Collapsible wrap-around solar wing configuration
By using a foldable, rolled solar array configuration and optimizing the solar array's deployment method through a folding and unfolding mechanism, the problems of reduced fundamental frequency and space occupation caused by increased solar array area are solved, achieving increased width, reduced length, and increased fundamental frequency.
Patent Information
- Application Number
- CN202511411542.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-09-29
- Publication Date
- 2025-11-21
AI Technical Summary
The increased deployment area of existing solar panels leads to a decrease in the fundamental frequency, affecting satellite attitude control. Furthermore, existing support methods suffer from space occupation or mechanical limitations.
It adopts a foldable, rolled solar array configuration. The second rolled solar array component is flipped outside the entire satellite envelope by a folding and unfolding mechanism, and then unfolded and laid out in a second direction by an extension mechanism. The width and length of the solar array are optimized by combining fixed and movable folding and unfolding components.
It effectively increases the width of the solar array in its deployed state, reduces its length, increases the baseband frequency, and reduces the winding diameter and the stacking height of flat-panel satellites, thus optimizing space utilization.
Smart Images
Figure CN120986703A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of solar panel technology, and more specifically, to a foldable, rollable solar panel configuration. Background Technology
[0002] As spacecraft become larger and their missions more complex, their power requirements for energy systems are increasing. A powerful energy system is the most important foundation for a spacecraft to perform its functions, which places higher demands on the deployment area of solar arrays. However, as the deployment area of solar arrays increases, their deployed fundamental frequency decreases accordingly, which has an adverse effect on satellite attitude control.
[0003] Solar array support methods are generally divided into two types: side support and rear support. For example, some space stations use side support for their flexible solar arrays. The advantage of this method is that the solar array deployment mechanism is subjected to axial pressure, and the deployment mechanism and the solar array do not interfere with each other during deployment. The disadvantage is that the side deployment mechanism will occupy space in the width direction of the solar array module.
[0004] Some solar arrays also use a back support scheme based on a scissor mechanism. The advantage is that the deployment mechanism does not affect the width of the flexible solar array, but the disadvantage is that the deployment mechanism is subjected to an eccentric force, which limits the tension of the solar array surface.
[0005] In summary, there is an urgent need for a solar array configuration that can effectively increase the solar array's deployed area while maximizing its deployed state fundamental frequency. Summary of the Invention
[0006] In view of the shortcomings of the prior art, the purpose of this invention is to provide a foldable, rollable solar array configuration.
[0007] According to the present invention, a foldable, rolled solar wing configuration includes: a first rolled solar wing component, a folding and unfolding mechanism, a plurality of second rolled solar wing components, and an extension mechanism; At least one second winding solar wing component is provided at both ends of the first winding solar wing component in the first direction. The end of the second winding solar wing component is connected to the first winding solar wing component through a folding and unfolding mechanism. The folding and unfolding mechanism is used to flip the second winding solar wing component. When in the deployed state, the second wound solar panel component rotates to be collinear with the first wound solar panel component in the first direction; The extension mechanism is provided on the first and / or the second wound solar wing component, the extension mechanism being used to unfold and lay the first and second wound solar wing components in a second direction.
[0008] Preferably, the extension mechanism on each of the second wound solar wing components connected to the first wound solar wing component simultaneously unfolds and lays the first wound solar wing component in the second direction.
[0009] Preferably, when the spiral solar array configuration is in the retracted state, both the second spiral solar array component and the first spiral solar array component are located on the surface of the satellite's upper top plate and are arranged parallel to the surface of the satellite's upper top plate.
[0010] Preferably, the first wound solar panel component includes a first fixed frame and a first wound battery blanket assembly connected to the first fixed frame, and the second wound solar panel component includes a second fixed frame and a second wound battery blanket assembly connected to the second fixed frame. The second fixed frame is connected to one end of the first fixed frame through the folding and unfolding mechanism, and the second fixed frames of two adjacent second winding solar wing components located on the same side as the first winding solar wing component are connected through the folding and unfolding mechanism.
[0011] Preferably, the first wound solar blanket assembly includes a first flexible solar cell blanket and a first winding cylinder, and the second wound solar blanket assembly includes a second flexible solar cell blanket and a second winding cylinder; One end of the first flexible solar cell blanket is fixedly connected to the first winding cylinder, and the other end is fixedly connected to the first fixed frame; one end of the second flexible solar cell blanket is fixedly connected to the second winding cylinder, and the other end is fixedly connected to the second fixed frame.
[0012] Preferably, the extension mechanism is disposed on the second fixed frame and is fixedly connected to the second winding cylinder.
[0013] Preferably, the folding and unfolding mechanism includes a fixed folding and unfolding component and a movable folding and unfolding component; The first fixed frame is connected to the second fixed frame through the fixed folding and unfolding component, and the second fixed frames of two adjacent second winding solar panel components are connected through the fixed folding and unfolding component; The extension mechanism on the second fixed frame, which is connected to the first fixed frame, is also fixedly connected to the first winding cylinder via a movable folding and unfolding component.
[0014] Preferably, the second winding cylinder is also connected to an extension mechanism on an adjacent second fixed frame via the movable folding and unfolding component.
[0015] Preferably, the first wound solar array component and each of the second wound solar array components are provided with a clamping and releasing mechanism, and the first fixed frame and the second fixed frame are both fixedly connected to the satellite surface through the clamping and releasing mechanism; The extension mechanism includes any one of the following: an extension mechanism based on an elastic extension rod, an extension mechanism based on a scissor fork, or an extension mechanism based on a telescopic sleeve.
[0016] Preferably, the extension mechanism is located on the side of the second wound battery blanket assembly near the first wound solar panel component.
[0017] Compared with the prior art, the present invention has the following beneficial effects: 1. By setting a folding and unfolding mechanism, the present invention can flip all the second-wound solar array components outside the entire satellite envelope. Then, the extension mechanism can unfold and lay out the first and second-wound solar array components, effectively increasing the width of the solar array in the fully unfolded state. Compared with the prior art, while effectively increasing the solar array area, it can effectively reduce the length of the solar array in the fully unfolded state, effectively increasing the overall fundamental frequency of the solar array. Attached Figure Description
[0018] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a top view of the invention, mainly showing the three-fold solar array in its retracted state; Figure 2 This invention is primarily illustrated by a top view showing the three-fold solar array unfolded into a straight line. Figure 3 This is a side view of the three-fold solar array in its extended state, which is the main feature of this invention. Figure 4 This is a schematic diagram illustrating the structure of the folding and unfolding mechanism when the three-fold solar array is unfolded into a straight state, which is the main feature of this invention. Figure 5 This is a schematic diagram illustrating the folding and unfolding mechanism of the three-fold solar array, which is the main feature of this invention.
[0019] As shown in the figure: Detailed Implementation
[0020] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.
[0021] This invention provides a foldable, rollable solar array configuration that can unfold multiple rollable solar array components beyond the satellite envelope before laying them out. This effectively increases the width of the solar array in the fully unfolded state, effectively reduces the length of the solar array in the fully unfolded state while effectively increasing the solar array area, and effectively improves the overall fundamental frequency of the solar array.
[0022] like Figure 1 As shown, a foldable, rollable solar array configuration includes: a first rollable solar array component 1, a folding and unfolding mechanism 2, multiple second rollable solar array components 3, and an extension mechanism 4.
[0023] At least one second-wound solar array component 3 is provided at each end of the first-wound solar array component 1. The number of second-wound solar array components 3 is unlimited, and the total volume is determined by the overall envelope of the satellite. The end of the second-wound solar array component 3 closest to the first-wound solar array component 1 is connected to one end of the first-wound solar array component 1 through a folding and unfolding mechanism 2. Adjacent second-wound solar array components 3 are connected by a folding and unfolding mechanism 2 to form a three-fold solar array.
[0024] One embodiment of the present invention is as follows: Figure 1 As shown, two second-winding solar wing components 3 are respectively disposed at both ends of the first-winding solar wing component 1, and the two second-winding solar wing components 3 are respectively connected to the ends of the first-winding solar wing component 1 through a folding and unfolding mechanism 2.
[0025] like Figure 1 As shown, in the folded state, multiple second-wound solar array components 3 and the first-wound solar array component 1 are all located on the surface of the satellite's upper top plate, placed parallel to the surface of the upper top plate; during the unfolding process, the folding and unfolding mechanism 2 is used to flip the second-wound solar array components 3 until the first-wound solar array component 1 and the multiple second-wound solar array components 3 are in a straight line in a first direction, wherein the first direction is the length direction of the first-wound solar array component 1, i.e. Figure 1 The left and right directions in the middle.
[0026] An extension mechanism 4 may be provided on the first wound solar wing component 1 and / or the second wound solar wing component 3. The extension mechanism 4 is used to unfold and lay the first wound solar wing component 1 and the second wound solar wing component 3 in a second direction.
[0027] In one embodiment, each second wound solar wing component 3 is provided with an extension mechanism 4. The extension mechanism 4 is used to unfold and lay the second wound solar wing component 3 in a second direction. Simultaneously, the extension mechanism 4 can also unfold and lay the first wound solar wing component 1 in the second direction, which is the width direction of the first wound solar wing component 1 and is perpendicular to the first direction. In another embodiment, extension mechanisms 4 can be provided on both the first wound solar wing component 1 and the second wound solar wing component 3, which can also unfold and lay the first wound solar wing component 1 and the second wound solar wing component 3 in the second direction.
[0028] like Figure 2 As shown, for example, the first wound solar panel component 1 includes a first fixed frame 11 and a first wound battery blanket assembly 12, the first wound battery blanket assembly 12 being connected to the first fixed frame 11. The second wound solar panel component 3 includes a second fixed frame 31 and a second wound battery blanket assembly 32, the first wound battery blanket assembly 12 being connected to the second fixed frame 31. Furthermore, the second fixed frame 31 is connected to the end of the first fixed frame 11 via a folding and unfolding mechanism 2, and the second fixed frames 31 of two adjacent second wound solar panel components 3 are connected via the folding and unfolding mechanism 2.
[0029] like Figure 3 As shown, for example, the first wound solar cell blanket assembly 12 includes a first flexible solar cell blanket 121 and a first winding cylinder 122, and the second wound solar cell blanket assembly 32 includes a second flexible solar cell blanket 321 and a second winding cylinder 322. One end of the first flexible solar cell blanket 121 is fixedly connected to the first winding cylinder 122, and the other end is fixedly connected to the first fixed frame 11; one end of the second flexible solar cell blanket 321 is fixedly connected to the second winding cylinder 322, and the other end is fixedly connected to the second fixed frame 31.
[0030] The extension mechanism 4 may include an elastic extension rod 41 and a storage tube 42. One end of the elastic extension rod 41 is fixedly connected to the second fixed frame 31, and the other end of the elastic extension rod 41 is fixedly connected to the storage tube 42. The storage tube 42 is fixedly connected to the second winding tube 322, or connected to the first winding tube 122 by moving the folding and unfolding component 22.
[0031] When the elastic extension rod 41 unfolds, it pushes the storage tube 42 to rotate, thereby driving the second winding tube 322 and the first winding tube 122 to rotate, thereby laying the first flexible solar cell blanket 121 on the first winding tube 122 and the second flexible solar cell blanket 321 on the second winding tube 322 downwards.
[0032] Figure 4 and Figure 5The structure of the folding and unfolding mechanism 2 is shown. The folding and unfolding mechanism 2 includes a fixed folding and unfolding component 21 and a movable folding and unfolding component 22. Figures 2 to 5 As shown, the extension mechanism 4 is mounted on the second fixed frame 31 and is fixedly connected to the second winding cylinder 322.
[0033] The first fixed frame 11 is connected to the second fixed frame 31 via a fixed folding and unfolding component 21, and the second fixed frames 31 of two adjacent second winding solar panel components 3 are connected via the fixed folding and unfolding component 21. The extension mechanism 4 on the second fixed frame 31 is also fixedly connected to the first winding cylinder 122 via a movable folding and unfolding component 22. The second winding cylinder 322 is also connected to the extension mechanism 4 on the adjacent second fixed frame 31 via the movable folding and unfolding component 22. For example, the extension mechanism 4 is located on the side of the second winding battery blanket assembly 32 closer to the first winding solar panel component 1.
[0034] For example, the first wound solar array component 1 and each of the second wound solar array components 3 are provided with a clamping and releasing mechanism 5. In the retracted state, the first wound solar array component 1 and each of the second wound solar array components 3 are fastened to the satellite surface by the clamping and releasing mechanism 5. That is, the first fixed frame 11 and the second fixed frame 31 are both fixedly connected to the satellite surface by the clamping and releasing mechanism 5 to bear the load during the launch process.
[0035] For example, the folding and unfolding mechanism 2 can be an active unfolding mechanism or a passive unfolding mechanism. The active unfolding mechanism can be driven by a motor, shape memory alloy, hydraulic / pneumatic, electromagnetic, smart materials, pyrotechnics, etc., while the passive unfolding mechanism can be driven by the elastic deformation of the material.
[0036] During the unfolding process of the first flexible solar cell blanket 121 and the second flexible solar cell blanket 321, the first fixed frame 11 and the second fixed frame 31 are fixed in position, the extension mechanism 4 is extended and driven, the first winding cylinder 122 and the second winding cylinder 322 rotate, thereby laying out the first flexible solar cell blanket 121 and the second flexible solar cell blanket 321.
[0037] In one embodiment, the extension mechanism 4 is a commonly used high-capacity extension mechanism. For example, the extension mechanism 4 can be any one of the following: an extension mechanism 4 based on a bistable thin-walled elastic extension rod 41, an extension mechanism 4 based on a scissor fork, or an extension mechanism 4 based on a telescopic sleeve.
[0038] Working principle After the clamping release mechanism 5 is released, the second wound solar panel component 3 begins to flip under the action of the folding and unfolding mechanism 2. Finally, the first fixed frame 11 of the first wound solar panel component 1 and the second fixed frames 31 of all the second wound solar panel components 3 rotate to the same straight line. The first wound battery blanket assembly 12 mounted on the first fixed frame 11 and the second wound battery blanket assembly 32 mounted on the second fixed frames 31 are also in a straight line (e.g., ...). Figure 2 (As shown).
[0039] When the extension mechanism 4 begins to extend upwards, it drives the first winding drum 122 and the second winding drum 322 to move upwards. Since one end of the first flexible solar cell blanket 121 is connected to the first fixed frame 11 and one end of the second flexible solar cell blanket 321 is connected to the second fixed frame 31, the first flexible solar cell blanket 121 and the second flexible solar cell blanket 321 begin to be laid out. Finally, the first winding solar wing component 1 and the second winding solar wing component 3 are unfolded as shown in the figure. Figure 3 As shown.
[0040] The folding and unfolding mechanism 2 of this application embodiment can flip all the second-wound solar array components 3 outside the entire satellite envelope before unfolding the solar cell blanket, and then use the stretching mechanism 4 to unfold and lay the solar cell blanket. Therefore, it can effectively increase the width of the solar array in the fully unfolded state. While effectively increasing the solar array area, it can effectively reduce the length of the solar array in the fully unfolded state, effectively increase the overall fundamental frequency of the solar array. In addition, this solution can also effectively reduce the winding diameter of the wound solar array, thereby effectively reducing the stacking height of the flat satellite and reducing space occupation.
[0041] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.
[0042] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.
Claims
1. A foldable, rollable solar array configuration, characterized in that, include: The first winding solar wing component (1), the folding and unfolding mechanism (2), multiple second winding solar wing components (3) and the extension mechanism (4); The first wound solar wing component (1) is provided with at least one second wound solar wing component (3) at both ends in the first direction. The end of the second wound solar wing component (3) is connected to the first wound solar wing component (1) through a folding and unfolding mechanism (2). The folding and unfolding mechanism (2) is used to flip the second wound solar wing component (3). When in the unfolded state, the second coiled solar wing component (3) rotates to be collinear with the first coiled solar wing component (1) in the first direction; The extension mechanism (4) is provided on the first wound solar wing component (1) and / or the second wound solar wing component (3), the extension mechanism (4) being used to unfold and lay the first wound solar wing component (1) and the second wound solar wing component (3) in a second direction.
2. The foldable, rollable solar array configuration as described in claim 1, characterized in that, The extension mechanism (4) on each of the second winding solar wing components (3) connected to the first winding solar wing component (1) simultaneously unfolds the first winding solar wing component (1) in the second direction.
3. The foldable, rollable solar array configuration as described in claim 1, characterized in that, When the spiral solar array configuration is in the retracted state, the second spiral solar array component (3) and the first spiral solar array component (1) are both located on the surface of the satellite's upper top plate and are arranged parallel to the surface of the satellite's upper top plate.
4. The foldable, rollable solar array configuration as described in claim 1, characterized in that, The first wound solar panel component (1) includes a first fixed frame (11) and a first wound battery blanket assembly (12) connected to the first fixed frame (11). The second wound solar panel component (3) includes a second fixed frame (31) and a second wound battery blanket assembly (32) connected to the second fixed frame (31). The second fixed frame (31) is connected to one end of the first fixed frame (11) through the folding and unfolding mechanism (2), and the second fixed frames (31) of two adjacent second winding solar wing components (3) located on the same side as the first winding solar wing component (1) are connected through the folding and unfolding mechanism (2).
5. The foldable, rollable solar array configuration as described in claim 4, characterized in that, The first wound solar blanket assembly (12) includes a first flexible solar blanket (121) and a first winding cylinder (122), and the second wound solar blanket assembly (32) includes a second flexible solar blanket (321) and a second winding cylinder (322). One end of the first flexible solar cell blanket (121) is fixedly connected to the first winding cylinder (122), and the other end is fixedly connected to the first fixed frame (11); one end of the second flexible solar cell blanket (321) is fixedly connected to the second winding cylinder (322), and the other end is fixedly connected to the second fixed frame (31).
6. The foldable, rollable solar array configuration as described in claim 5, characterized in that, The extension mechanism (4) is mounted on the second fixed frame (31) and is fixedly connected to the second winding cylinder (322).
7. The foldable, rollable solar array configuration as described in claim 6, characterized in that, The folding and unfolding mechanism (2) includes a fixed folding and unfolding component (21) and a movable folding and unfolding component (22). The first fixed frame (11) is connected to the second fixed frame (31) through the fixed folding and unfolding component (21), and the second fixed frames (31) of two adjacent second rolled solar wing components (3) are connected through the fixed folding and unfolding component (21). The extension mechanism (4) on the second fixed frame (31) connected to the first fixed frame (11) is also fixedly connected to the first winding cylinder (122) by moving the folding unfolding component (22).
8. The foldable, rollable solar array configuration as described in claim 7, characterized in that, The second winding cylinder (322) is also connected to the extension mechanism (4) on the adjacent second fixed frame (31) via the movable folding unfolding component (22).
9. The foldable, rollable solar array configuration as described in any one of claims 4-8, characterized in that, Each of the first wound solar panel component (1) and each of the second wound solar panel components (3) is provided with a clamping release mechanism (5), and the first fixed frame (11) and the second fixed frame (31) are both fixedly connected to the satellite surface through the clamping release mechanism (5); The extension mechanism (4) includes any one of the following: an extension mechanism based on an elastic extension rod, an extension mechanism based on a scissor fork, or an extension mechanism based on a telescopic sleeve.
10. The foldable, rollable solar array configuration as described in any one of claims 1-8, characterized in that, The extension mechanism (4) is located on the side of the second wound battery blanket assembly (32) near the first wound solar panel component (1).