Flexible solar wing and spacecraft

Abstract

The invention relates to a flexible solar wing and a spacecraft, the flexible solar wing is loaded on a satellite, and the flexible solar wing comprises a storage box assembly, a connecting rod assembly and a solar blanket assembly. The storage box assembly comprises a box body and a cover plate arranged on the box body in an opening and closing mode. A rotatable reel is arranged in the box body; the two opposite ends of the connecting rod assembly are connected with the satellite and the box body correspondingly and can drive the storage box assembly to move to the working position in the direction away from the satellite. The solar blanket assembly is wound on the reel and keeps a tightening posture when the cover plate is closed; the solar blanket assembly is provided with a fixed end connected with the reel and a free end opposite to the fixed end; when the storage box assembly is located at the working position and the cover plate is opened, the free end can move in the direction away from the satellite under the driving effect of the unfolding assembly so that the solar blanket assembly can move to the unfolding posture. The mass center of the unfolded flexible solar wing is close to the satellite, so that the unfolding fundamental frequency is improved, the rotational inertia is reduced, and satellite in-orbit attitude control is facilitated.

Description

Technical Field

[0001] This disclosure relates to the field of aerospace technology, specifically to a flexible solar array and a spacecraft. Background Technology

[0002] Solar panels are core energy supply components for spacecraft during their on-orbit operation. Their main function is to convert solar energy into electrical energy, providing power support for the operation of various on-orbit equipment. With the continuous development of aerospace technology, more and more spacecraft are adopting flexible solar panels. Flexible solar panels have become an important choice for various spacecraft due to their advantages such as light weight, small storage volume, and large deployment area.

[0003] Currently, most flexible solar arrays in my country adopt a folding design, which suffers from problems such as complex bottom disassembly, high coupling with the entire spacecraft, and long assembly and integration time, hindering large-scale mass production. To overcome these shortcomings, engineers have developed a roll-up solar array as an alternative. Specifically, the roll-up solar array stores the flexible solar blanket by winding it around a roller. In orbit, the solar blanket is gradually released and unfolded by rotating the roller in conjunction with the unfolding mechanism. It has advantages such as high storage efficiency and simple structure.

[0004] In existing technologies, as the solar blanket gradually unfolds, the reel moves further away from the star's end, eventually ending up at a position far from the star. Due to the reel's large mass, its placement at the end of the solar array results in an outward-biased mass distribution after deployment, leading to a low fundamental frequency and poor structural dynamics. Furthermore, the center of mass shifting away from the star after full deployment results in a large moment of inertia relative to the star, increasing the difficulty and energy consumption of on-orbit attitude control and hindering overall spacecraft attitude control. Summary of the Invention

[0005] This disclosure provides a flexible solar array and a spacecraft to address the problems existing in the prior art.

[0006] According to a first aspect of this disclosure, a flexible solar array is provided for mounting on a satellite, the flexible solar array comprising: A storage box assembly includes a box body and a cover plate that opens and closes on the box body; a rotatable scroll is provided in the box body; A linkage assembly, wherein the opposite ends of the linkage assembly are respectively connected to the satellite and the housing, and is configured to drive the housing assembly to move in a direction away from the satellite to the working position; A sun blanket assembly is wound on the spool and configured to remain in a taut position when the cover is closed; the sun blanket assembly has a fixed end connected to the spool and a free end opposite to the fixed end; When the storage box assembly is in the working position and the cover is open, the free end of the sun blanket assembly can move away from the satellite under the driving action of the unfolding assembly, so that the sun blanket assembly moves to the unfolded posture.

[0007] In one embodiment of this disclosure, a clamping release device is further provided between the housing and the satellite, the clamping release device being configured to restrain the housing assembly in an initial position adjacent to the satellite; when the clamping release device is unlocked, the housing assembly moves in a direction away from the satellite to a working position.

[0008] In one embodiment of this disclosure, at least one of the clamping release devices is disposed on the linkage assembly, which is configured to remain in a folded state under the action of the clamping release device; when the clamping release device is unlocked, the linkage assembly can switch from the folded state to the extended state to drive the storage box assembly to move in a direction away from the satellite to the working position.

[0009] In one embodiment of this disclosure, an unlocking device is also provided on the storage box assembly. The cover is kept closed under the locking action of the unlocking device to press the sun blanket assembly into the box body. When the unlocking device is unlocked, the cover can be opened and the sun blanket assembly can be released.

[0010] In one embodiment of this disclosure, the cover is configured to be rotatably connected to the housing via a spring hinge, and is configured to have a tendency to rotate toward an open position under the elastic force applied by the spring hinge. When the unlocking device is unlocked, the cover plate rotates relative to the box body under the elastic force of the spring hinge and remains in the open position.

[0011] In one embodiment of this disclosure, a first limiting member is provided on the cover plate, and a second limiting member is provided on the reel for cooperating with the first limiting member; when the cover plate is closed, the first limiting member and the second limiting member remain in cooperation to restrict the rotational freedom of the reel; when the cover plate is opened, the first limiting member disengages from the second limiting member.

[0012] In one embodiment of this disclosure, the first limiting member includes two racks disposed on the inner wall surface of the cover plate, the two racks being located at opposite ends in the extending direction of the cover plate; The second limiting member includes two gears disposed at opposite ends of the spool, and the two gears are disposed in a one-to-one correspondence with the two racks; when the cover is closed, the racks mesh with the corresponding gears to restrict the rotational freedom of the spool.

[0013] In one embodiment of this disclosure, the unfolding assembly includes a power unit for driving the sun blanket assembly to unfold, and a tensioning device connected between the free end and the power unit; At least when the sun blanket assembly is in the deployed position, the tensioning device is configured to continuously apply a tension force to the sun blanket assembly in a direction away from the satellite.

[0014] In one embodiment of this disclosure, a damping device mounted on the reel is also included, which is configured to apply rotational resistance to the reel during the unfolding of the sun blanket assembly driven by the power unit. The flexible solar array further includes a rotation drive device disposed between the linkage assembly and the satellite, and a swing drive device disposed on the housing; the rotation drive device has a first output axis, the swing drive device has a second output axis, the first output axis is perpendicular to the second output axis, and the second output axis is parallel to the extension axis of the reel; When the sun blanket assembly is in the unfolded position, the rotation drive device is configured to drive the flexible sun wings to rotate around the first output axis, and the swing drive device is configured to drive the sun blanket assembly to swing around the second output axis within a preset angle range via the housing.

[0015] According to a second aspect of this disclosure, a spacecraft is provided, including a satellite, and a flexible solar array according to a first aspect of this disclosure, the flexible solar array being mounted on the satellite.

[0016] One beneficial effect of this disclosure is that by using a linkage assembly to move the storage box assembly to the working position first, and then using the deployment assembly to drive the free end of the solar blanket assembly to unfold, the flexible solar array can be deployed in an orderly, step-by-step manner after entering orbit, thereby improving the controllability and reliability of the deployment process. Furthermore, the scroll is integrated into the storage box assembly, and the linkage assembly connecting the satellite and the storage box assembly ensures that the scroll remains close to the satellite after the solar blanket assembly reaches its deployment posture. This keeps the center of mass of the flexible solar array close to the satellite after deployment, thereby increasing the deployment fundamental frequency, reducing rotational inertia, and facilitating on-orbit attitude control of the satellite.

[0017] Other features and advantages of this disclosure will become clear from the following detailed description of exemplary embodiments with reference to the accompanying drawings. Attached Figure Description

[0018] The accompanying drawings, which are incorporated in and form a part of this specification, illustrate embodiments of the present disclosure and, together with their description, serve to explain the principles of the present disclosure.

[0019] Figure 1 This is a schematic diagram of the flexible solar panel structure of the storage box assembly in its initial position according to an embodiment of this disclosure; Figure 2 yes Figure 1 A magnified view of the left end of the flexible solar panel; Figure 3 This is a schematic diagram of a partial structure of the flexible solar panel when the cover is closed, according to an embodiment of this disclosure; Figure 4 This is a schematic diagram of a partial structure of the flexible solar panel when the cover is opened, according to an embodiment of this disclosure; Figure 5 This is a schematic diagram of the flexible solar panel structure of the storage box assembly provided in an embodiment of the present disclosure when it is in the working position; Figure 6 This is a front view of the flexible solar panel of a solar blanket assembly provided in an embodiment of the present disclosure when it is in the deployed posture; Figure 7 yes Figure 6 A magnified view of the free end of the central sun blanket assembly; Figure 8 This is a rear view of the flexible solar panel of a solar blanket assembly provided in an embodiment of the present disclosure when it is in the deployed position; Figure 9 yes Figure 8 A magnified view of the free end of the central sun blanket assembly; Figure 10 This is a schematic diagram of the rotation and swing of a sun blanket assembly provided in one embodiment of the present disclosure.

[0020] Figures 1 to 10 The one-to-one correspondence between the component names and the reference numerals in the figures is as follows: 1. Storage box assembly; 11. Box body; 12. Cover plate; 13. Spring hinge; 14. Rack; 2. Roller; 21. Gear; 22. Damping device; 3. Linkage assembly; 31. First rod; 32. Second rod; 33. Rotating shaft; 4. Sun blanket assembly; 41. Fixed end; 42. Free end; 5. Pressing release device; 6. Unlocking device; 7. Unfolding assembly; 71. Power unit; 711. Scissor mechanism; 712. Crossbeam; 72. Tensioning device; 8. Swing drive device. Detailed Implementation

[0021] Various exemplary embodiments of the present disclosure will now be described in detail with reference to the accompanying drawings. It should be noted that, unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the present disclosure.

[0022] The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit this disclosure or its application or use.

[0023] Techniques, methods, and equipment known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and equipment should be considered part of the specification.

[0024] It should be noted that similar labels and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be discussed further in subsequent figures.

[0025] In this article, terms such as "up," "down," "front," "back," "left," and "right" are used only to indicate the relative positional relationship between related parts, rather than to define the absolute position of these related parts.

[0026] In this article, "first," "second," etc., are used only to distinguish one another, and not to indicate degree of importance, order, or prerequisite for each other.

[0027] In this document, terms such as “equal” and “same” are not strict mathematical and / or geometric limitations, but also include errors that are understandable to those skilled in the art and permissible in manufacturing or use.

[0028] This disclosure provides a spacecraft and a flexible solar array. The spacecraft includes a satellite and the flexible solar array, which is mounted on the satellite. During the satellite's on-orbit operation, the flexible solar array converts solar energy into electrical energy through photoelectric conversion, thereby providing energy to the on-orbit satellite and ensuring the long-term stable operation of the spacecraft in orbit. During the satellite launch phase, the flexible solar array remains in a retracted (folded or rolled up) state. At this time, the flexible solar array has a small volume and windward area, suitable for the harsh mechanical environment of rocket launch, and reduces the risk of interference before initial deployment in orbit. Once the satellite is stable in orbit, the flexible solar array can be deployed according to a preset program, fully exposing the solar cells on its surface to sunlight, thereby generating electricity to power the satellite.

[0029] refer to Figure 6 The flexible solar panel disclosed herein includes: a storage box assembly 1, a connecting rod assembly 3, and a solar blanket assembly 4. The storage box assembly 1 is used to store the solar blanket assembly 4, as shown in the reference. Figure 1 , Figure 5 and Figure 6The storage box assembly 1 includes a box body 11 and a cover plate 12 that opens and closes on the box body 11. A rotatable scroll 2 is disposed within the box body 11. Specifically, the box body 11 is a cavity structure with one open end, which is used for the solar blanket assembly 4 to extend and unfold outward. The cover plate 12 is opened and closed at the open end of the box body 11. When closed, the cover plate 12 can press the solar blanket assembly 4 tightly inside the box body 11 to prevent damage to the solar blanket assembly 4 from vibration, impact, or space dust during the launch phase, ensuring that the flexible solar array as a whole has good resistance performance. The opposite ends of the scroll 2 are rotatably engaged with the opposite side walls of the box body 11 in the extension direction to achieve rotatable assembly, ensuring that the scroll 2 rotates smoothly when winding or releasing the solar blanket assembly 4.

[0030] refer to Figure 1 and Figure 5 The connecting rod assembly 3 connects the satellite and the housing 11 at opposite ends, and is configured to move the storage box assembly 1 away from the satellite to its working position. It should be noted that in this embodiment, the storage box assembly 1 is defined to have an initial position and a working position, such as... Figure 1 As shown, "initial position" refers to the location of the storage box assembly 1 near the satellite during the satellite launch phase, at which time the linkage assembly 3 is in a folded state; as Figure 5 As shown, the "working position" refers to the preset position after the linkage assembly 3 drives the storage box assembly 1 to complete its initial extension, providing a foundation for the deployment of the sun blanket assembly 4. At this time, the linkage assembly 3 is in the extended state. When the storage box assembly 1 is in the working position, the sun blanket assembly 4 is pushed away from the satellite by a certain distance. This can prevent the sun blanket assembly 4 from generating heat during power generation and causing the satellite temperature to rise. In addition, it is also beneficial to meet the field of view requirements of each unit of the satellite.

[0031] In one embodiment of this disclosure, the linkage assembly 3 includes a first link 31, a second link 32, and a pivot 33, as shown in the reference. Figure 5 In the view, the lower end of the first rod 31 is used to connect to the satellite, and the upper end of the second rod 32 is used to connect to the housing 11. The upper end of the first rod 31 and the lower end of the second rod 32 are rotatably connected via a pivot 33. Specifically, the lower end of the first rod 31 is rotatably connected to the satellite. For example, the lower end of the first rod 31 can be connected to a rotary drive device, which is fixedly installed on the satellite, thereby indirectly rotatably connecting the lower end of the first rod 31 to the satellite. The upper end of the second rod 32 is rotatably connected to the housing 11. In this embodiment, the linkage assembly 3 has at least three degrees of rotational freedom, which allows the linkage assembly 3 to have a large deformation space and drive the storage box assembly 1 to move a large displacement.

[0032] like Figure 1As shown, the linkage assembly 3 is initially in a folded state. At this time, the first rod 31 and the second rod 32 are fixed in a folded posture under the action of the external component, so that the storage box assembly 1 is in an initial position close to the satellite. After the fixing action of the external component is removed, the linkage assembly 3 can move to the extended state under the driving action of the built-in drive component (such as a spring, motor, etc.). Specifically, the first rod 31 can rotate relative to the satellite to be substantially perpendicular to the satellite surface, and the second rod 32 can rotate relative to the box body 11 to be substantially perpendicular to the bottom surface of the box body. Moreover, the first rod 31 and the second rod 32 can rotate through the pivot 33 to have the same extension direction, thereby driving the storage box assembly 1 to move smoothly away from the satellite to the working position. Preferably, the extension speed of the linkage assembly 3 during the movement can be controlled by the built-in damping component to avoid impact damage caused by excessive extension speed.

[0033] refer to Figure 5 and Figure 6 The solar blanket assembly 4 is wound onto the scroll 2. Specifically, the main body of the solar blanket assembly 4 can be a flexible photovoltaic film. Compared to traditional rigid solar panels, flexible photovoltaic films are much lighter, thus significantly reducing the overall weight of the flexible solar array and lowering spacecraft launch costs. Furthermore, the flexibility of the photovoltaic film allows it to be stored in a wound manner, eliminating the need for traditional folding methods. Traditional folding methods require folding the solar array into a multi-layered structure, and the folded shape is limited by the overall contour of the solar array, resulting in significant wasted storage space. In contrast, the wound solar blanket assembly 4 used in this disclosure achieves storage through a spiral winding method on the scroll 2. The layers of the solar blanket assembly 4 fit tightly together, requiring only an adjustment to the diameter of the scroll 2 for storage, thus reducing the space occupied by the flexible solar array during satellite launch.

[0034] Furthermore, foldable solar panels require high folding precision, necessitating multi-layer folding and positioning during ground assembly, resulting in a cumbersome process. When unfolding, the constraint structures of each fold layer must be unlocked sequentially; failure to unlock any layer's constraint will directly lead to overall unfolding failure. In contrast, the roll-up solar blanket assembly 4 disclosed in this invention only requires rotation of the roller 2 for storage, significantly simplifying the ground assembly process. The unfolding of the solar blanket assembly 4 eliminates the need for cumbersome timing control, resulting in fewer constraint structures and fewer potential failure points, thereby greatly improving the unfolding success rate. Moreover, the solar blanket assembly 4 leaves no residual folds after unfolding, maintaining a better flattened state, ensuring the photovoltaic layer receives sufficient light, and improving photoelectric conversion efficiency.

[0035] refer to Figure 6 and Figure 8The solar blanket assembly 4 has a fixed end 41 connected to the roll 2 and a free end 42 opposite to the fixed end 41. Specifically, the fixed end 41 can be fixedly connected to the roll 2 by means of bolts or adhesive, ensuring that the roll 2 can synchronously drive the solar blanket assembly 4 to wind or unwind when it rotates. A rigid traction strip can be provided on the free end 42, and the traction strip has reserved mounting holes for connecting to the unfolding assembly 7. The solar blanket assembly 4 is configured to maintain a tightened posture when the cover plate 42 is closed. The cover plate 42 can constrain the free end 42 of the solar blanket assembly 4 and the unfolding assembly 7. The solar blanket assembly 4 in the tightened posture is tightly wound on the roll 2, thereby reducing vibration displacement during the emission phase, avoiding collision and wear of the solar blanket assembly 4, and protecting the integrity of the photovoltaic layer.

[0036] When the storage box assembly 1 is in the working position and the cover 12 is open, the free end 42 of the sun blanket assembly 4 can move away from the satellite under the driving action of the deployment assembly 7, so that the sun blanket assembly 4 moves to the deployed posture. The flexible solar array provided in this disclosure follows the working sequence of first extending the storage box assembly 1 and then deploying the sun blanket assembly 4. After the satellite enters the predetermined orbit, the linkage assembly 3 is triggered first, driving the storage box assembly 1 from the initial position to the working position away from the satellite; then the cover 12 is opened, releasing the constraints on the sun blanket assembly 4 and the deployment assembly 7. The deployment assembly 7 drives the free end 42 of the sun blanket assembly 4 to move away from the satellite, simultaneously driving the roller 2 to rotate and release the sun blanket assembly 4, until the sun blanket assembly 4 is fully deployed and maintained in the deployed posture. This disclosure adopts a step-by-step deployment process to avoid mutual interference between the movement of the storage box assembly 1 and the deployment of the sun blanket assembly 4, improving the controllability and reliability of the overall deployment process of the flexible solar array.

[0037] This disclosure integrates the scroll 2 into the storage box assembly 1, and the linkage assembly 3 connects the satellite and the storage box assembly 1. This arrangement ensures that the scroll 2 remains close to the satellite after the solar blanket assembly 4 moves to its deployed position. This brings the center of mass of the flexible solar array closer to the satellite after deployment, thereby increasing the deployment fundamental frequency, reducing rotational inertia, and facilitating on-orbit attitude control of the satellite. It should be noted that the solar array deployment fundamental frequency is a key indicator for evaluating its structural dynamic performance. If the deployment fundamental frequency is too low, it can easily lead to fatigue or even damage to the solar array and structure. This disclosure positions the scroll 2 close to the satellite, thereby reducing the pulling force of the far-end mass on the solar blanket assembly 4. The centralized mass distribution increases the deployment fundamental frequency, thus improving the reliability of the flexible solar array.

[0038] In one embodiment of this disclosure, reference is made to Figure 1The flexible solar array also includes a clamping release device 5 disposed between the housing 11 and the satellite. The clamping release device 5 is configured to secure the housing assembly 1 to an initial position adjacent to the satellite; when the clamping release device 5 is unlocked, the housing assembly 1 moves away from the satellite to a working position. Specifically, the clamping release device 5 can be a shape memory alloy unlocker, a pyrotechnic unlocker, an electromagnetic unlocker, etc., and this disclosure does not limit its specific type. Multiple clamping release devices 5 can be provided, and multiple clamping release devices 5 are distributed in the connection area between the housing 11 and the satellite body.

[0039] Specifically, at least one clamping release device 5 is provided on the linkage assembly 3, and the linkage assembly 3 is configured to remain in a folded state under the action of the clamping release device 5, such as Figure 1 As shown, the two ends of the clamping release device 5 can be respectively mounted on the first rod 31 and the second rod 32. When the clamping release device 5 is in the locked state, the first rod 31 and the second rod 32 maintain an approximately parallel folded state; when the clamping release device 5 is unlocked, the linkage assembly 3 is no longer constrained, the first rod 31 and the second rod 32 can rotate relative to each other, and the linkage assembly 3 can switch from the folded state to the extended state to drive the storage box assembly 1 to move away from the satellite to the working position. This disclosure, by directly setting the clamping release device 5 on the linkage assembly 3, can directly release the motion freedom of the linkage assembly 3 after unlocking, making the extension response of the linkage assembly 3 faster and reducing power transmission loss.

[0040] In this embodiment, a total of five clamping and releasing devices 5 are provided. Four of the clamping and releasing devices 5 are installed on the opposite ends of the housing 11 and the satellite body, respectively, and one of the clamping and releasing devices 5 is installed on the connecting rod assembly 3, thus achieving dual constraint on the connecting rod assembly 3 and the storage box assembly 1. The five clamping and releasing devices 5 can be unlocked simultaneously by control signals. During the satellite launch phase, all clamping and releasing devices 5 are in a locked state, thereby firmly binding the storage box assembly 1 to the initial position adjacent to the satellite and binding the connecting rod assembly 3 to a folded state. When the satellite enters the predetermined orbit, all clamping and releasing devices 5 are energized and disconnected, thereby freeing the storage box assembly 1 and the connecting rod assembly 3 from constraint. The connecting rod assembly 3 can move to the extended state under the driving action of the built-in driving component (such as a spring, motor, etc.), thereby driving the storage box assembly 1 to the working position.

[0041] This disclosure improves the stability of the housing assembly 1 by incorporating a clamping and releasing device 5, enabling it to withstand strong vibrations and impact loads during launch, preventing relative displacement between the housing assembly 1 and the satellite, and thus protecting the internal solar blanket assembly 4. The use of multiple evenly distributed clamping and releasing devices 5 ensures uniform distribution of constraint force, preventing excessive localized stress on the housing 11 and subsequent deformation. The clamping and releasing devices 5 can quickly unlock without leaving any residual constraint after unlocking, and do not interfere with the subsequent movement of the housing assembly 1.

[0042] In one embodiment of this disclosure, reference is made to Figure 2 , Figure 3 and Figure 5 The flexible solar panel also includes an unlocking device 6 disposed on the storage box assembly 1. The cover 12 remains closed under the locking action of the unlocking device 6, thus pressing the solar blanket assembly 4 into the box body 11. When the unlocking device 6 unlocks, the cover 12 can open and release the solar blanket assembly 4. Specifically, the unlocking device 6 can be a shape memory alloy unlocker, a pyrotechnic unlocker, an electromagnetic unlocker, etc., and this disclosure does not limit its specific type. The opposite ends of the unlocking device 6 can be respectively installed on the cover 12 and the box body 11. When the unlocking device 6 is in the locked state, the cover 12 remains closed under its binding force. At this time, the cover 12 can form a radial pressing force on the solar blanket assembly 4 inside the box body 11, ensuring that the solar blanket assembly 4 remains in a taut posture and preventing loosening. Preferably, two unlocking devices 6 can be provided, which are used to fix the opposite ends of the cover 12 in the extending direction, thereby making the pressing force applied by the cover 12 to the solar blanket assembly 4 more uniform. When the storage box assembly 1 moves to the working position, the unlocking device 6 is powered off, thereby freeing the cover 12 from restraint. The cover 12 can be opened by external force or its own driving structure.

[0043] This disclosure utilizes an unlocking device 6 to control the opening and closing of the cover 12, preventing it from accidentally opening during launch due to vibration or impact. This ensures the sun blanket assembly 4 is firmly held within the housing 11 and does not deploy prematurely. The pressing action of the cover 12 when closed keeps the sun blanket assembly 4 in a taut position, reducing winding gaps and improving storage compactness. It also prevents collisions and wear caused by the sun blanket assembly 4 moving around within the housing 11. Furthermore, the unlocking device 6 features fast response, high locking reliability, and small size, adapting to the space and operational requirements of spacecraft. After unlocking, it leaves no residual constraints, does not interfere with the subsequent movement of the cover 12, and does not obstruct the deployment path of the sun blanket assembly 4.

[0044] In one embodiment of this disclosure, reference is made to Figure 3 and Figure 5The cover plate 12 is configured to be rotatably connected to the housing 11 via a spring hinge 13, and is configured to tend to rotate towards the open position under the elastic force applied by the spring hinge 13. When the unlocking device 6 is unlocked, the cover plate 12 rotates relative to the housing 11 under the elastic force of the spring hinge 13 and remains in the open position. Specifically, the cover plate 12 is rotatably connected to one edge of the opening end of the housing 11 via a spring hinge 13, and the spring hinge 13 has a built-in torsion spring. In the locked state, the unlocking device 6 overcomes the elastic force of the spring hinge 13 to fix the cover plate 12 in the closed position; when the unlocking device is unlocked, the cover plate 12 is no longer affected by the unlocking device 6, and the cover plate 12 rotates under the torsional elastic force of the spring hinge 13 until it rotates to the preset open position. The cover plate 12 can remain in this open position without interfering with the subsequent unfolding of the sun blanket assembly 4. By setting the spring hinge 13, this disclosure eliminates the need for additional drive components such as motors and cylinders, simplifying the structure and reducing energy consumption and failure risk.

[0045] In one embodiment of this disclosure, a first limiting member is provided on the cover plate 12, and a second limiting member is provided on the roll 2 for cooperating with the first limiting member. When the cover plate 12 is closed, the first limiting member and the second limiting member remain engaged to restrict the rotational freedom of the roll 2. When the cover plate 12 is open, the first limiting member disengages from the second limiting member. Specifically, the first limiting member and the second limiting member are correspondingly provided. When the cover plate 12 is closed, the first limiting member and the second limiting member form a mechanical engagement, restricting the rotational freedom of the roll 2 through mechanical locking, preventing the roll 2 from rotating, thereby ensuring that the sun blanket assembly 4 wound on the roll 2 remains in a taut position. When the cover plate 12 is opened, the cover plate 12 drives the first limiting member to move synchronously, causing the first limiting member to disengage from the second limiting member, releasing the rotational freedom of the roll 2, which can then rotate freely as the sun blanket assembly 4 is subsequently unwound.

[0046] This disclosure provides a locking function to the scroll 2 by setting a first limiting member and a second limiting member. This prevents the scroll 2 from rotating accidentally due to vibration during the launch or storage phase, thus preventing the solar blanket assembly 4 from becoming loose or shifting, protecting the photovoltaic layer of the solar blanket assembly 4 from wear, and ensuring the stability of the winding state of the solar blanket assembly 4 before unfolding, laying the foundation for subsequent orderly unfolding. Furthermore, the first limiting member is linked to the cover plate 12, eliminating the need for separate control of the locking and unlocking of the scroll 2, reducing the complexity of the control system.

[0047] In one specific embodiment of this disclosure, reference is made to Figure 2 , Figure 4 and Figure 5The first limiting component includes two racks 14 disposed on the inner wall of the cover plate 12, with the two racks 14 located at opposite ends in the extending direction of the cover plate 12 and their tooth surfaces facing the scroll 2. The second limiting component includes two gears 21 disposed at opposite ends of the scroll 2, with each gear 21 corresponding to one of the two racks 14. When the cover plate 12 is closed, the racks 14 are engaged with the corresponding gears 21 to restrict the rotational freedom of the scroll 2 through the meshing of the tooth surfaces of the gears 21 and the racks 14. When the cover plate 12 is opened, the racks 14 gradually disengage from the gears 21 as the cover plate 12 rotates, and the rotational constraint on the scroll 2 is released.

[0048] The meshing of gear 21 and rack 14 features high limiting accuracy and strong locking reliability, effectively restricting the rotation of the roll 2 and preventing the sun blanket assembly 4 from loosening due to slight rotation. It can also withstand stronger vibrations and impacts. Furthermore, the symmetrical arrangement of the two racks 14 and two gears 21 ensures even force distribution at both ends of the roll 2, preventing eccentricity or deformation of the roll 2 caused by unilateral limiting. Figure 4 As shown, the gear 21 is installed in the unused space on both sides of the scroll 2, thus eliminating the need to provide additional installation space for the scroll 2 limiting structure and improving the utilization rate of the internal space of the box 11.

[0049] In one embodiment of this disclosure, reference is made to Figures 6 to 9 The unfolding assembly 7 includes a power unit 71 for driving the unfolding of the sun blanket assembly 4, and a tensioning device 72 connected between the free end 42 and the power unit 71; at least when the sun blanket assembly 4 is in the unfolded posture, the tensioning device 72 is configured to continuously apply a tension force to the sun blanket assembly 4 in the direction away from the satellite. Specifically, in this embodiment, the power unit 71 consists of a scissor mechanism 711 and a crossbeam 712. The scissor mechanism 711 has a built-in elastic drive element or is equipped with a drive motor, which has the driving capability to extend in the direction away from the satellite and retract in the direction closer to the satellite.

[0050] One end of the scissor mechanism 711 is fixed to the storage box assembly 1, and the other end is fixedly connected to the crossbeam 712. A tensioning device 72 is installed on the crossbeam 712, and the traction end of the tensioning device 72 is connected to the free end 42 of the sun blanket assembly 4, thereby applying tension to the sun blanket assembly 4. The length of the crossbeam 712 is adapted to the width of the sun blanket assembly 4. Multiple connection points are evenly arranged along the length of the crossbeam 712. The number of tensioning devices 72 corresponds one-to-one with the connection points on the crossbeam 712, thus providing a uniform tension to the sun blanket assembly 4 and avoiding uneven force distribution caused by a single traction point. This disclosure achieves multi-point synchronous traction of the free end 42 of the sun blanket assembly 4 by setting the crossbeam 712, ensuring that the sun blanket assembly 4 is simultaneously stressed and extended in the width direction during unfolding, and avoiding skewed unfolding paths.

[0051] During the unfolding of the sun blanket assembly 4, the power unit 71 is activated, and the scissor mechanism 711 gradually extends away from the satellite, driving the crossbeam 712 to move synchronously. The crossbeam 712, through the tensioning devices 72, synchronously pulls the free end 42 of the sun blanket assembly 4 away from the satellite, and drives the roller 2 to rotate and release the sun blanket assembly 4. At the final moment of the unfolding of the sun blanket assembly 4, the scissor mechanism 711 extends to its final position, and the tensioning devices 72 can maintain a constant force output within a certain range of displacement, thereby tauting the sun blanket assembly 4.

[0052] This disclosure utilizes a tensioning device 72 to continuously apply tension, ensuring the solar blanket assembly 4 remains flat and taut. This improves the light-receiving area and photoelectric conversion efficiency of the photovoltaic layer, while preventing the slack solar blanket assembly 4 from swaying due to airflow or vibration in the space environment, thus reducing the risk of interference with other components. Furthermore, prolonged on-orbit operation may cause thermal deformation of the solar blanket assembly 4; the continuous tension output of the tensioning device 72 effectively adapts to on-orbit thermal deformation scenarios, ensuring the solar blanket assembly 4 remains flat and taut after deployment.

[0053] In one embodiment of this disclosure, reference is made to Figure 3 The flexible solar panel also includes a damping device 22 mounted on the reel 2. During the unfolding of the solar blanket assembly 4 driven by the power unit 71, the damping device 22 is configured to apply rotational resistance to the reel 2. Specifically, the damping device 22 can be installed at one end of the reel 2 and is coaxially arranged with the reel 2. When the reel 2 rotates (i.e., when the solar blanket assembly 4 unfolds), the damping device 22 can apply rotational resistance in the opposite direction of rotation. The magnitude of the rotational resistance can be adapted to the unfolding speed requirements of the solar blanket assembly 4 to ensure that the rotation speed of the reel 22 is stable and to avoid the reel 2 rotating too fast due to excessive driving force of the power unit 71. By setting the damping device 22, this disclosure makes the unfolding process of the solar blanket assembly 4 slow and stable, avoiding damage caused by excessive unfolding impact.

[0054] In one embodiment of this disclosure, reference is made to Figure 5 and Figure 10The flexible solar array also includes a rotation drive device (not shown in the figure) disposed between the linkage assembly 3 and the satellite, and a swing drive device 8 disposed on the housing 11. The rotation drive device has a first output axis, and the swing drive device 8 has a second output axis. The first output axis is perpendicular to the second output axis, and the second output axis is parallel to the extension axis of the reel 2. Specifically, the rotation drive device is fixed to the satellite, and its output end is connected to the end of the linkage assembly 3 near the satellite. The rotation axis of this output end is the first output axis, which can extend in a direction perpendicular to the surface of the satellite body. The swing drive device 8 is installed close to the connection area between the linkage assembly 3 and the housing 11, without interfering with the unfolding and storage space of the solar blanket assembly 4. The output end of the swing drive device 8 is connected to the housing 11, and the rotation axis of this output end is the second output axis. The second output axis is parallel to the reel 2 and is perpendicular to the first output axis.

[0055] When the solar blanket assembly 4 is in its unfolded position, the rotation drive device is configured to drive the flexible solar wings to rotate around the first output axis, and the swing drive device 8 is configured to drive the solar blanket assembly 4 to swing around the second output axis within a preset angle range via the housing 11. Specifically, after the solar blanket assembly 4 is fully unfolded, it needs to be controlled to orient itself towards the sun. The two drive devices can work together according to a preset program. The rotation drive device can drive the entire flexible solar wings to rotate around the first output axis, with a rotation angle range of ±360°, achieving seamless rotation coverage to adapt to changes in the sun's position. The swing drive device 8 can drive the storage box assembly 1 and the solar blanket assembly 4 to swing together, with a preset swing angle range of ±30° to adapt to changes in the sun's angle. Based on the vertical distribution relationship between the first and second output axes, the rotation drive device and the swing drive device 8 form a dual-axis drive system, which can adjust the orientation of the solar blanket assembly 4 in real time, ensuring that the photovoltaic layer of the solar blanket assembly 4 is precisely facing the sun, achieving sun orientation, and improving photoelectric conversion efficiency.

[0056] The various embodiments of this disclosure have been described above. These descriptions are exemplary and not exhaustive, and are not limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen to best explain the principles, practical application, or technical improvements to the embodiments in the market, or to enable others skilled in the art to understand the embodiments disclosed herein. The scope of this disclosure is defined by the appended claims.

Claims

1. A flexible solar array, mounted on a satellite, characterized in that, The flexible solar panel includes: A storage box assembly includes a box body and a cover plate that opens and closes on the box body; a rotatable scroll is provided in the box body; A linkage assembly, wherein the opposite ends of the linkage assembly are respectively connected to the satellite and the housing, and is configured to drive the housing assembly to move in a direction away from the satellite to the working position; A sun blanket assembly is wound on the spool and configured to remain in a taut position when the cover is closed; the sun blanket assembly has a fixed end connected to the spool and a free end opposite to the fixed end; When the storage box assembly is in the working position and the cover is open, the free end of the sun blanket assembly can move away from the satellite under the driving action of the unfolding assembly, so that the sun blanket assembly moves to the unfolded posture.

2. The flexible solar array according to claim 1, characterized in that, It also includes a clamping release device disposed between the housing and the satellite, the clamping release device being configured to restrain the housing assembly in an initial position adjacent to the satellite; when the clamping release device is unlocked, the housing assembly moves to a working position in a direction away from the satellite.

3. The flexible solar array according to claim 2, characterized in that, At least one of the clamping release devices is disposed on the linkage assembly, which is configured to remain in a folded state under the action of the clamping release device; when the clamping release device is unlocked, the linkage assembly can switch from the folded state to the extended state to drive the storage box assembly to move away from the satellite to the working position.

4. The flexible solar array according to claim 1, characterized in that, It also includes an unlocking device disposed on the storage box assembly, wherein the cover is kept closed under the locking action of the unlocking device to press the sun blanket assembly into the box body; when the unlocking device is unlocked, the cover can be opened and the sun blanket assembly can be released.

5. The flexible solar array according to claim 4, characterized in that, The cover is configured to be rotatably connected to the box body via a spring hinge, and is configured to have a tendency to rotate toward the open position under the elastic force applied by the spring hinge. When the unlocking device is unlocked, the cover plate rotates relative to the box body under the elastic force of the spring hinge and remains in the open position.

6. The flexible solar array according to claim 1, characterized in that, The cover plate is provided with a first limiting member, and the scroll is provided with a second limiting member for cooperating with the first limiting member; when the cover plate is closed, the first limiting member and the second limiting member cooperate to restrict the rotational freedom of the scroll; when the cover plate is opened, the first limiting member disengages from the second limiting member.

7. The flexible solar array according to claim 6, characterized in that, The first limiting member includes two toothed racks disposed on the inner wall surface of the cover plate, the two toothed racks being located at opposite ends in the extending direction of the cover plate; The second limiting member includes two gears disposed at opposite ends of the spool, and the two gears are disposed in a one-to-one correspondence with the two racks; when the cover is closed, the racks mesh with the corresponding gears to restrict the rotational freedom of the spool.

8. The flexible solar array according to claim 1, characterized in that, The unfolding assembly includes a power unit for driving the unfolding of the sun blanket assembly, and a tensioning device connected between the free end and the power unit; At least when the sun blanket assembly is in the deployed position, the tensioning device is configured to continuously apply a tension force to the sun blanket assembly in a direction away from the satellite.

9. The flexible solar array according to claim 8, characterized in that, It also includes a damping device mounted on the reel, which is configured to apply rotational resistance to the reel during the process of the power unit driving the sun blanket assembly to unfold; The flexible solar array further includes a rotation drive device disposed between the linkage assembly and the satellite, and a swing drive device disposed on the housing; the rotation drive device has a first output axis, the swing drive device has a second output axis, the first output axis is perpendicular to the second output axis, and the second output axis is parallel to the extension axis of the reel; When the sun blanket assembly is in the unfolded position, the rotation drive device is configured to drive the flexible sun wings to rotate around the first output axis, and the swing drive device is configured to drive the sun blanket assembly to swing around the second output axis within a preset angle range via the housing.

10. A spacecraft, characterized in that, The satellite includes a flexible solar array according to any one of claims 1-9, wherein the flexible solar array is mounted on the satellite.

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