Solar wing and solar wing on-orbit repeated unfolding and folding method

Abstract

The invention provides a solar wing device which is characterized in that one end of a flexible solar panel (6) is wound on a winding drum (3), the other end of the flexible solar panel (6) is connected with a uniform load rod (5), and the uniform load rod (5) is always parallel to a rotating shaft of the winding drum (3); the scissor mechanism (4) is formed by cascading four equal-length rods which form parallelograms when unfolded, the flexible solar panel is unfolded and folded in the bottom end-top end direction, elastic components are arranged at the bending positions of the left end and the right end, opposite to each other, of each parallelogram, and the scissor mechanism is driven by the elastic components to be unfolded. The elastic component enables the scissor mechanism (4) to always keep a force for pushing away the uniform load rod (5), and in the unfolding state or the folding state of the solar blanket, the torque generated by the motor adapts to the elastic force generated by the elastic component. The flexible solar wing can be repeatedly unfolded and folded in orbit for many times.

Description

Technical Field

[0001] This invention relates to the field of spacecraft solar array technology, and in particular to a solar array and a method for repeatedly deploying and retracting solar arrays in orbit. Background Technology

[0002] With the continuous development of the space industry, spacecraft structures are becoming increasingly complex, and the demands on spacecraft are also increasing. For example, if a large space debris is predicted to collide with the deployed solar array, the control center can retract the solar array in advance through the control system to maximize its protection, and then re-deploy it after the danger has passed; or if the spacecraft needs to perform special attitude maneuvers, the solar array may need to be temporarily retracted to reduce rotational inertia or avoid structural damage, and then re-deployed after the maneuver is completed.

[0003] Patent document CN 119683015 A (application date 20250123) discloses a flexible solar array structure made of a coiled arm that can be deployed or retracted by rotating a pivot. However, this structure limits the size of the solar array and is only suitable for small spacecraft. Patent document CN 119429177A (application date 20241206) discloses a typical scissor-type deployment and retraction structure. However, this mechanism requires a drive unit to deploy or retract the solar array, and a limiting and locking device is required after deployment or retraction, making it unsuitable for repeated use in orbit.

[0004] How to provide a solar array mechanism that can be repeatedly deployed and retracted in orbit has become a technical problem that urgently needs to be solved by people in this field. Summary of the Invention

[0005] This invention provides a repeatedly deployable and retractable solar array device in orbit. After the solar array is deployed or retracted, no additional locking mechanism is required. Instead, the flexible solar array is repeatedly deployed and retracted in orbit by matching the torque provided by the motor with the elastic force generated by the elastic component of the scissor mechanism.

[0006] This invention provides a repeatedly deployable and retractable solar array device in orbit, employing the following technical solution:

[0007] A solar panel device includes a frame 1, a motor 2, a drum 3, a scissor mechanism 4, a load-equalizing rod 5, and a flexible solar panel 6. The motor 2 is fixed to the outside of the frame 1, and the drum 3 is placed inside the frame 1. The motor 2 can drive the drum 3 to rotate. One end of the flexible solar panel 6 is wound around the drum 3, and the other end is connected to the load-equalizing rod 5. The load-equalizing rod 5 and the rotation axis of the drum 3 are always parallel. The scissor mechanism 4 is composed of four cascaded rods of equal length that form a "parallelogram" when unfolded. The bottom end of the first "parallelogram" is installed on the frame 1, and the top end of the last "parallelogram" is connected to the load-equalizing rod 5. When the scissor mechanism 4 unfolds or retracts, it moves the load-equalizing rod 5 outward or inward, thereby unfolding or retracting the flexible solar panel 6. Each "parallelogram" of the scissor mechanism 4 has elastic components at the hinge points on both sides. These elastic components drive the scissor mechanism 4 to maintain an outward unfolding tendency and keep the flexible solar panel 6 under a certain unfolding force, which is variable. When motor 2 stops rotating, it provides a locking force to flexible solar panel 6 (i.e., related to the torque maintained when the motor is de-energized). When motor 2 rotates with drum 3 and moves flexible solar panel 6, it provides tension to flexible solar panel 6. The locking force or tension provided by the motor is adapted to the unfolding force, that is: the locking force should always be greater than the unfolding force, so that a relatively locked state can be maintained after unfolding or retracting. As the motor works, the locking force disappears: during unfolding, the tension is less than or in the same direction as the unfolding force, causing flexible solar panel 6 to unfold; during retracting, the tension is greater than the unfolding force, causing flexible solar panel 6 to retract.

[0008] Optionally, the elastic component is a pull rope disposed between the bends at the opposite ends of the "parallelogram".

[0009] Optionally, the rod is provided with a pulley system and a spring, and the spring applies its elastic force to the pull rope through the pulley system.

[0010] Optionally, the pulley block includes a guide wheel, a fixed pulley, and a movable pulley. One end of the spring is fixed to the rod, and the other end is connected to the movable pulley. The pull rope passes around the guide wheel, the fixed pulley, and the movable pulley in sequence.

[0011] Optionally, the elastic component is a torsion spring or a spiral spring.

[0012] Optionally, the motor (2) is a servo or stepper motor with dynamically adjustable speed to adapt to the unfolding speed of the scissor mechanism (4) during the unfolding process.

[0013] Optionally, the two rods at the bottom of the first "parallelogram" are mounted on the frame (1) via a linkage assembly. The linkage assembly includes a linkage head and a linkage gear. The linkage head is connected to the two rods, and the linkage gear meshes with each other and is rotatably mounted on a base fixed to the frame.

[0014] Optionally, the frame is provided with a spring-loaded telescopic rod for pushing the scissor structure to a predetermined angle when it is just unfolded from its retracted state.

[0015] The present invention also provides an on-orbit reusable deployment and recovery method based on the aforementioned solar array device, the method comprising:

[0016] When the solar panels are retracted, the elastic components store energy, and the scissor-structure rods close.

[0017] During the deployment of the solar array, the load-equalizing beam is released, and the elastic shear mechanism based on the elastic component deploys;

[0018] During the retraction of the solar panels, the motor starts and drives the drum to rotate in the opposite direction. The solar blanket is rewound onto the drum, and the scissor mechanism acts as resistance during this process, retracting and recharging.

[0019] The solar array mechanism that can be repeatedly deployed and retracted in orbit provided by the present invention solves the problem of flexible solar arrays being able to be repeatedly deployed and retracted in orbit by matching the motor with the elastic components of the scissor mechanism, thus avoiding the need for a complex clamping mechanism. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in this 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 some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the solar array device provided by the present invention after it has been deployed.

[0022] Figure 2 This is a schematic diagram of the scissor mechanism of the solar array device provided by the present invention.

[0023] Figure 3 This is an enlarged view of the A-direction in the scissor mechanism of the solar array device provided by the present invention.

[0024] Figure 4 This is a schematic diagram of the layout of the guide wheel in the scissor mechanism of the solar array device provided by the present invention.

[0025] Figure 5This is a schematic diagram showing the direction of the force between the scissor mechanism and the drum in the solar array device provided by the present invention.

[0026] Figure 6 This is an isometric view of the linkage component in the solar array device provided by the present invention.

[0027] Figure 7 This is a schematic diagram of the installation of the micro switch in the solar array device provided by the present invention.

[0028] Figure label:

[0029] 1: Frame; 2: Motor; 3: Drum; 4: Scissor mechanism; 5: Load-sharing rod; 6: Solar fin; 7: Thrust telescopic rod; 8: Micro switch; 9: Linkage base; 41: Wire rope; 42: Guide wheel; 43: Moving pulley; 44: Tension spring; 45: Tension spring hanging point; 46: Fixed pulley; 91: Linkage head; 92: Linkage gear; 93: Base. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0031] Figure 1 This is a schematic diagram of the solar array device provided by the present invention after it has been deployed. Figure 1 As shown, the entire flexible solar panel device consists of a frame 1, a servo motor 2, a drum 3, a scissor mechanism 4, a load-equalizing rod 5, and a flexible solar panel 6. The motor 2 is fixed to the outside of the frame 1, while the drum 3 is placed inside the frame 1. The motor 2 drives the drum 3 to rotate. One end of the flexible solar panel 6 is wound around the drum 3, and the other end is connected to the load-equalizing rod 5. The load-equalizing rod 5 and the rotation axis of the drum 3 remain parallel. The scissor mechanism 4 consists of multiple sets of parallelogram-shaped rods. The bottom end of the first parallelogram is mounted on the frame 1, and the top end of the last parallelogram is connected to the load-equalizing rod 5. When the scissor mechanism 4 unfolds or retracts, it moves the load-equalizing rod 5 outwards or inwards, thereby unfolding or retracting the flexible solar panel 6.

[0032] Figure 2This is a typical schematic diagram of the scissor mechanism in this invention. The scissor mechanism 4 consists of multiple long rods arranged in a cross configuration, hinged in the middle to form a cross-rod structure. The ends of adjacent cross rods are hinged together to form multiple parallelogram structures. In this example, it consists of four groups, but it can also be configured as three or five groups. The bottom end of the first "parallelogram" is mounted on the frame 1, and the top end of the last "parallelogram" is connected to the load-sharing rod 5. Each "parallelogram" of the scissor mechanism 4 has a steel wire rope 41 at its opposite hinge points on both sides. The two ends of the steel wire rope 41 are connected to tension springs located inside the rods on both sides, forming elastic components.

[0033] Figure 3 This is an enlarged view of the scissor mechanism in this invention, view A. The wire rope 41 passes over the guide wheel 42 on the hinge and the fixed pulley 46 inside the rod, then passes over the movable pulley 43 that can move up and down within the rod space before returning to the fixed end. The distance between the fixed pulley 46 and the guide wheel 42 remains constant. The upper hook point of the tension spring 44 is hooked to the center of the movable pulley 43, and the lower hook point 45 of the tension spring is fixed to a fixed position inside the rod. The other end of the wire rope 41 is connected and fixed in the same way to the opposite side of the parallelogram rod. The tension spring 44 always has tension (even after the scissor mechanism is fully extended), ensuring that the relative hinge points (guide wheels 42) of the parallelogram always tend to approach each other. When the motor 2 stops rotating, it has a locking force, which, through the extended sun wing 6, acts on the farthest end of the scissor mechanism, preventing that end from continuing to extend. The two maintain balance, and the extended sun wing 6 has a certain rigidity. The tension spring 44 can be composed of multiple springs to accommodate different amounts of tension and force requirements.

[0034] Figure 4 This is a schematic diagram of the layout of the guide wheel in this invention. The guide wheel 42 is arranged on the outside of the parallelogram-shaped connecting rod hinge shaft, and the steel wire rope is wound in the groove of the guide wheel to avoid the steel wire rope from snagging with other structures during use.

[0035] Figure 5This is a schematic diagram illustrating the force direction between the scissor mechanism and the drum in this invention. In this example, three forces exist: first, a power-off holding torque generated internally when the motor is powered off, preventing the motor shaft from continuing to rotate; this torque is converted into a power-on holding torque or driving torque when the motor is powered back on; second, the tension force provided by the elastic component of the scissor mechanism for the solar panels, which ensures the solar panels always tend to unfold; and third, the driving torque when the motor rotates the drum to retract the solar panels. The power-off holding torque of the motor is far greater than the tension force, thus ensuring that the solar panels can reliably maintain their proper position after unfolding or retracting. The driving torque of the motor is even greater than the holding torque. When the unfolded solar panels need to be retracted, the motor 2 drives the drum 3 to rotate, outputting a larger torque to overcome the tension force generated by the scissor mechanism 4. The solar panels 6 slowly retract as the drum 3 rotates, while simultaneously the wire rope 41 of the scissor mechanism 4 is pulled out from the rod, and the tension spring 44 stores force. When the solar panels need to be deployed from the retracted position, the motor drives the drum to rotate in the opposite direction. Under the tension force provided by the elastic component of the scissor mechanism, the solar panels begin to deploy. The motor mainly serves to limit the speed until the panels are fully deployed. Once the motor is de-energized, the position is locked by the retaining torque, and the solar panels maintain sufficient rigidity under the tension force. To provide more driving force in the initial stage of deployment, a universal elastic telescopic rod 7 can be installed on the frame. This rod provides auxiliary thrust at the beginning of deployment, pushing the long rod of the scissor mechanism to a predetermined angle. Multiple sets of elastic telescopic rods 7 can be installed as needed.

[0036] The motor uses a servo motor, which can adjust the motor speed to adapt to the speed at which the solar panels unfold or retract.

[0037] Of course, in addition to using the tension spring and wire rope structure to form the elastic component as in this example, a torsion spring or spiral spring can also be used instead on the rotating shaft.

[0038] Figure 6 yes Figure 5 The isometric view of the linkage component 9. Linkage components are provided at the bottom of the first "parallelogram" and the top of the last parallelogram of the scissor mechanism to ensure synchronous linkage of the two hinged long rods. Two linkage heads 91 in the linkage component are connected to the two rods of the scissor mechanism 4. Each linkage head 91 rotates synchronously with one of two meshing linkage gears 92 and is rotatably mounted on a base 93 fixed to the frame or load-bearing rod.

[0039] Figure 7 This is a schematic diagram of the installation of the micro switch in the solar array device provided by the present invention. In this example, in order to indicate whether the solar array is fully extended or retracted, a micro switch 7 is installed at a suitable position below the hinge of the rod. When the solar array is fully extended or retracted to the predetermined position, the micro switch 7 is activated and sends a signal to the control system, which then cuts off the power supply to the motor.

[0040] The micro switch can also be replaced by other commonly used switches, or by using parameters collected by the servo motor itself.

[0041] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A solar panel device, comprising a frame (1), a motor (2), a drum (3), a scissor mechanism (4), a load-equalizing rod (5), and a flexible solar panel (6); the motor (2) is mounted and fixed on the outside of the frame (1), the drum (3) is placed on the inside of the frame (1), and the motor (2) drives the drum (3) to rotate around a pivot; one end of the flexible solar panel (6) is wound around the drum (3), and the other end is connected to the load-equalizing rod (5), the load-equalizing rod (5) and the pivot of the drum (3) always remain parallel; characterized in that: The scissor mechanism (4) is composed of four rods of equal length that form a "parallelogram" when unfolded. The bottom end of the first "parallelogram" is mounted on the frame (1), and the top end of the last "parallelogram" is connected to the load-equalizing rod (5). The flexible solar panel unfolds and retracts along the bottom-top direction. Each "parallelogram" has elastic components at the bends at its left and right opposite ends. The scissor structure is unfolded by the elastic components, and the elastic components ensure that the scissor mechanism (4) always has a force to push the load-equalizing rod (5). In the unfolded or retracted state of the solar blanket, the torque generated by the motor is adapted to the elastic force generated by the elastic components.

2. The solar array device according to claim 1, characterized in that: The elastic component is a pull rope located between the bends at the two opposite ends of the "parallelogram".

3. The solar array device according to claim 2, characterized in that: The rod is equipped with a pulley system and a spring, and the spring applies its elastic force to the pull rope through the pulley system.

4. The solar array device according to claim 2, characterized in that: The pulley system includes a guide wheel, a fixed pulley, and a movable pulley. One end of the spring is fixed to the rod, and the other end is connected to the movable pulley. The pull rope passes around the guide wheel, the fixed pulley, and the movable pulley in sequence.

5. The solar array device according to claim 1, characterized in that: The elastic component is a torsion spring or a spiral spring.

6. The solar array device according to claim 1, characterized in that: The motor (2) is a servo motor with dynamically adjustable speed to adapt to the unfolding speed of the scissor mechanism (4) during the unfolding process.

7. The solar array device according to claim 1, characterized in that: The two rods at the bottom of the first "parallelogram" are mounted on the frame (1) by a linkage assembly. The linkage assembly includes a linkage head and a linkage gear. The linkage head is connected to the two rods, and the linkage gear meshes with each other and is rotatably mounted on a base fixed to the frame.

8. The solar array device according to claim 1, characterized in that: The frame is equipped with a spring-loaded telescopic rod, which is used to push the scissor structure to a predetermined angle when it is just unfolded from the retracted state.

9. A method for repeated deployment and recovery in orbit based on the solar array device according to claim 1, characterized in that, The method includes: When the solar panels are retracted, the elastic components store energy, and the scissor-structure rods close. During the deployment of the solar array, the load-bearing beam is released, the elastic shear mechanism based on the elastic component deploys, and the motor performs process speed limiting; During the retraction of the solar panels, the motor starts and drives the drum to rotate in the opposite direction. The solar blanket is rewound onto the drum, and the scissor mechanism acts as resistance during this process, retracting and recharging.

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