Solar wing device capable of being repeatedly unfolded and folded and star body

Abstract

The invention provides a solar wing device capable of being repeatedly unfolded and folded and a star body. The solar wing device comprises a battery array, an unfolding assembly and a driving assembly. The battery array is formed by splicing a plurality of battery panels including a first battery panel and a second battery panel, the first battery panel and the second battery panel are arranged at the two ends of the battery array respectively, and a flexible hinge assembly is arranged between every two adjacent battery panels; the unfolding assembly comprises an end part driving unit, a shear fork unit and a tail part rotating unit which are connected in sequence; the end driving unit is fixedly connected with the first cell panel, and the tail rotating unit is fixedly connected with the second cell panel; one end of the driving assembly is connected with the star body, and the other end is connected with the unfolding assembly for driving the unfolding assembly to unfold and fold. The solar wing device belongs to a stacked structure, the effect of high unfolding and folding ratio is achieved, efficient and low-energy-consumption unfolding of the space large-size multi-module solar wing mechanism is achieved, the unfolding process is stable and reliable, the driving efficiency is high, and unfolding disturbance is small.

Description

Technical Field

[0001] The present invention belongs to the technical field of spacecraft energy supply, and relates to a repeatedly deployable and retractable solar wing device and a star body. Background Art

[0002] The increasing complexity of space missions places higher demands on spacecraft energy supply. Traditional solar wing deployment and retraction mechanism designs often struggle to achieve an ideal balance between deployment and retraction ratio, structural weight, and thermal management capabilities. Especially for spacecraft that must frequently deploy and retract and adapt to extreme temperature fluctuations, designing solar wings that efficiently collect solar energy while adapting to the unique demands of the space environment has become a key to the development of current aerospace technology.

[0003] The primary function of a battery array is to provide energy for spacecraft. It consists of solar cells, a substrate, a locking mechanism for deployment, and a compression and release mechanism. Before the spacecraft enters orbit, the battery array is folded against the sidewall of the spacecraft using the compression mechanism. Once in orbit, the compression mechanism is released, allowing the battery array to deploy to the desired spatial position and state, continuously powering the spacecraft. In recent years, with the increasing number of human exploration activities and the growing variety of spacecraft, higher requirements have been placed on the battery array and its deployment and retraction mechanisms. Summary of the Invention

[0004] In order to overcome the defect of relatively small expansion and contraction of solar wing devices in the prior art, a repeatedly expandable and retractable solar wing device and star body are provided. The solar wing device has a stacked structure, which achieves a high expansion and contraction ratio by reducing the gap between the battery arrays after folding and reducing the thickness of a single fold. It also solves the problems of long force transmission path, low driving efficiency, and high driving power consumption of traditional rope-driven solar wing systems, and realizes efficient and low-energy deployment of large-scale multi-module solar wing mechanisms in space, with a smooth and reliable deployment process, high driving efficiency, and small deployment disturbance.

[0005] The present invention solves the above technical problems through the following technical solutions:

[0006] The present invention provides a repeatedly expandable and retractable solar wing device, which includes a battery array, an expansion assembly and a drive assembly; the battery array is composed of a plurality of battery panels including a first battery panel and a second battery panel, the first battery panel and the second battery panel are respectively arranged at the two ends of the battery array, and a flexible hinge assembly is provided between two adjacent battery panels, so that each of the battery panels can fold with each other in the folded state of the solar wing device; the expansion assembly includes an end drive unit, a scissors unit and a tail rotation unit connected in sequence; the end drive unit is fixedly connected to the first battery panel, and the tail rotation unit is fixedly connected to the second battery panel; one end of the drive assembly is connected to the star body, and the other end is connected to the expansion assembly, which is used to drive the expansion and retraction of the expansion assembly.

[0007] In the present invention, when the solar wing device changes from a folded state to an unfolded state, the end driving unit rotates, driving the scissors unit and the tail rotating unit to rotate, pulling the battery array to unfold; when the solar wing device changes from an unfolded state to a folded state, the end driving unit rotates, causing the scissors unit and the tail rotating unit to retract, and driving the battery panels in the battery array to retract and fold, and then the tail rotating unit rotates to drive the second battery panel to be stacked above or below the first battery panel.

[0008] In the present invention, the tail rotating unit in the unfolding assembly cooperates with the scissor unit and the end driving unit to perform the unfolding or folding action; during the folding process, the battery panels at both ends of the battery array cannot be stacked directly, and the first battery panel and the second battery panel need to be stacked after rotating in conjunction with the tail rotating unit.

[0009] In some embodiments, the scissor unit includes several pairs of scissor rods; adjacent scissor rods are connected by a rotary hinge.

[0010] Among them, when unfolded, each pair of scissors rods are in a crossed state; when changing from the unfolded state to the folded state, the scissors rods fold from an "X-shape" to a "S-shape"; when folded, each pair of scissors rods are in a vertically parallel structure or a nearly vertically parallel structure.

[0011] In some embodiments, a rotary hinge is provided between the end drive unit and the scissor unit.

[0012] In some embodiments, a rotary hinge is provided between the scissor unit and the tail rotating unit.

[0013] In a specific embodiment, the rotary hinge includes two hinge joints, a first rotating shaft, a pre-tightening nut, a bearing and a sleeve; the adjacent scissor rods are respectively inserted on different sides of the two hinge joints; the two hinge joints are arranged up and down along the same axis, and are both provided with a center hole; the first rotating shaft is arranged through the two center holes, and the upper and lower surfaces of each center hole are installed with the bearings, and the sleeve is used to axially position the two hinge joints in contact, one side of the first rotating shaft is in contact with the bearing, and the other side is connected by a pre-tightening nut, so that the two hinge joints form a secondary connection through rotation.

[0014] In the present invention, the material of the hinge joint may be aluminum alloy.

[0015] In the present invention, the number of the tail rotating unit and the end driving unit may be one; the end driving unit may be composed of two rods, and the tail rotating unit may be composed of two rods.

[0016] In a specific embodiment, the scissors rod comprises a carbon fiber rod.

[0017] In a specific embodiment, the number of the scissor-type rods is at least 3 pairs.

[0018] In one embodiment, the number of the scissor-type rods is 3 pairs.

[0019] In the present invention, two flexible hinge assemblies are provided between two adjacent solar panels, and the two flexible hinge assemblies are symmetrically arranged on both sides of the transverse center line of the solar panels.

[0020] Among them, when the solar wing device is unfolded, the flexible hinge components on the same side of the transverse center line of the solar panel are on the same straight line; when the solar wing device is folded, the flexible hinge components on the same side of the transverse center line of the solar panel are staggered with each other.

[0021] In some embodiments, the flexible hinge assembly includes a second rotating shaft, a spring leaf, and a torsion spring; the end of the second rotating shaft is arranged inside the torsion spring to achieve the torsion of the battery panel and the series connection between adjacent battery panels; the spring leaf is arranged between adjacent battery panels and is located on the second rotating shaft.

[0022] In the present invention, the elastic force of the spring sheet causes each solar panel to have a tendency to fold around the second rotation axis, thereby ensuring that each solar panel folds regularly during the folding process and also reducing the gap at the folding position.

[0023] In the present invention, the torsion spring has a function similar to that of the spring sheet, and generates a torsion force inside the torsion spring, thereby achieving the effect of causing each solar panel to have a folding tendency around the second rotation axis.

[0024] In some embodiments, the drive assembly includes a support end connector, a ball screw, a conductive element, a guide rail, a fixed end connector, a coupling and a motor reducer; wherein, the two ends of the ball screw are rotatably connected to the support end connector and the fixed end connector respectively; the fixed end connector is connected to the motor reducer through the coupling; the ball screw is connected to the guide rail through the conductive element, and the conductive element is also connected to the deployment assembly; the guide rail is arranged between the support end connector and the fixed end connector, and is arranged parallel to the ball screw.

[0025] In a specific embodiment, the number of the conductive elements is 2; the two conductive elements are arranged on both sides of the center line of the ball screw.

[0026] In the present invention, the rotation of the ball screw can drive the conducting element to move left and right.

[0027] In a specific embodiment, the ball screw is a birotational screw; a set of motor reducers can be used to enable the two conducting elements to move in opposite directions; wherein, the opposite direction means that one conducting element moves to the left and the other conducting element moves to the right, thereby driving the expansion device connected thereto to expand or retract.

[0028] In a specific embodiment, the conducting element includes a ball nut, a mounting seat and an embedded linear bearing; the ball nut is mounted on the ball screw through the mounting seat, and the ball nut is also connected to the end drive unit; the embedded linear bearing is fixedly connected to the mounting seat and is mounted on the guide rail.

[0029] In the present invention, the drive assembly adopts a ball screw and a slider formed by a mounting seat and a ball nut, and utilizes the self-locking feature of the nut transmission in the ball screw to ensure that the solar wing device can remain locked after being deployed into place.

[0030] In a preferred embodiment, the drive assembly further comprises a torsion spring, which is disposed on a rotating shaft inside the mounting seat to assist in initial deployment.

[0031] In the present invention, the provision of the torsion spring can prevent the rod in the end drive unit from being at a dead point during the deployment process, resulting in the problem of being unable to deploy or having a large initial deployment force.

[0032] In some embodiments, the solar wing device also includes a two-dimensional rotation component for adjusting the orientation of the battery array; the solar wing device is fixedly connected to the star body through the two-dimensional rotation component; the two-dimensional rotation component includes a horizontal rotation motor, a normal rotation motor, a horizontal rotation axis system and a normal rotation axis system; the output shaft of the horizontal rotation motor is connected to the horizontal rotation axis system, the output shaft of the normal rotation motor is connected to the normal rotation axis system, and the horizontal rotation axis system is fixedly connected to the normal rotation axis system.

[0033] In the present invention, the horizontal rotation of the horizontal rotating motor can drive the normal rotation and pull other devices to operate; therefore, the rotation of the horizontal rotating motor can drive the horizontal rotating shaft system, the normal rotating shaft system, the normal rotating motor and other components of the solar wing device connected to the output shaft of the normal shaft system. The normal rotating motor drives the long rotating shaft in the normal rotating shaft system to rotate, and the solar wing assembly on the output shaft is rotated circumferentially through two bevel gears to keep the front of the battery array in the solar wing device receiving sunlight at all times.

[0034] The present invention also provides a satellite comprising the solar wing device described above.

[0035] The present invention has the following beneficial effects:

[0036] 1. The deployment components of the repeatedly deployable solar wing device of the present invention are composed of multiple groups of scissor-type mechanisms, forming a multi-loop parallel mechanism, realizing single-point drive and multi-point synchronous linkage, solving the problems of long force transmission path, low drive efficiency, and high drive power consumption of traditional rope-driven solar wing systems, and realizing efficient and low-energy deployment of large-scale multi-module solar wing mechanisms in space, with a smooth and reliable deployment process, high drive efficiency, and small deployment disturbance.

[0037] 2. In the present invention, the flexible hinge structure connecting two adjacent solar panels is simple, which can reduce the folding gap.

[0038] 3. The cell array in the retractable solar wing device of the present invention can be composed of multiple single panels, stacked in a foldable manner, which reduces the bending and other performance requirements of the cell array itself. Due to the difficulty in manufacturing flexible solar panels, stacked solar panels composed of multiple small-area single panels are easier to manufacture. The cell array has a larger adjustable area, that is, multiple panels of different areas can be assembled in the solar wing device through splicing.

[0039] 4. The retractable solar wing device of the present invention is a large lightweight structure. Its folding method is to directly stack adjacent panels to achieve a high folding ratio. Compared with the scroll-type stacking method, the thickness of the folded panels of the same area is smaller, and the degree of folding is correspondingly higher. Specifically, the surface density of the folded device is less than 0.8kg / m 2 , much smaller than the scroll-type unfolding device. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 A front view of the retractable solar wing device in a retracted state;

[0041] Figure 2 A top view of the retractable solar wing device in a retracted state;

[0042] Figure 3 A schematic diagram of the structure of a retractable solar wing device in an unfolded state;

[0043] Figure 4 Schematic diagram of the flexible hinge structure in the solar wing device;

[0044] Figure 5 It is a schematic diagram of the structure of the drive assembly in the solar wing device;

[0045] Figure 6 This is a partial enlarged structural diagram of the drive assembly in the solar wing device;

[0046] Figure 7 This is a schematic diagram of the structure of a complete scissor mechanism in a solar wing device;

[0047] Figure 8 It is a schematic structural diagram of the deployment end rotation unit in the solar wing device;

[0048] Figure 9 A schematic diagram of the structure of the hinge at the connection of the scissor mechanism in the solar wing device;

[0049] Figure 10 It is a schematic diagram of the structure of the two-dimensional rotating component in the solar wing device;

[0050] Description of reference numerals:

[0051] 1. Deployment assembly; 2. Flexible hinge assembly; 2.1. Second rotating shaft; 2.2. Spring leaf; 2.3. Torsion spring; 3. Battery array; 4. Drive assembly; 4.1. Support end connector; 4.2. Ball screw; 4.3. Ball screw nut, 4.4. Mounting seat; 4.5. Embedded linear bearing; 4.6. Guide rail; 4.7. Fixed end connector; 4.8. Coupling; 4.9. Motor reducer; 4.10. Torsion spring; 5. Rotary hinge; 5.1. Scissor rod; 5.2. Aluminum alloy hinge joint; 5.3. First rotating shaft; 5.4. Pre-tightening nut; 5.5. Bearing; 5.6. Bushing; 6. Two-dimensional rotation assembly; 6.1. Horizontal rotation motor; 6.2. Normal rotation motor; 7. Horizontal rotation axis system; 8. Normal rotation axis system. DETAILED DESCRIPTION

[0052] The present invention will be described below with reference to the accompanying drawings and specific embodiments.

[0053] An embodiment of the present invention provides a large, lightweight, and retractable solar wing device.

[0054] Figure 1 This is a front view of the retractable solar wing device of the present invention in the retracted state. Figure 1 As shown, the solar wing device includes an unfolding component 1, a flexible hinge component 2, a battery array component 3, a driving component 4 and a two-dimensional rotation component 6.

[0055] Figure 2 FIG1 is a top view of the retractable solar wing device of the present invention in the retracted state. Figure 2 As mentioned above, the solar wing device also includes a rotating hinge 5.

[0056] Figure 3 The figure is a schematic diagram of the unfolded structure of the solar wing device that can be repeatedly unfolded and retracted according to the present invention. Figure 3As shown, the solar wing device includes an unfolding assembly 1 consisting of an end drive unit, a scissors unit, and a tail rotation unit. The two ends of the unfolding assembly 1 are connected to the two ends of the battery array 3 up and down, driving the battery array 3 to unfold or fold; each battery panel is connected by a flexible hinge 2, and there is a drive assembly 4 on the side of the unfolding assembly 1 close to the star. The drive assembly 4 adopts a screw and nut mechanism. The entire solar wing mechanism is fixed to the star through a two-dimensional rotation assembly 6. The two-dimensional rotation assembly 6 can adjust the direction of the battery array so that it is directly exposed to sunlight. Figure 7 This is a schematic structural diagram of a complete scissor mechanism in the retractable solar wing device of the present invention; Figure 8 This is a schematic structural diagram of the deployment end rotation unit in the repeatedly deployable solar wing device of the present invention.

[0057] Figure 4 Figure 2 is a schematic diagram of the flexible hinge structure in the solar wing device. Figure 4 As shown, the flexible hinge assembly 2 between two connected battery panels consists of a rotating shaft 2-1, a spring sheet 2-2 and a torsion spring 2-3. The end of the rotating shaft 2-1 is arranged inside the rotating spring 2-3 to achieve the torsion of the battery panel and the series connection between adjacent battery panels; the spring sheet 2-2 is arranged between adjacent battery panels 2-4. The elastic force of the spring sheet 2-2 will cause the battery array to have a tendency to fold around the rotating shaft 2-1, ensuring that the battery array folds regularly when it is folded, and can also fold with gaps.

[0058] Figure 5 This is a schematic diagram of the structure of the drive assembly in the solar wing device. Figure 6 This is a partial enlarged structural diagram of the drive component in the solar wing device. Figure 5 and Figure 6As shown, the drive assembly 4 includes a support end connector 4-1, a ball screw 4-2, a ball nut 4-3, a mounting seat 4-4, an embedded linear bearing 4-5, a guide rail 4-6, a fixed end connector 4-7, a coupling 4-8, a motor reducer 4-9, and a torsion spring 4-10. The two ends of the two guide rails 4-6 are respectively fixedly connected to the support end connector 4-1 on the left and the fixed end connector 4-7 on the right. The two ends of the ball screw 4-2 are rotationally connected to the two end connectors. The right end of the ball screw 4-2 is connected to the motor reducer 4-9 via the coupling 4-8. The embedded linear bearing 4-5 is sleeved on the guide rail 4-6 and can slide along the guide rail. The screw adopts a dual-rotation screw, and a single motor reducer can be used to complete the movement of the two nuts in opposite directions. The ball nut 4-3 fits over the ball screw 4-2 and is fixedly connected to the embedded linear bearing 4-5. Rotation of the ball screw 4-2 moves the ball nut 4-3 left and right. The two rods of the end drive unit are connected at their ends to the mounting base 4-4, which is fixedly connected to the embedded linear guide 4-5. A torsion spring 4-10 is installed at the rotating shaft to assist in initial deployment, preventing the folding rod from being unable to deploy due to a dead point or excessive initial deployment force.

[0059] Figure 9 The diagram below is a schematic diagram of the hinge structure at the scissor-fork connection of the solar wing device. Figure 9 As shown, the hinge at the rotating connection of the scissor mechanism of the deployment assembly 1 includes a scissor rod 5-1, an aluminum alloy hinge joint 5-2, a rotating shaft 5-3, a preload nut 5-4, a bearing 5-5, and a bushing 5-6. The carbon fiber rod 5-1 is fixedly connected to the aluminum alloy hinge joint 5-2. The rotating shaft 5-3 passes through the center hole of the joint. Bearings 5-5 are mounted on the upper and lower surfaces of the center hole of the aluminum alloy hinge joint 5-2. The two joints are axially positioned and contacted by bushings 5-6. One side of the rotating shaft 5-3 rests on the bearing, while the other side is connected by a preload nut 5-4, connecting the two joints together through a rotating pair.

[0060] Figure 10 This is a schematic diagram of the structure of the two-dimensional rotating component in the solar wing device. Figure 10 As shown, the two-dimensional rotation assembly 6 includes a horizontal rotation motor 6-1, a normal rotation motor 6-2, a horizontal rotation shaft system 7, and a normal rotation shaft system 8. The output shaft of the horizontal rotation motor 6-1 is connected to the horizontal rotation shaft system 7, while the normal rotation motor 6-2 is connected to the normal rotation shaft system 8. The horizontal rotation shaft system 7 is fixedly connected to the normal rotation shaft system 8. Rotation of the horizontal rotation motor 6-1 drives all solar wing assemblies connected to the horizontal rotation shaft system 7, the normal rotation shaft system 8, the normal rotation motor 6-2, and the output shaft of the normal rotation shaft system. The normal rotation motor 6-2 drives the long shaft in the normal rotation shaft system 8 to rotate. Through two bevel gears, the solar wing assemblies on the output shaft rotate circumferentially, ensuring that the front of the solar wing is always exposed to sunlight.

[0061] Example 1

[0062] This embodiment provides a solar wing device and a star body that can be repeatedly extended and retracted.

[0063] like Figure 1 and 2 As shown, the solar wing device comprises a battery array (3), an unfolding assembly (1), a driving assembly (4) and a rotating hinge (5); the battery array (3) is formed by splicing a plurality of battery panels including a first battery panel and a second battery panel, the first battery panel and the second battery panel are respectively arranged at two ends of the battery array (3), and a flexible hinge assembly (2) is provided between two adjacent battery panels, so that the battery panels can be folded relative to each other when the solar wing device is in a folded state; the unfolding assembly (1) comprises an end driving unit, a scissor unit and a tail rotating unit connected in sequence; the end driving unit is fixedly connected to the first battery panel, and the tail rotating unit is fixedly connected to the second battery panel; one end of the driving assembly (4) is connected to the star body, and the other end is connected to the unfolding assembly (1), and is used to drive the unfolding assembly (1) to unfold and retract.

[0064] like Figure 3 、 7 As shown in FIG8 , the scissor unit includes three pairs of carbon fiber scissor rods (5-1); adjacent scissor rods (5-1) are connected by a rotary hinge (5); a rotary hinge (5) is provided between the end drive unit and the scissor unit; and a rotary hinge (5) is provided between the scissor unit and the tail rotary unit.

[0065] like Figure 9 As shown, the rotary hinge (5) includes two hinge joints (5-2), a first rotating shaft (5-3), a pre-tightening nut (5-4), a bearing (5-5) and a sleeve (5-6); adjacent scissor rods (5-1) are respectively inserted on different sides of the two hinge joints (5-2); the two hinge joints (5-2) are arranged up and down along the same axis and are both provided with a center hole; the first rotating shaft (5-3) is arranged through the two center holes, and the upper and lower surfaces of each center hole are both installed with bearings (5-5); the sleeve is used to axially position the two hinge joints (5-2) in contact, one side of the first rotating shaft (5-3) is in contact with the bearing, and the other side is connected through the pre-tightening nut (5-4), so that the two hinge joints form a secondary connection through rotation.

[0066] like Figure 4 As shown, the flexible hinge assembly (2) includes a second rotating shaft (2-1), a spring sheet (2-2) and a torsion spring (2-3); the second rotating shaft (2-1) is arranged between adjacent battery panels, the torsion spring (2-3) is arranged on the second rotating shaft (2-1), and the spring sheet (2-2) is arranged between adjacent battery panels and is located on the second rotating shaft (2-1).

[0067] like Figure 5 As shown, the drive assembly (4) includes a supporting end connection member (4-1), a ball screw (4-2), a conductive element, a guide rail (4-6), a fixed end connection member (4-7), a coupling (4-8) and a motor reducer (4-9); wherein, the two ends of the ball screw (4-2) are rotatably connected to the supporting end connection member (4-1) and the fixed end connection member (4-7) respectively; the fixed end connection member (4-7) is connected to the motor reducer (4-9) through the coupling (4-8); the ball screw (4-2) is connected to the guide rail (4-6) through the conductive element, and the conductive element is also connected to the expansion assembly; the guide rail (4-6) is arranged between the supporting end connection member (4-1) and the fixed end connection member (4-7), and is arranged parallel to the ball screw.

[0068] The number of conducting elements is two; the two conducting elements are respectively arranged on both sides of the center line of the ball screw (4-2); the ball screw is a birotational screw; the conducting elements include a ball screw nut (4-3), a mounting seat (4-4) and an embedded linear bearing (4-5); the ball screw nut (4-3) is sleeved on the ball screw (4-2) through the mounting seat (4-4), and the ball screw nut (4-3) is also connected to the end drive unit; the embedded linear bearing (4-5) is fixedly connected to the mounting seat (4-4) and sleeved on the guide rail (4-6). The drive assembly (4) also includes a torsion spring (4-10), which is arranged on the rotating shaft inside the mounting seat (4-4) to assist initial deployment.

[0069] like Figure 10 As shown, the solar wing device further includes a two-dimensional rotation component (6) for adjusting the orientation of the battery array (3); the solar wing device is fixedly connected to the star through the two-dimensional rotation component (6); the two-dimensional rotation component (6) includes a horizontal rotation motor (6-1), a normal rotation motor (6-2), a horizontal rotation shaft system (7) and a normal rotation shaft system (8); the output shaft of the horizontal rotation motor (6-1) is connected to the horizontal rotation shaft system (7), the output shaft of the normal rotation motor (6-2) is connected to the normal rotation shaft system (8), and the horizontal rotation shaft system (7) is fixedly connected to the normal rotation shaft system (8).

[0070] The satellite body of this embodiment includes the repeatedly extendable and retractable solar wing device as described above.

[0071] The working process of the solar wing device in this embodiment is as follows:

[0072] The solar wing deployment process is as follows: After the mechanism is unlocked, the drive assembly 4 activates, the motor reducer 4-9 is powered on, and this, through the coupling 4-8, drives the ball screw 4-2. Because the ball screw 4-2 is a dual-rotation screw, the two ball nuts 4-5 at each end of the ball screw 4-2 are guided toward the center by the guide rail 4-6, causing the deployment assembly 1, which consists of a scissor-type mechanism, to unfold. Once fully deployed, the motor reducer 4-9 stops rotating. The self-locking action of the screw nut maintains the stability of the structure. The battery array 3, connected to the ends of the deployment assembly 1 at both ends, unfolds with the scissor-type mechanism. The two-dimensional rotation assembly adjusts the direction of the solar wing to ensure direct sunlight on the array. Motor 1 drives the horizontal rotation shaft system through the coupling to achieve a horizontal rotation of ±60°. Motor 2, connected to the horizontal shaft, drives two bevel gears to rotate the normal rotation shaft system 360°. This enables the drive assembly and deployment assembly mounted thereon to rotate in both the horizontal and normal directions. The device solves the problems of long force transmission path, low driving efficiency and high driving power consumption in traditional rope-driven solar wing systems, and realizes the efficient and low-energy deployment of large-scale multi-module solar wing mechanisms. The deployment process is smooth and reliable, the driving efficiency is high, and the deployment disturbance is small.

[0073] This mechanism has a repetitive expansion and contraction function. When retracting, the motor reducer in the drive assembly 4 reverses, separating the two mounting bases 4-4 from each other, and the scissor mechanism in the deployment assembly 1 retracts. The battery array 3 is assisted by the spring sheet 2-2 to retract, providing a certain amount of retraction force and ensuring the orderly retraction of the battery array. The retraction method of this device is to directly stack adjacent battery panels to achieve a high expansion and retraction ratio. After retraction, the surface density of the device is less than 0.8kg / m 2 , much smaller than the scroll-type unfolding device.

[0074] The above description is merely a preferred embodiment of the present invention and does not constitute any form of limitation to the present invention. Although the present invention has been disclosed as a preferred embodiment as above, it is not intended to limit the present invention. Any technician familiar with the present profession can make some changes or modifications to equivalent embodiments of equivalent changes using the technical content disclosed above without departing from the scope of the technical solution of the present invention. However, any simple modification, equivalent replacement and improvement of the above embodiments made according to the technical essence of the present invention, within the spirit and principles of the present invention, without departing from the content of the technical solution of the present invention, shall still fall within the scope of protection of the technical solution of the present invention.

Claims

1. A solar wing device that can be repeatedly extended and retracted, characterized in that: It includes a battery array (3), an expansion component (1) and a driving component (4); The battery array (3) is formed by splicing a plurality of battery panels including a first battery panel and a second battery panel, wherein the first battery panel and the second battery panel are respectively arranged at two ends of the battery array (3), and a flexible hinge assembly (2) is provided between two adjacent battery panels so that the battery panels can be folded relative to each other when the solar wing device is in a folded state; The deployment assembly (1) comprises an end drive unit, a scissor unit and a tail rotation unit connected in sequence; the end drive unit is fixedly connected to the first battery panel, and the tail rotation unit is fixedly connected to the second battery panel; One end of the driving component (4) is connected to the star body, and the other end is connected to the unfolding component (1), and is used to drive the unfolding component (1) to unfold and retract.

2. The solar wing device according to claim 1, wherein: The expansion component (1) satisfies at least one of the following conditions: ① The scissor-fork unit comprises a plurality of pairs of scissor-fork rods (5-1); adjacent scissor-fork rods (5-1) are connected via a rotary hinge (5); ② A rotary hinge (5) is provided between the end drive unit and the scissor unit; ③ A rotary hinge (5) is provided between the scissor unit and the tail rotating unit.

3. The solar wing device according to claim 2, wherein: The rotary hinge (5) comprises two hinge joints (5-2), a first rotating shaft (5-3), a pre-tightening nut (5-4), a bearing (5-5) and a shaft sleeve (5-6); The adjacent scissor rods (5-1) are respectively inserted on different sides of the two hinge joints; The two hinge joints (5-2) are arranged vertically along the same axis and are both provided with a center hole; the first rotating shaft (5-3) is arranged through the two center holes, and the upper and lower surfaces of each center hole are both installed with the bearing (5-5); the shaft sleeve is used to axially position and contact the two hinge joints (5-2); one side of the first rotating shaft (5-3) is in contact with the bearing, and the other side is connected via a pre-tightening nut (5-4), so that the two hinge joints form a secondary connection through rotation.

4. The solar wing device according to claim 2, wherein: The scissor-type rod (5-1) satisfies at least one of the following conditions: ① The scissor rods include carbon fiber rods; ② The number of the scissor-type rods is at least 3 pairs.

5. The solar wing device according to claim 1, wherein: The flexible hinge assembly (2) comprises a second rotating shaft (2-1), a spring sheet (2-2) and a torsion spring (2-3); The end of the second rotating shaft (2-1) is arranged inside the torsion spring (2-3) and is used to realize the torsion of the solar panel and the series connection between adjacent solar panels; The spring sheet (2-2) is arranged between adjacent battery panels and is located on the second rotating shaft (2-1).

6. The solar wing device according to claim 1, wherein: The driving assembly (4) comprises a supporting end connecting piece (4-1), a ball screw (4-2), a conducting element, a guide rail (4-6), a fixed end connecting piece (4-7), a coupling (4-8) and a motor reducer (4-9); wherein, The two ends of the ball screw (4-2) are rotatably connected to the support end connection piece (4-1) and the fixed end connection piece (4-7) respectively; the fixed end connection piece (4-7) is connected to the motor reducer (4-9) via the coupling (4-8); The ball screw (4-2) is connected to the guide rail (4-6) via the conductive element, and the conductive element is also connected to the deployment assembly (1); The guide rail (4-6) is arranged between the support end connecting piece (4-1) and the fixed end connecting piece (4-7), and is arranged parallel to the ball screw.

7. The solar wing device according to claim 6, characterized in that: The drive assembly (4) satisfies at least one of the following conditions: ① The number of the conductive elements is 2; the two conductive elements are arranged on both sides of the center line of the ball screw (4-2); ② The ball screw is a double-rotation screw; ③ The conducting element comprises a ball screw nut (4-3), a mounting seat (4-4) and an embedded linear bearing (4-5); the ball screw nut (4-3) is sleeved on the ball screw (4-2) through the mounting seat (4-4), and the ball screw nut (4-3) is also connected to the end drive unit; the embedded linear bearing (4-5) is fixedly connected to the mounting seat (4-4) and sleeved on the guide rail (4-6).

8. The solar wing device according to claim 7, characterized in that: The driving assembly (4) further comprises a torsion spring (4-10), which is arranged on a rotating shaft inside the mounting seat (4-4) and is used to assist initial deployment.

9. The solar wing device according to claim 1, wherein: The solar wing device further comprises a two-dimensional rotating assembly (6) for adjusting the orientation of the battery array (3); the solar wing device is fixedly connected to the star body via the two-dimensional rotating assembly (6); The two-dimensional rotation assembly (6) comprises a horizontal rotation motor (6-1), a normal rotation motor (6-2), a horizontal rotation shaft system (7) and a normal rotation shaft system (8); the output shaft of the horizontal rotation motor (6-1) is connected to the horizontal rotation shaft system (7), the output shaft of the normal rotation motor (6-2) is connected to the normal rotation shaft system (8), and the horizontal rotation shaft system (7) is fixedly connected to the normal rotation shaft system (8).

10. A celestial body, characterized in that: It comprises the solar wing device according to any one of claims 1 to 9.

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