wing array surface; A central connecting piece, arranged at the center of the flexible solar wing array; The second support frames are provided in at least four numbers, the first ends of the four second support frames are respectively connected to the four corners of the central connecting member, and the second ends thereof extend to the four corners of the flexible solar wing array and are fixedly connected to the flexible solar wing array; The two second support frames on the same diagonal line are configured to be foldable and unfoldable around the center of the central connecting piece, so that the flexible solar wing array can be folded from a rectangle to a triangle, and unfolded from a triangle to a rectangle.

2. The flexible solar wing according to claim 1, characterized in that: The central connecting member is made of elastic material. After the flexible solar wing array is folded, the central connecting member generates elastic deformation to provide driving force when the flexible solar wing array is unfolded.

3. The flexible solar wing according to claim 2, characterized in that: The central connecting member is configured in a cross shape, and the four ends of the central connecting member are fixedly connected to the first ends of the four second supporting frames respectively.

4. The flexible solar wing according to any one of claims 1 to 3, characterized in that: The second end of the second supporting frame is fixedly connected to the end of the first supporting frame.

5. The flexible solar wing according to claim 1, characterized in that: The flexible solar wing is arranged in plurality, and the plurality of the flexible solar wings are distributed in a straight line direction, and the adjacent first support frames in the plurality of the flexible solar wings are connected by a first hinge structure so that the adjacent flexible solar wings can be folded and unfolded.

6. The flexible solar wing according to claim 5, characterized in that: The first hinge structure includes a first connecting part, a second connecting part and a first elastic member, the first connecting part is fixedly connected to the first supporting frame on one side, the second connecting part is fixedly connected to the first supporting frame on the other side, the first connecting part and the second connecting part are hinged, and the two ends of the first elastic member are respectively fixedly connected to the first connecting part and the second connecting part, so as to provide driving force for the expansion of the first connecting part and the second connecting part.

7. The flexible solar wing according to claim 6, characterized in that: The first hinge structure further includes a first limiting portion, and the first limiting portion is used to limit the unfolding rotation angle of the first connecting portion and the second connecting portion.

8. A high-orbit satellite, characterized in that: It comprises a star body, a folding and unfolding connecting piece, a compression and unfolding device and a flexible solar wing as claimed in any one of claims 1 to 7; wherein, The first end of the folding and unfolding connecting piece is connected to the star body, and the second end is connected to the flexible solar wing. After being folded, the flexible solar wing is stacked on the star body through the folding and unfolding connecting piece; The compression and expansion device is arranged on the star body, and is used to compress and fix the folded flexible solar wing and release the flexible solar wing when expanding.

9. The high-orbit satellite according to claim 8, characterized in that: The folding and unfolding connecting member includes a two-fold rigid rod and an unfolding bracket, the first end of the two-fold rigid rod is fixedly connected to the star body, the second end is fixedly connected to the first end of the unfolding bracket, the second end of the unfolding bracket is fixedly connected to the first support frame on one side of the flexible solar wing, and the first end and the second end of the unfolding bracket are hinged.

10. The high-orbit satellite according to claim 9, characterized in that: A second limit portion is provided in the deployment bracket, and the second limit portion is used to limit the deployment angle between the first end and the second end of the deployment bracket; A second elastic member is connected between the first end and the second end of the deployment bracket, and the second elastic member is used to provide a driving force for the deployment of the first end and the second end of the deployment bracket; The two-fold rigid rod includes a base, a first rod body and a second rod body, the base is fixedly connected to the star body, the two ends of the first rod body are hinged to the base and the second rod body respectively, the unfolding bracket is arranged on the second rod body, and a third elastic member is arranged between the base and the first rod body and between the first rod body and the second rod body.

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