Expandable solar wing structure based on cable-driven parallel sun orientation device

Abstract

The invention discloses an expandable solar wing structure based on a cable-driven parallel sun orientation device, and relates to the technical field of spatial large expandable thin film solar wings and application thereof.The cable-driven parallel sun orientation device is embedded in a pod rod folding and unfolding device, and a flexible solar wing thin film is installed in the pod rod folding and unfolding device; therefore, the cable-driven parallel sun orientation device, the pod rod folding and unfolding device and the flexible solar wing film are integrated, the high storage ratio of the expandable flexible solar wing structure is guaranteed, the envelope size of the whole structure of the device is reduced, and the occupied space of the whole device is reduced.

Description

Technical Field

[0001] The present invention relates to the field of large-scale deployable thin-film solar wing and its application technology, and in particular to a deployable solar wing configuration based on a cable-driven parallel sun-orienting device. Background Art

[0002] As the most common energy supply equipment, solar arrays are widely used in current spacecraft. Among them, high folding ratio, low surface density and ultra-high power have become the development direction of the new generation of solar arrays. Its main structure can be divided into two parts: solar wing surface and solar orientation device. The basic structures currently under research include flexible solar arrays, which mainly include foldable flexible solar arrays, retractable flexible solar arrays and circular array solar arrays; and solar orientation devices, which mainly include single-degree-of-freedom solar orientation devices and double-degree-of-freedom solar orientation devices. The foldable flexible solar wing is in a folded state before the spacecraft enters the predetermined working orbit. When the spacecraft enters the working orbit, the flexible solar wing is driven to unfold by the unfolding mechanism, and the angle of the solar wing surface is adjusted through the solar orientation device to ensure that the solar wing surface is oriented to the sun and provide energy for the spacecraft.

[0003] The widely used flexible solar wing surface can be composed of laminated glass fiber or carbon fiber composite materials and Kapton / polyimide film. The folding flexible solar wing is similar to the accordion unfolding method, folding like the ancient "Zou Zhe"; the retractable flexible solar wing is rolled on a cylinder during launch and fully extended by the unfolding mechanism during operation; the circular array flexible solar wing adopts a structure similar to the antenna reflector, and multiple arrays are unfolded in a circle around a hub-shaped support structure. The stability and reliability of the mechanical structure of the solar orientation device are directly related to the overall performance and operational safety of the spacecraft. The single-degree-of-freedom solar orientation method is currently commonly used, which is simple to control and relatively mature in technology. However, since the single-degree-of-freedom drive can only adjust the attitude of the solar wing panel within a certain range, it is impossible to achieve complete alignment with the sunlight, so the solar energy reception efficiency is relatively low. In addition, facing the complex and changeable space environment, the single-degree-of-freedom drive has poor adaptability and it is difficult to adjust the solar wing panel in real time to maximize the reception of solar energy. The dual-degree-of-freedom solar orientation device achieves precise alignment of sunlight through two mutually perpendicular degrees of freedom adjustment, ensuring that the solar wing panels always face the sun, thereby significantly improving the efficiency of solar energy reception. However, since the dual-degree-of-freedom solar orientation device requires more mechanical components and control systems to achieve the adjustment of two degrees of freedom, the structure is relatively complex, and the manufacturing and maintenance costs are also higher. After the flexible solar wing retractable and unfolding device and the solar orientation device are integrated, the size of the solar orientation device cannot be changed, and the solar orientation device will occupy a large space, which cannot meet the high storage ratio of the current flexible solar wing folding and unfolding. 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 folding and unfolding device and the solar orientation device are integrated, the solar orientation device will occupy a large space and cannot meet the high storage ratio of the current flexible solar wing folding and unfolding, the technical problem to be solved by the present invention is to provide a deployable solar wing configuration based on a cable-driven parallel solar orientation device that can achieve a high storage ratio of the deployable flexible solar wing overall device.

[0005] In order to solve the above technical problems, the present invention provides a deployable solar wing configuration based on a cable-driven parallel solar orientation device, a cable-driven parallel solar orientation device, a pod pole retracting and extending device and a flexible solar wing film, the cable-driven parallel solar orientation device is embedded in the pod pole retracting and extending device, and the flexible solar wing film is installed on the pod pole retracting and extending device.

[0006] Preferably, the pod rod folding and unfolding device includes a pod rod, a reel, a hollow direct-drive motor and a pod rod folding and unfolding mechanism, the end of the pod rod close to the reel is bonded to the side of the reel, the stator end of the hollow direct-drive motor is fixedly installed on the pod rod folding and unfolding mechanism, and the rotor end of the hollow direct-drive motor is fixedly installed on the bottom surface of the reel.

[0007] Preferably, the cable-driven parallel solar orientation device includes an outer shell, a telescopic support rod, a cable-driven motor, a support rod fixing clamp, a rope and a hinge ball. The outer shell is installed on the pod rod retracting and extending device through fixing bolts, the cable-driven motor is installed on the bottom surface of the outer shell, the hinge ball is installed in the middle of the top surface of the spacecraft connecting plate, the bottom of the telescopic support rod is installed in the hinge ball, the telescopic support rod is fixed to the bottom surface of the outer shell 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 connecting plate.

[0008] Preferably, the shell is embedded in the drum, the number of the cable drive motors is 3 and they are evenly distributed on the bottom surface of the shell, and the telescopic support rod is a three-section telescopic rod and is retracted inside the hollow direct drive motor.

[0009] Preferably, the flexible solar wing film is an isosceles right triangle, the top corner of the flexible solar wing film is bonded to the side of the pod rod retracting and unfolding mechanism, the bottom corner of the flexible solar wing film is connected with a cable, and the end of the cable away from the flexible solar wing film is connected to the end of the pod rod away from the reel.

[0010] Preferably, the pod rod folding and unfolding mechanism includes an upper carbon plate, a lower carbon plate, a large guide wheel, a small guide wheel, a tensioning wheel, a tensioning 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 rod is guided between the large guide wheel and the small guide wheel, the tensioning wheel is connected to one end of the tensioning arm close to the reel, one end of the tension spring is connected to the support column, and the other end is connected to the first bolt of the tensioning arm.

[0011] Preferably, the tensioning arm consists of an upper connecting rod and a lower connecting rod, and the tensioning arm is fixed at the connection between the upper connecting rod and the lower connecting rod through a copper column.

[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 through a first bearing.

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

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

[0015] Beneficial Effects The present invention embeds a cable-driven parallel solar orientation device into a pod pole retractable device, and installs a flexible solar wing film in the pod pole retractable device, thereby integrating the cable-driven parallel solar orientation device, the pod pole retractable device and the flexible solar wing film into one, thereby ensuring a high storage ratio of the deployable flexible solar wing structure, reducing the envelope size of the overall structure of the device, and reducing the occupied space of the entire device.

[0016] The present invention adopts a hollow direct-drive motor, and extends the telescopic support rod of the cable-driven parallel solar orientation device into the interior of the hollow direct-drive motor. At the same time, the cable-driven parallel solar orientation device is integrated as a whole inside the reel, which not only increases the telescopic range of the telescopic support rod, increases the adjustment range of the solar orientation device, but also reduces the longitudinal size of the solar wing when it is folded.

[0017] The present invention adopts a cable-driven method to adjust the solar orientation, adopts a 3-RPS parallel platform to drive the motion platform through multi-rope traction, and adjusts the angle range of the motion platform (i.e. the solar wing surface) by changing the rope length. The control theory is mature and precise solar orientation can be achieved.

[0018] When the flexible solar wing film of the present invention is unfolded, the flexible solar wing film is connected to the pod rod by a cable. The centrally symmetrical pod rod can ensure that both sides of the pod rod are subjected to the tension of the cable when the pod rod is extended. The two right-angled sides of the flexible solar wing film are tensioned into shape. The overall structure can ensure force balance and maintain the surface stiffness of the entire solar wing surface.

[0019] The area of ​​the flexible solar wing film in the present invention can be changed according to the length of the pod rod. When the overall length of the pod rod increases, the two right-angled sides of the flexible solar wing film can be increased accordingly to meet the requirements of the extra-large size of the flexible solar wing. When the solar wing is not working, the pod rod is flattened and wound on a reel, which can meet the requirements of the high storage ratio of the flexible solar wing. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0021] Figure 1 It is a schematic diagram of the unfolded state of the unfoldable solar wing configuration based on the cable-driven parallel sun orientation device in the present invention; Figure 2 It is a schematic diagram of the folded state of the deployable solar wing configuration based on the cable-driven parallel sun-orienting device in the present invention; Figure 3 A cross-sectional view of a cable-driven parallel solar orientation device of the present invention with a deployable solar wing configuration based on the cable-driven parallel solar orientation device; Figure 4 It is a general schematic diagram of a pod pole retracting and unfolding device of a deployable solar wing configuration based on a cable-driven parallel sun-orienting device in the present invention; Figure 5 It is a schematic diagram of the internal structure of the pod pole retracting and unfolding device of the deployable solar wing configuration based on the cable-driven parallel sun-orienting device in the present invention; Figure 6 It is a cross-sectional view of the tensioning arm of the pod pole stowage and deployment device of the deployable solar wing configuration based on the cable-driven parallel sun-orientation device in the present invention; Figure 7 It is a schematic diagram of the connection between a single flexible solar wing film and a pod pole of a deployable solar wing configuration based on a cable-driven parallel solar orientation device in the present invention.

[0022] Explanation of the reference numerals in the figure: 1. Sun-directing device; 11. Shell; 12. Fixing bolt; 13. Telescopic support rod; 14. Cable drive motor; 15. Support rod fixing fixture; 16. Rope; 17. Hinge ball; 18. Spacecraft connecting plate; 2. Pod rod retracting and extending device; 21. Pod rod; 22. Reel; 23. Hollow direct drive motor; 24. Pod rod retracting and extending 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 wing film; 31. Cable. DETAILED DESCRIPTION

[0023] In order to further understand the content of the present invention, the present invention is described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the embodiments are only for explaining the present invention and are not intended to limit it.

[0024] Example 1 A deployable solar wing configuration based on a cable-driven parallel sun-orienting device, such as Figure 1-7 As shown, it includes a cable-driven parallel sun orientation device 1, a pod pole retracting and extending device 2 and a flexible solar wing film 3. The cable-driven parallel sun orientation device 1 is embedded in the pod pole retracting and extending device 2, and the flexible solar wing film 3 is installed on the pod pole retracting and extending device 2.

[0025] The pod rod folding and unfolding device 2 includes a pod rod 21, a reel 22, a hollow direct-drive motor 23 and a pod rod folding and unfolding mechanism 24, wherein one end of the pod rod 21 close to the reel 22 is bonded to the side of the reel 22, the stator end of the hollow direct-drive motor 23 is fixedly mounted on the pod rod folding and unfolding mechanism 24, and the rotor end of the hollow direct-drive motor 23 is fixedly mounted on the bottom surface of the reel 22.

[0026] The cable-driven parallel solar orientation device 1 includes an outer shell 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 outer shell 11 is installed on the pod rod retracting and extending device 2 through a fixing bolt 12, the cable-driven motor 14 is installed on the bottom surface of the outer shell 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 in the hinge ball 17, the telescopic support rod 13 is fixed to the bottom surface of the outer shell 11 through 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.

[0027] The housing 11 is embedded in the drum 22 . The number of the cable drive motors 14 is three and they are evenly distributed on the bottom surface of the housing 11 . The telescopic support rod 13 is a three-section telescopic rod and is retracted inside the hollow direct drive motor 23 .

[0028] Furthermore, the diameter of the cylindrical portion of the housing 11 should be smaller than the inner diameter of the drum 22 to ensure that the housing 11 can be placed inside the drum 22, thereby reducing the envelope thickness of the overall device.

[0029] 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, so that the last section of the telescopic support rod 13 can be stored inside the hollow direct-drive motor 23, further reducing the longitudinal size of the entire device after folding. The flexible solar wing film 3 is an isosceles right triangle. The top corner of the flexible solar wing film 3 is bonded to the side of the pod rod retracting and unfolding mechanism 24. A pull cable 31 is connected to the bottom corner of the flexible solar wing film 3. The end of the pull cable 31 away from the flexible solar wing film 3 is connected to the end of the pod rod 21 away from the reel 22.

[0030] The pod rod folding and unfolding mechanism 24 includes an upper carbon plate 241, a lower carbon plate 242, a large guide wheel 243, a small guide wheel 244, a tensioning wheel 245, a tensioning 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 pod rod 21 is guided between the large guide wheel 243 and the small guide wheel 244. The tensioning wheel 245 is connected to one end of the tensioning arm 246 close to the reel 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 tensioning arm 246.

[0031] The tensioning arm 246 is composed 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 through a copper column 2462.

[0032] The tension wheel 245 is a hollow cylindrical rubber column, and the tension wheel 245 is fixed to the lower connecting rod of the tension arm 246 through a first bearing 2451 .

[0033] The large guide wheel 243 is a hollow cylindrical rubber column, and 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, and 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.

[0034] The flexible solar wing film 3 is folded in a Miura folding manner.

[0035] Working principle: When the device starts to unfold, the hollow direct-drive motor 23 starts to rotate, which in turn drives the reel 22 to rotate, driving the pod rod 21 to start extending outward along the gap between the large guide wheel 243 and the small guide wheel 244, and also drives the flexible solar wing film 3 to slowly unfold. After the entire device is fully unfolded, at this time, the angle of the unfolded flexible solar wing film 3 facing the sun is adjusted according to actual conditions, and the distance between the pod rod folding and unfolding device 2 and the spacecraft connecting plate 18 is increased by starting the telescopic support rod 13 to extend, and the angle adjustment range of the unfolded pod rod folding and unfolding device 2 is also increased. By starting the rope drive motor 14 and adjusting the length of the rope 16, the angle range of the pod rod folding and unfolding device 2 is driven to adjust, and then the angle of the unfolded flexible solar wing film 3 facing the sun is adjusted; When the device begins to fold, the hollow direct-drive motor 23 begins to rotate in the opposite direction, thereby driving the reel 22 to rotate in the opposite direction, driving the pod rod 21 to begin to shrink back along the gap between the large guide wheel 243 and the small guide wheel 244, and at the same time, it will also drive the flexible solar wing film 3 to shrink slowly. When the pod rod 21 is wound on the reel 22 to a movable extent, the pod rod 21 will be close to the tensioning wheel 245, which will give the tensioning wheel 245 an extrusion force. At this time, the tension spring 247 will pull the tensioning arm 246 and give the tensioning wheel 245 a pulling force, which will make the pod rod 21 close to the reel 22 and ensure that the pod rod 21 is tightly wound on the reel after being flattened. After the pod rod folding and unfolding device 2 is shrunk, the telescopic support rod 13 is started to be recovered, so that the pod rod folding and unfolding device 2 is close to the spacecraft connecting plate 18, further reducing the occupied space of the entire device.

[0036] The above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit the same. Although the present invention has been described in detail with reference to the above embodiments, a person skilled in the art should understand that the specific implementation modes of the present invention can still be modified or replaced by equivalents, and any modification or equivalent replacement that does not depart from the spirit and scope of the present invention should be included in the scope of protection of the claims of the present invention.

Claims

1. A deployable solar wing configuration based on a cable-driven parallel sun-orienting device, characterized in that: It comprises a cable-driven parallel solar orientation device (1), a pod pole retracting and extending device (2) and a flexible solar wing film (3), wherein the cable-driven parallel solar orientation device (1) is embedded in the pod pole retracting and extending device (2), and the flexible solar wing film (3) is installed on the pod pole retracting and extending device (2).

2. A deployable solar wing configuration based on a cable-driven parallel sun-orienting device as claimed in claim 1, characterized in that: The pod rod folding and unfolding device (2) comprises a pod rod (21), a reel (22), a hollow direct-drive motor (23) and a pod rod folding and unfolding mechanism (24); one end of the pod rod (21) close to the reel (22) is bonded to the side of the reel (22); a stator end of the hollow direct-drive motor (23) is fixedly mounted on the pod rod folding and unfolding mechanism (24); and a rotor end of the hollow direct-drive motor (23) is fixedly mounted on the bottom surface of the reel (22).

3. A deployable solar wing configuration based on a cable-driven parallel sun orientation device as claimed in claim 2, characterized in that: The cable-driven parallel solar orientation device (1) comprises a shell (11), a telescopic support rod (13), a cable-driven motor (14), a support rod fixing fixture (15), a rope (16) and a hinge ball (17); the shell (11) is mounted on the pod rod retracting and extending device (2) via a fixing bolt (12); the cable-driven motor (14) is mounted on the bottom surface of the shell (11); the hinge ball (17) is mounted on the middle part of the top surface of the spacecraft connecting plate (18); the bottom of the telescopic support rod (13) is mounted in the hinge ball (17); the telescopic support rod (13) is fixed to the bottom surface of the shell (11) via the support rod fixing fixture (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).

4. A deployable solar wing configuration based on a cable-driven parallel sun-orienting device as claimed in claim 3, characterized in that: The outer shell (11) is embedded in the reel (22), the number of the cable drive motors (14) is three 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 and is retracted inside the hollow direct drive motor (23).

5. A deployable solar wing configuration based on a cable-driven parallel sun-orienting device as claimed in claim 2, characterized in that: The flexible solar wing film (3) is an isosceles right triangle; the top corner of the flexible solar wing film (3) is bonded to the side of the pod rod retracting and unfolding mechanism (24); a pull cable (31) is connected to the bottom corner of the flexible solar wing film (3); an end of the pull cable (31) away from the flexible solar wing film (3) is connected to an end of the pod rod (21) away from the reel (22).

6. A deployable solar wing configuration based on a cable-driven parallel sun-orienting device as claimed in claim 2, characterized in that: The pod rod folding and unfolding mechanism (24) comprises 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 pod rod (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) close to the reel (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).

7. A deployable solar wing configuration based on a cable-driven parallel sun-orienting device as claimed in claim 6, characterized in that: The tensioning arm (246) is composed 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 through a copper column (2462).

8. A deployable solar wing configuration based on a cable-driven parallel sun-orienting device as claimed in claim 7, characterized in that: The tension wheel (245) is a hollow cylindrical rubber column, and the tension wheel (245) is fixed to the lower connecting rod of the tension arm (246) via a first bearing (2451).

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

10. A deployable solar wing configuration based on a cable-driven parallel sun-orienting device as claimed in claim 1, characterized in that: The flexible solar wing film (3) is folded in a Miura folding manner.

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