An expandable solar wing configuration based on a cable-driven parallel sun-pointing orientation device

Abstract

The application discloses an expandable solar wing configuration based on a cable drive parallel sun-orienting device, relates to the technical field of a large-scale expandable thin-film solar wing in space and application thereof, and embeds the cable drive parallel sun-orienting device in a pod pole folding and unfolding device, and installs a flexible solar wing film in the pod pole folding and unfolding device, so that the cable drive parallel sun-orienting device, the pod pole folding and unfolding device and the flexible solar wing film are integrated, and the high folding ratio of the expandable flexible solar wing structure is ensured, the envelope size of the overall structure of the device is reduced, and the occupied space of the whole device is reduced.

Description

Technical Field

[0001] This invention relates to the field of large-scale deployable thin-film solar arrays and their applications, and in particular to a deployable solar array configuration based on a cable-driven parallel solar orientation device. Background Technology

[0002] Solar arrays, as the most common energy supply devices, are widely used in modern spacecraft. High convergence ratios, low areal density, and ultra-high power output are the development directions for next-generation solar arrays. Their main structure can be divided into two parts: solar array surfaces and solar orientation devices. Current research focuses on flexible solar arrays, including foldable flexible solar arrays, roll-up flexible solar arrays, and circular array solar arrays; and solar orientation devices, including single-degree-of-freedom and dual-degree-of-freedom solar orientation devices. Foldable flexible solar arrays are folded before the spacecraft enters its designated working orbit. Once in orbit, the deployment mechanism drives the flexible solar arrays to unfold, and the solar orientation device adjusts the angle of the solar array surfaces to ensure solar orientation, thus providing energy to the spacecraft.

[0003] Currently widely used flexible solar panels can be composed of laminated glass fiber or carbon fiber composite materials and Kapton / polyimide films. Foldable flexible solar panels unfold like an accordion, resembling an ancient memorial; roll-up flexible solar panels are rolled up on a cylinder during launch and fully extended by a deployment mechanism during operation; circular array flexible solar panels adopt a structure similar to an antenna reflector, with multiple arrays unfolding in a circular pattern around a hub-shaped support structure. The stability and reliability of the mechanical structure of the solar orientation device directly affect the overall performance and operational safety of the spacecraft. Currently, the commonly used method is single-degree-of-freedom solar orientation, which is simple to control and relatively mature in technology. However, because single-degree-of-freedom drive can only adjust the attitude of the solar panels within a certain range, it cannot achieve complete alignment with sunlight, resulting in relatively low solar energy reception efficiency. Furthermore, facing the complex and ever-changing space environment, single-degree-of-freedom drive has poor adaptability and struggles to adjust the solar panels in real time to maximize solar energy reception. The dual-degree-of-freedom (DOF) solar orientation device achieves precise alignment with sunlight through adjustments of two mutually perpendicular degrees of freedom, ensuring that the solar panels always face the sun, thus significantly improving solar energy reception efficiency. However, because the dual-DOF solar orientation device requires more mechanical components and a control system to achieve the adjustment of the two degrees of freedom, its structure is relatively complex, and its manufacturing and maintenance costs are also higher. After integrating the flexible solar panel deployment and retraction device with the solar orientation device, the size of the solar orientation device cannot be changed, and it will occupy a large space, failing to meet the high retraction ratio characteristic of current flexible solar panels. Summary of the Invention

[0004] In order to overcome the problem that the size of the solar orientation device cannot be changed after the flexible solar wing deployment and retraction device and the solar orientation device are integrated, and the solar orientation device occupies a large space, which cannot meet the high folding ratio of the current flexible solar wing, the present invention aims to provide a deployable solar wing configuration based on a cable-driven parallel solar orientation device that can achieve a high folding ratio of the overall deployable flexible solar wing device.

[0005] To address the aforementioned technical problems, this invention provides a deployable solar array configuration based on a cable-driven parallel solar orientation device, comprising a cable-driven parallel solar orientation device, a pod-shaped extension and retraction device, and a flexible solar array film. The cable-driven parallel solar orientation device is embedded within the pod-shaped extension and retraction device, and the flexible solar array film is mounted on the pod-shaped extension and retraction device.

[0006] Preferably, the pod stalk winding and unwinding device includes a pod stalk, a drum, a hollow direct drive motor, and a pod stalk winding and unwinding mechanism. One end of the pod stalk near the drum is bonded to the side of the drum. The stator end of the hollow direct drive motor is fixedly installed on the pod stalk winding and unwinding mechanism, and the rotor end of the hollow direct drive motor is fixedly installed on the bottom surface of the drum.

[0007] Preferably, the cable-driven parallel sun-orientation device includes a housing, a telescopic support rod, a cable-driven motor, a support rod fixing clamp, a rope, and a hinge ball. The housing is mounted to the pod-shaped rod extension / retraction device by fixing bolts. The cable-driven motor is mounted on the bottom surface of the housing. The hinge ball is mounted in the middle of the top surface of the spacecraft connection plate. The bottom of the telescopic support rod is mounted inside the hinge ball. The telescopic support rod is fixed to the bottom surface of the housing by the support rod fixing clamp. One end of the rope is connected to the cable-driven motor, and the other end is connected to the spacecraft connection plate.

[0008] Preferably, the outer shell is embedded inside the drum, the number of cable drive motors is three and they are evenly distributed on the bottom surface of the outer shell, and the telescopic support rod is a three-section telescopic rod that retracts inside the hollow direct drive motor.

[0009] Preferably, the flexible solar panel film is an isosceles right triangle, the apex of the flexible solar panel film is bonded to the side of the pod rod retracting mechanism, and a cable is connected to the base of the flexible solar panel film. The end of the cable away from the flexible solar panel film is connected to the end of the pod rod away from the roll.

[0010] Preferably, the pod stalk winding mechanism includes an upper carbon plate, a lower carbon plate, a large guide wheel, a small guide wheel, a tension wheel, a tension arm, a tension spring, and a support column. The support column is fixed between the upper carbon plate and the lower carbon plate. The pod stalk is guided between the large guide wheel and the small guide wheel. The tension wheel is connected to one end of the tension arm near the drum. One end of the tension spring is connected to the support column, and the other end is connected to the first bolt of the tension arm.

[0011] Preferably, the tensioning arm consists of an upper connecting rod and a lower connecting rod, and the tensioning arm is fixed to the connection between the upper connecting rod and the lower connecting rod by a copper pillar.

[0012] Preferably, the tensioning wheel is a hollow cylindrical rubber column, and the tensioning wheel is fixed to the lower connecting rod of the tensioning arm by a first bearing.

[0013] Preferably, the large guide wheel is a hollow cylindrical rubber column, which is sleeved on the second bearing. The stator of the second bearing is sleeved on the second bolt between the upper carbon plate and the lower carbon plate. The small guide wheel is a hollow cylindrical rubber column, which is sleeved on the third bearing. The stator of the third bearing is sleeved on the third bolt between the upper carbon plate and the lower carbon plate.

[0014] Preferably, the flexible solar panel film is folded in a Miura folding manner.

[0015] Beneficial effects

[0016] This invention integrates the cable-driven parallel sun orientation device, the pod-shaped rod retraction device, and the flexible solar wing film into a single unit by embedding the cable-driven parallel sun orientation device within the pod-shaped rod retraction device and installing the flexible solar wing film within the pod-shaped rod retraction device. This ensures a high retraction ratio for the deployable flexible solar wing structure, reduces the overall envelope size of the device, and minimizes the space occupied by the entire device.

[0017] This invention employs a hollow direct-drive motor, with the telescopic support rod of the cable-driven parallel sun-aligning device extending into the hollow direct-drive motor. Simultaneously, the cable-driven parallel sun-aligning device is integrated entirely into the drum. This not only increases the telescopic range of the support rod and the adjustment range of the sun-aligning device, but also reduces the longitudinal dimension of the solar array when folded.

[0018] This invention uses a cable-driven method for adjusting solar orientation. It employs a 3-RPS parallel platform to drive the motion platform through multiple rope traction. The angle range of the motion platform (i.e., the solar wing surface) is adjusted by changing the rope length. The control theory is mature and can achieve precise solar orientation.

[0019] In this invention, when the flexible solar wing film is deployed, the flexible solar wing film and the pod rod are connected by cables. The centrally symmetrical pod rod ensures that both sides of the pod rod are subjected to tension from the cables when it is extended. Both right-angled sides of the flexible solar wing film are stretched and shaped. The overall structure can ensure force balance and maintain the surface stiffness of the entire solar wing surface.

[0020] In this invention, the area of ​​the flexible solar panel film can be changed according to the length of the pod stem. When the overall length of the pod stem increases, the two right-angled sides of the flexible solar panel film can be increased accordingly to meet the requirements of the ultra-large size of the flexible solar panel. Moreover, when the solar panel is not in operation, the pod stem is flattened and wound on the roll, which can meet the requirements of the high storage ratio of the flexible solar panel. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the deployed solar array configuration based on the cable-driven parallel solar orientation device in this invention in its deployed state.

[0023] Figure 2 This is a schematic diagram of the retracted state of the deployable solar array configuration based on the cable-driven parallel solar orientation device in this invention;

[0024] Figure 3 This is a cross-sectional view of the cable-driven parallel solar orientation device based on the deployable solar wing configuration of the cable-driven parallel solar orientation device in this invention;

[0025] Figure 4 This is a schematic diagram of the pod-shaped extension and retraction device of the deployable solar array based on the cable-driven parallel solar orientation device in this invention.

[0026] Figure 5 This is a schematic diagram of the internal structure of the pod-shaped retractable device of the deployable solar array configuration based on the cable-driven parallel solar orientation device in this invention.

[0027] Figure 6 This is a cross-sectional view of the tensioning arm of the pod-shaped extension and retraction device of the deployable solar array configuration based on the cable-driven parallel solar orientation device in this invention;

[0028] Figure 7 This is a schematic diagram showing the connection between a single flexible solar wing film and a pod rod in the deployable solar wing configuration of the cable-driven parallel solar orientation device of the present invention.

[0029] Figure reference numerals: 1. Solar orientation device; 11. Outer shell; 12. Fixing bolt; 13. Telescopic support rod; 14. Cable drive motor; 15. Support rod fixing clamp; 16. Rope; 17. Hinge ball; 18. Spacecraft connection plate; 2. Pod rod deployment / retraction device; 21. Pod rod; 22. Drum; 23. Hollow direct drive motor; 24. Pod rod deployment / retraction mechanism; 241. Upper carbon plate; 242. Lower carbon plate; 243. Large guide wheel; 2431. Second bearing; 244. Small guide wheel; 2441. Third bearing; 245. Tensioning wheel; 2451. First bearing; 246. Tensioning arm; 2461. First bolt; 2462. Copper column; 247. Tension spring; 248. Support column; 3. Flexible solar panel film; 31. Cable. Detailed Implementation

[0030] To further understand the content of this invention, the invention will be described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the embodiments are merely illustrative and not limiting of the invention.

[0031] Example 1

[0032] A deployable solar array configuration based on a cable-driven parallel sun-orienting device, such as Figure 1-7 As shown, it includes a cable-driven parallel sun-orienting device 1, a pod-shaped stalk retraction and extension device 2, and a flexible solar wing film 3. The cable-driven parallel sun-orienting device 1 is embedded in the pod-shaped stalk retraction and extension device 2, and the flexible solar wing film 3 is installed on the pod-shaped stalk retraction and extension device 2.

[0033] The bean pod stalk winding and unwinding device 2 includes a bean pod stalk 21, a drum 22, a hollow direct drive motor 23, and a bean pod stalk winding and unwinding mechanism 24. One end of the bean pod stalk 21 near the drum 22 is bonded to the side of the drum 22. The stator end of the hollow direct drive motor 23 is fixedly installed on the bean pod stalk winding and unwinding mechanism 24, and the rotor end of the hollow direct drive motor 23 is fixedly installed on the bottom surface of the drum 22.

[0034] The cable-driven parallel sun-oriented device 1 includes a housing 11, a telescopic support rod 13, a cable-driven motor 14, a support rod fixing clamp 15, a rope 16, and a hinge ball 17. The housing 11 is installed on the pod rod extension / retraction device 2 by fixing bolts 12. The cable-driven motor 14 is installed on the bottom surface of the housing 11. The hinge ball 17 is installed in the middle of the top surface of the spacecraft connection plate 18. The bottom of the telescopic support rod 13 is installed inside the hinge ball 17. The telescopic support rod 13 is fixed on the bottom surface of the housing 11 by the support rod fixing clamp 15. One end of the rope 16 is connected to the cable-driven motor 14, and the other end is connected to the spacecraft connection plate 18.

[0035] The outer shell 11 is embedded inside the drum 22. There are three cable drive motors 14, which are evenly distributed on the bottom surface of the outer shell 11. The telescopic support rod 13 is a three-section telescopic rod that retracts inside the hollow direct drive motor 23.

[0036] Furthermore, the diameter of the cylindrical portion of the outer casing 11 should be smaller than the inner diameter of the drum 22 to ensure that the outer casing 11 can be placed inside the drum 22, thereby reducing the overall envelope thickness of the device.

[0037] Furthermore, the inner diameter of the hollow direct drive motor 23 is larger than the diameter of the last section of the telescopic support rod 13, allowing the last section of the telescopic support rod 13 to be stored inside the hollow direct drive motor 23, further reducing the longitudinal dimension of the overall device after folding.

[0038] The flexible solar panel film 3 is an isosceles right triangle. The apex of the flexible solar panel film 3 is bonded to the side of the pod stalk retracting mechanism 24. A cable 31 is connected to the base of the flexible solar panel film 3. The end of the cable 31 away from the flexible solar panel film 3 is connected to the end of the pod stalk 21 away from the roll 22.

[0039] The bean pod stalk retraction mechanism 24 includes an upper carbon plate 241, a lower carbon plate 242, a large guide wheel 243, a small guide wheel 244, a tension wheel 245, a tension arm 246, a tension spring 247, and a support column 248. The support column 248 is fixed between the upper carbon plate 241 and the lower carbon plate 242. The bean pod stalk 21 is guided between the large guide wheel 243 and the small guide wheel 244. The tension wheel 245 is connected to one end of the tension arm 246 near the drum 22. One end of the tension spring 247 is connected to the support column 248, and the other end is connected to the first bolt 2461 of the tension arm 246.

[0040] The tensioning arm 246 consists of an upper connecting rod and a lower connecting rod, and the tensioning arm 246 is fixed at the connection between the upper connecting rod and the lower connecting rod by a copper pillar 2462.

[0041] The tensioning wheel 245 is a hollow cylindrical rubber column, and the tensioning wheel 245 is fixed to the lower connecting rod of the tensioning arm 246 by the first bearing 2451.

[0042] The large guide wheel 243 is a hollow cylindrical rubber column, which is fitted onto the second bearing 2431. The stator of the second bearing 2431 is fitted onto the second bolt between the upper carbon plate 241 and the lower carbon plate 242. The small guide wheel 244 is a hollow cylindrical rubber column, which is fitted onto the third bearing 2441. The stator of the third bearing 2441 is fitted onto the third bolt between the upper carbon plate 241 and the lower carbon plate 242.

[0043] The flexible solar panel film 3 is folded in the form of a Miura fold.

[0044] Working principle: When the device starts to unfold, the hollow direct drive motor 23 starts to rotate, which in turn drives the drum 22 to rotate, causing the pod rod 21 to extend outward along the gap between the large guide wheel 243 and the small guide wheel 244. At the same time, it also causes the flexible solar wing film 3 to slowly unfold. After the entire device is fully unfolded, the angle of the unfolded flexible solar wing film 3 facing the sun is adjusted according to the actual situation. By activating the telescopic support rod 13 to extend, the distance between the pod rod unfolding device 2 and the spacecraft connecting plate 18 is increased, which also increases the angle adjustment range of the unfolded pod rod unfolding device 2. By activating the cable drive motor 14, the length of the rope 16 is adjusted to drive the adjustment of the angle range of the pod rod unfolding device 2, thereby adjusting the angle of the unfolded flexible solar wing film 3 facing the sun.

[0045] When the device begins to retract, the hollow direct drive motor 23 starts to rotate in the opposite direction, which in turn drives the drum 22 to rotate in the opposite direction. This causes the pod rod 21 to retract along the gap between the large guide wheel 243 and the small guide wheel 244. At the same time, the flexible solar panel film 3 also slowly retracts. When the pod rod 21 is wound on the drum 22 to the desired extent, the pod rod 21 will press against the tension wheel 245, giving the tension wheel 245 a compressive force. At this time, the tension spring 247 will pull the tension arm 246, giving the tension wheel 245 a tensile force. This will make the pod rod 21 press tightly against the drum 22, ensuring that the pod rod 21 is flattened and tightly wound on the drum. After the pod rod retraction device 2 has retracted, the telescopic support rod 13 is activated to retract, causing the pod rod retraction device 2 to move closer to the spacecraft connection plate 18, further reducing the space occupied by the entire device.

[0046] The above embodiments are only used to illustrate the technical solutions of the present invention and not to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the specific implementation of the present invention. Any modifications or equivalent substitutions that do not depart from the spirit and scope of the present invention should be covered within the protection scope of the claims of the present invention.

Claims

1. A deployable solar array configuration based on a cable-driven parallel solar orientation device, characterized in that, It includes a cable-driven parallel sun orientation device (1), a pod-shaped rod retraction device (2), and a flexible solar wing film (3). The cable-driven parallel sun orientation device (1) is embedded in the pod-shaped rod retraction device (2), and the flexible solar wing film (3) is installed on the pod-shaped rod retraction device (2). The bean pod stalk winding device (2) includes a bean pod stalk (21), a drum (22), a hollow direct drive motor (23), and a bean pod stalk winding mechanism (24). One end of the bean pod stalk (21) near the drum (22) is bonded to the side of the drum (22). The stator end of the hollow direct drive motor (23) is fixedly installed on the bean pod stalk winding mechanism (24), and the rotor end of the hollow direct drive motor (23) is fixedly installed on the bottom surface of the drum (22). The cable-driven parallel sun-oriented device (1) includes a housing (11), a telescopic support rod (13), a cable-driven motor (14), a support rod fixing clamp (15), a rope (16), and a hinge ball (17). The housing (11) is installed on the pod rod extension device (2) by fixing bolts (12). The cable-driven motor (14) is installed on the bottom surface of the housing (11). The hinge ball (17) is installed in the middle of the top surface of the spacecraft connecting plate (18). The bottom of the telescopic support rod (13) is installed inside the hinge ball (17). The telescopic support rod (13) is fixed on the bottom surface of the housing (11) by the support rod fixing clamp (15). One end of the rope (16) is connected to the cable-driven motor (14), and the other end is connected to the spacecraft connecting plate (18). The outer shell (11) is embedded inside the drum (22), the number of cable drive motors (14) is 3 and they are evenly distributed on the bottom surface of the outer shell (11), and the telescopic support rod (13) is a three-section telescopic rod that retracts inside the hollow direct drive motor (23).

2. The deployable solar array configuration based on a cable-driven parallel sun-oriented device as described in claim 1, characterized in that, The flexible solar wing film (3) is an isosceles right triangle. The apex of the flexible solar wing film (3) is bonded to the side of the pod rod retracting mechanism (24). A cable (31) is connected to the bottom corner of the flexible solar wing film (3). The end of the cable (31) away from the flexible solar wing film (3) is connected to the end of the pod rod (21) away from the roll (22).

3. The deployable solar array configuration based on a cable-driven parallel sun-oriented device as described in claim 1, characterized in that, The bean pod stalk retracting mechanism (24) includes an upper carbon plate (241), a lower carbon plate (242), a large guide wheel (243), a small guide wheel (244), a tension wheel (245), a tension arm (246), a tension spring (247), and a support column (248). The support column (248) is fixed between the upper carbon plate (241) and the lower carbon plate (242). The bean pod stalk (21) is guided between the large guide wheel (243) and the small guide wheel (244). The tension wheel (245) is connected to one end of the tension arm (246) near the drum (22). One end of the tension spring (247) is connected to the support column (248), and the other end is connected to the first bolt (2461) of the tension arm (246).

4. The deployable solar array configuration based on a cable-driven parallel sun-oriented device as described in claim 3, characterized in that, The tensioning arm (246) consists of an upper connecting rod and a lower connecting rod, and the tensioning arm (246) is fixed at the connection between the upper connecting rod and the lower connecting rod by a copper pillar (2462).

5. The deployable solar array configuration based on a cable-driven parallel sun-oriented device as described in claim 4, characterized in that, The tensioning wheel (245) is a hollow cylindrical rubber column, and the tensioning wheel (245) is fixed to the lower connecting rod of the tensioning arm (246) by the first bearing (2451).

6. The deployable solar array configuration based on a cable-driven parallel sun-oriented device as described in claim 3, characterized in that, The large guide wheel (243) is a hollow cylindrical rubber column. The large guide wheel (243) is sleeved on the second bearing (2431). The stator of the second bearing (2431) is sleeved on the second bolt between the upper carbon plate (241) and the lower carbon plate (242). The small guide wheel (244) is a hollow cylindrical rubber column. The small guide wheel (244) is sleeved on the third bearing (2441). The stator of the third bearing (2441) is sleeved on the third bolt between the upper carbon plate (241) and the lower carbon plate (242).

7. The deployable solar array configuration based on a cable-driven parallel sun-oriented device as described in claim 1, characterized in that, The flexible solar panel film (3) is folded in the manner of Miura folding.

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