A circular solar wing deployment mechanism, a satellite-borne control unit and a circular solar wing

Abstract

The application relates to the field of aerospace technology, in particular to a circular solar wing unfolding and folding mechanism, a satellite-borne control unit and a circular solar wing. The circular solar wing unfolding and folding mechanism comprises a driving member, an arc-shaped nesting assembly and a self-locking assembly. The driving member is an integrated driving element made of a shape memory material; two ends of the driving member are connected to arc-shaped housings at the head and tail ends of the arc-shaped nesting assembly; the self-locking assembly is arranged at the end of the arc-shaped nesting assembly; the driving member is used for generating extension and contraction deformation in response to external excitation, so as to drive the arc-shaped nesting assembly to make the arc-shaped housings slide along a guide matching pair in sequence, so that the arc-shaped nesting assembly is unfolded or folded in stages; and the self-locking assembly is used for locking the arc-shaped nesting assembly when the arc-shaped nesting assembly is completely unfolded. The light weight, simple structure and high storage ratio are realized, efficient and stable driving and unfolding are achieved, and the reliability, adaptability and intelligent level of the whole solar wing system are remarkably improved.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and more specifically, to a circular solar array deployment and retraction mechanism, a spaceborne control unit, and a circular solar array. Background Technology

[0002] A circular solar array is a type of solar array that unfolds into a near-circular shape. It typically consists of solar cells attached to multiple flexible triangular thin films, and is a type of flexible solar array. Circular solar arrays are characterized by their compact structure and high retraction ratio, making them widely used in space missions such as deep space exploration, manned spacecraft, and cargo spacecraft, with demand continuing to grow. Due to the strict space constraints during spacecraft launch, these solar arrays must remain folded during launch and unfold again after entering orbit; therefore, a reliable and efficient deployment and retraction mechanism is crucial.

[0003] Currently, circular solar array deployment and retraction mechanisms generally employ a combined drive system of a spiral spring at the center of the circle and a terminal motor, relying on a complex linkage truss as a supporting framework and achieving deployment through mechanical transmission. However, this traditional drive scheme is structurally complex with numerous components, and redundant motors are often required to ensure reliability, resulting in a heavy system and large space occupation. At the same time, the long transmission chain also leads to low drive efficiency and high energy consumption, and the complex mechanical structure also affects motion smoothness and long-term on-orbit reliability. Summary of the Invention

[0004] To address the aforementioned technical problems, this invention provides a circular solar array deployment and retraction mechanism, a spaceborne control unit, and a circular solar array, solving the problems of high complexity, heavy weight, and low drive efficiency of traditional circular solar array deployment and retraction mechanisms.

[0005] On one hand, the present invention provides a circular solar wing deployment and retraction mechanism, comprising:

[0006] The driving element is an integrated driving component made of shape memory material;

[0007] An arc-shaped nested assembly includes at least two arc-shaped shells that are concentrically nested in sequence through a guide mating pair. The arc-shaped shells extend in an arc shape, and the two ends of the driving member are respectively connected to the arc-shaped shells at the beginning and end of the arc-shaped nested assembly.

[0008] A self-locking component is disposed at the end of the arc-shaped nested component;

[0009] The driving component is used to generate expansion and contraction deformation in response to external excitation, so as to drive the arc-shaped nested component to make each arc-shaped shell slide relative to the other along the guide mating pair, thereby realizing the hierarchical expansion or contraction of the arc-shaped nested component; the self-locking component is used to lock the arc-shaped nested component when it is fully expanded, and when the arc-shaped nested component is fully expanded, its multiple arc-shaped shells together form a ring.

[0010] Preferably, the shape memory material is a bidirectional shape memory polymer; the driving member changes from a first form to a second form under the external excitation to provide an unfolding driving force for the arc-shaped nested component, and the driving member returns from the second form to the first form after the external excitation is removed to provide a closing driving force for the arc-shaped nested component.

[0011] Preferably, the driving component is an elastic member, and is one of the following: spring-shaped, negative Poisson's ratio arc-shaped push rod-shaped, or corrugated tube-shaped.

[0012] Preferably, the self-locking assembly includes a locking element and a mating sleeve;

[0013] The locking member is disposed at the head end of the arc-shaped nested assembly, which serves as the unfolding and propulsion end, and the mating sleeve is disposed at the tail end of the arc-shaped nested assembly;

[0014] The locking element is made of a bidirectional shape memory material and is designed to change between a locked and released state in response to temperature changes in order to engage or disengage with the mating sleeve.

[0015] Preferably, the locking member includes a locking part, which, in the locked state, is hook-shaped, arrow-shaped, or boss-shaped for engaging with the mating sleeve.

[0016] Preferably, the locking element is integrally formed with the arc-shaped shell at the head end of the arc-shaped nesting assembly by 3D printing additive manufacturing.

[0017] Preferably, the guide mating pair includes a guide rail disposed on the inner side wall of the arc-shaped housing, and a slider disposed on the outer side wall of another arc-shaped housing adjacent to the arc-shaped housing, and the slider and the guide rail are in sliding engagement.

[0018] Preferably, each of the arcuate shells has a connecting rib extending radially outward on its outer arcuate wall surface, the connecting rib being used to connect and support the flexible thin-film substrate of the solar cell.

[0019] On the other hand, the present invention also provides a spaceborne control unit, mounted on a spacecraft and communicatively connected to a ground-based main control terminal, the spaceborne control unit comprising:

[0020] The instruction receiving and transmitting module is used to receive control instructions from the ground master control terminal and generate drive signals according to the control instructions to apply external excitation to the drive components of the circular solar wing deployment and retraction mechanism as described above.

[0021] The status monitoring and feedback module is used to monitor the deployment and retraction status of the arc-shaped nested components of the circular solar wing deployment and retraction mechanism, and send feedback signals to the ground main control terminal.

[0022] The feedback signal is used to generate updated control commands for the ground control terminal, so as to adjust the extension and retraction process of the arc-shaped nested component.

[0023] In another aspect, the present invention provides a circular solar array, including the circular solar array deployment and retraction mechanism as described above, and / or including the spaceborne control unit as described above.

[0024] The beneficial technical effects of this invention are as follows:

[0025] This invention provides a circular solar wing deployment and retraction mechanism. The driving component is an integrated driving element made of shape memory material, which not only simplifies the structure and reduces weight, but also achieves direct and efficient energy conversion from electrical or thermal excitation to mechanical deformation, improving driving efficiency and response speed. The construction and connection of the arc-shaped nested components utilize the concentric nesting and guided sliding cooperation of multiple arc-shaped shells. This ensures that the arc-shaped shells unfold smoothly and orderly along a predetermined arc trajectory while achieving a high degree of structural compactness. Furthermore, its simple sleeve-type hierarchical deployment mechanism replaces the complex linkage truss system, further reducing the complexity of the mechanism and motion uncertainty. The self-locking component automatically completes mechanical locking at the end of the driving process, eliminating the need for an additional independent locking mechanism. This allows the locking function to be naturally and reliably embedded in the final state of the deployment process. Therefore, this invention provides a circular solar wing deployment and retraction mechanism that achieves lightweight, structural simplicity, and high retraction ratio, while simultaneously achieving efficient and stable driving and deployment, as well as reliable and autonomous terminal locking, significantly improving the reliability, adaptability, and intelligence level of the entire solar wing system.

[0026] The invention provides a spaceborne control unit. The command receiving and transmission module ensures that ground control intentions are accurately and reliably parsed by the satellite system and converted into excitation signals for the driving components, enabling remote command control of the deployment and recovery actions. The status monitoring and feedback module can acquire and report the precise deployment and recovery status of the arc-shaped nested components in real time, allowing the ground control terminal to make decisions based on real and timely telemetry data, rather than operating blindly. This status feedback-based control mode enables ground personnel or automatic control algorithms to assess the health of the deployment and recovery process in real time. Once an anomaly is detected, rapid intervention can be initiated by sending updated control commands for dynamic intervention and strategy adjustments. This effectively addresses risks arising from space environment interference or accidental deviations of the deployment and recovery mechanisms themselves, improving mission success rate and safety.

[0027] The circular solar array provided by the invention has the same beneficial effects on the prior art as the aforementioned circular solar array deployment and retraction mechanism or a spaceborne control unit, and will not be repeated here. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the structure of a circular solar wing deployment and retraction mechanism in one embodiment of the present invention when it is deployed;

[0029] Figure 2 for Figure 1 A magnified view of a portion of the image;

[0030] Figure 3 for Figure 2 The locking element in the diagram is a structural schematic of the locking configuration;

[0031] Figure 4 This is a schematic diagram of the arc-shaped shell structure in one embodiment of the present invention;

[0032] Figure 5 This is a schematic diagram of the structure of a circular solar wing retraction mechanism when it is retracted, according to one embodiment of the present invention;

[0033] Figure 6 for Figure 5 A schematic diagram of the internal structure of the arc-shaped nested component;

[0034] Figure 7 This is a schematic diagram of the driving member in a stretched and unfolded state in one embodiment of the present invention;

[0035] Figure 8 This is a schematic diagram of the driving component in a compressed and retracted state in one embodiment of the present invention.

[0036] Explanation of reference numerals in the attached figures:

[0037] 1-Driver; 2-Arc-shaped nested assembly; 21-Arc-shaped housing; 221-Guide rail; 222-Slider; 23-Connecting rib; 3-Self-locking assembly; 31-Locking component; 32-Matching sleeve. Detailed Implementation

[0038] To make the above-mentioned objects, features, and advantages of the present invention more apparent and understandable, specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. Although some embodiments of the present invention are shown in the drawings, it should be understood that the present invention can be implemented in various forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of the present invention. It should be understood that the accompanying drawings and embodiments of the present invention are for illustrative purposes only and are not intended to limit the scope of protection of the present invention.

[0039] The term "comprising" and its variations as used herein are open-ended, meaning "including but not limited to"; the term "based on" means "at least partially based on"; the term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments"; and the term "optionally" means "optional embodiments". Definitions of other terms will be given in the following description. It should be noted that the concepts of "first," "second," etc., mentioned in this invention are used only to distinguish different devices, modules, or units, and are not intended to limit the order of functions performed by these devices, modules, or units or their interdependencies.

[0040] It should be noted that the terms "a" and "a plurality of" used in this invention are illustrative rather than restrictive. Those skilled in the art should understand that, unless otherwise expressly indicated in the context, they should be understood as "one or more".

[0041] See Figure 1 , Figure 2 and Figure 6As shown, the present invention provides a circular solar wing deployment and retraction mechanism, including a drive element 1, an arc-shaped nested assembly 2, and a self-locking assembly 3. The drive element 1 is an integrated drive element made of shape memory material; the arc-shaped nested assembly 2 includes at least two arc-shaped shells 21 concentrically nested together by guide mating pairs, the arc-shaped shells 21 extending in an arc shape, and the two ends of the drive element 1 are respectively connected to the first and last ends of the arc-shaped shells 21 of the arc-shaped nested assembly 2; the self-locking assembly 3 is disposed at the end of the arc-shaped nested assembly 2; wherein, the drive element 1 is used to generate expansion and contraction deformation in response to external excitation, so as to drive the arc-shaped nested assembly 2 so that each arc-shaped shell 21 slides relative to each other along the guide mating pairs, thereby realizing the graded deployment or retraction of the arc-shaped nested assembly 2; the self-locking assembly 3 is used to lock the arc-shaped nested assembly 2 when it is fully deployed, and when the arc-shaped nested assembly 2 is fully deployed, its multiple arc-shaped shells 21 together form a ring.

[0042] See Figure 7 and Figure 8 As shown, further, the arc-shaped shells 21 at the beginning and end of the arc-shaped nested assembly 2 specifically refer to the outermost and innermost arc-shaped shells 21 in the concentric nesting arrangement. The drive component 1 is programmed at room temperature; in the high-temperature state, it is a stretched and unfolded spiral spring, and in the low-temperature state, it is a compressed and folded spiral spring. When energized, heating will change it to a high-temperature state, and when de-energized, cooling will restore it to a low-temperature state.

[0043] It should be noted that the material properties and integrated design of the drive component 1 not only greatly simplify the structure and reduce weight, but also achieve direct and efficient energy conversion from electrical (or thermal) excitation to mechanical deformation, improving drive efficiency and response speed. The construction and connection method of the arc-shaped nested component 2 utilizes the concentric nesting and guided sliding cooperation of multiple arc-shaped shells 21. While ensuring the smooth and orderly unfolding of the arc-shaped shells 21 along a predetermined arc trajectory, it achieves a high degree of structural compactness. Furthermore, its simple sleeve-type hierarchical unfolding mechanism replaces the complex linkage truss system, further reducing the complexity of the mechanism and motion uncertainty. The self-locking component 3 automatically completes mechanical locking at the end of the drive process, eliminating the need for an additional independent locking mechanism, allowing the locking function to be naturally and reliably embedded in the final state of the unfolding process. Therefore, this invention provides a circular solar wing unfolding and retracting mechanism that achieves lightweight, structural simplicity, and high retraction ratio, while simultaneously achieving efficient and smooth drive and unfolding, as well as reliable and autonomous terminal locking, significantly improving the reliability, adaptability, and intelligence level of the entire solar wing system.

[0044] See Figure 7 and Figure 8 As shown, in one embodiment of the present invention, the driving member 1 is an elastic member, and is one of the following: spring-shaped, negative Poisson's ratio arc-shaped push rod-shaped, or corrugated tube-shaped.

[0045] It should be noted that the driving component 1 is an elastic member, which is both a power source and a core component of the transmission mechanism. It outputs controllable linear driving force through direct and reversible deformation (such as extension and contraction) in response to external excitation. This not only eliminates components such as motors, reducers, and transmission linkages found in traditional solutions, maximizing the simplification and integration of the overall drive structure, but also avoids the inherent frictional losses and energy waste in multi-stage mechanical transmissions due to the reduction in energy conversion stages (e.g., direct conversion of electrical energy into material deformation energy), thereby significantly improving drive efficiency and energy utilization. Furthermore, the integrated design of the elastic component and its direct connection to the arc-shaped nested component 2 ensure a simple and clear force transmission path, smooth and reliable motion, and avoidance of instability factors.

[0046] In one embodiment of the present invention, the shape memory material is a bidirectional shape memory polymer; the driving member 1 changes from a first form to a second form under external excitation to provide an unfolding driving force for the arc-shaped nested component 2, and the driving member 1 returns from the second form to the first form after the external excitation is removed to provide a closing driving force for the arc-shaped nested component 2.

[0047] It should be noted that during the dynamic unfolding process of the drive component 1 changing from the first form to the second form, the arc-shaped nested component 2, under external excitation, the power supply is on and the drive component 1 is gradually heated, causing it to gradually change shape from a coiled spring compressed and contracted at a low temperature to a coiled spring stretched and unfolded at a high temperature.

[0048] After the external excitation is removed, the drive component 1 returns from the second form to the first form, which is the process of the arc-shaped nested component 2 closing. The power is off, and the drive component 1 gradually cools down, causing it to gradually change shape from a spiral spring that is stretched and unfolded at a high temperature to a spiral spring that is compressed and closed at a low temperature.

[0049] See Figure 4 As shown, in one embodiment of the present invention, the guide mating pair includes a guide rail 221 disposed on the inner side wall of the arc-shaped housing 21, and a slider 222 disposed on the outer side wall of another arc-shaped housing 21 adjacent to the arc-shaped housing 21, and the slider 222 and the guide rail 221 are in sliding engagement.

[0050] Furthermore, the guide rail 221 is a groove opened on the inner side wall of the arc-shaped housing 21 and slides in cooperation with the slider 222. The groove is opened along the arc-shaped direction (i.e., circumferential direction) of the arc-shaped housing 21. The grooves can be symmetrically opened in pairs on the inner walls of both sides of the arc-shaped housing 21. The outer side wall of the other arc-shaped housing 21 that is adjacent to it is provided with two matching sliders 222. This allows the two adjacent arc-shaped housings 21 to maintain precise concentricity and movement trajectory during sliding and effectively resist lateral forces or torques, ensuring the smooth and reliable unfolding and retraction of the entire arc-shaped nested assembly 2.

[0051] In one embodiment of the present invention, the self-locking component 3 includes a locking member 31 and a mating sleeve 32; the locking member 31 is disposed at the first end of the arc-shaped nested component 2 as the unfolding propulsion end, and the mating sleeve 32 is disposed at the tail end of the arc-shaped nested component 2; the locking member 31 is made of a bidirectional shape memory material and is used to change between a locked state and a released state in response to temperature changes, so as to achieve engagement or separation with the mating sleeve 32.

[0052] It should be noted that the locking function of the self-locking component 3 is directly applied to the locking element 31 made of shape memory material, enabling it to reversibly change between locked and released states in response to temperature changes. This allows for engagement or disengagement with the mating sleeve 32 through the material's inherent properties. This not only simplifies the system configuration and reduces weight and space usage, but also fundamentally reduces potential failure points caused by redundant moving parts. Furthermore, the locking element 31 is integrated into the leading end, which serves as the unfolding propulsion end, allowing the locking action to seamlessly connect with the unfolding process of the arc-shaped nested component 2 in both timing and space, eliminating the need for additional transmission or positioning devices and improving locking accuracy and reliability. Therefore, the design of this self-locking component 3 achieves functional simplification, integration, and intelligence while ensuring a secure lock in the unfolded state.

[0053] See Figure 3 As shown, in one embodiment of the present invention, the locking member 31 includes a locking part, which, in the locked state, is presented as a hook, arrow, or boss for engaging with the mating sleeve 32.

[0054] It should be noted that the hook-shaped, arrow-shaped, or boss-shaped designs mentioned above all have excellent pull-out resistance. In this case, the fitting sleeve 32 is provided with a locking cavity that matches the shape of the locking part, ensuring that it remains locked when subjected to loads pointing in the separation direction in the unfolded state. Among them, the arrow-shaped configuration is conducive to achieving self-guidance and centering during the locking process, reducing the docking accuracy requirements, and generating a self-tightening effect through its wedge-shaped inclined surface after locking, resisting vibration and impact.

[0055] In one embodiment of the present invention, the locking member 31 is integrally formed with the arc-shaped shell 21 at the head end of the arc-shaped nested component 2 by 4D printing additive manufacturing.

[0056] It should be noted that by combining the locking component 31 and the arc-shaped shell 21, which serves as its base, into a single unit through continuous material growth during the same manufacturing process, the physical connection interfaces such as threads, adhesives, and interference fits inherent in traditional mechanical assembly are fundamentally eliminated. Furthermore, 4D printing technology is particularly suitable for the precision forming of advanced materials such as shape memory polymers. It can not only faithfully reproduce the complex hook-shaped, arrow-shaped, and other intricate geometric features of the locking part, but also, through precise control of the printing path and process parameters, simultaneously program the material's memory properties during manufacturing (such as setting specific shapes for the high-temperature and low-temperature phases), ensuring the consistency and predictability of product performance.

[0057] In one embodiment of the present invention, each arc-shaped shell 21 has a connecting rib 23 extending radially outward on its outer arc wall surface. The connecting rib 23 is used to connect and support the flexible thin film substrate of the solar cell.

[0058] It should be noted that the connecting rib 23 is not an independent additional component, but rather an indispensable structural extension of the arc-shaped shell 21. During the unfolding of the arc-shaped nested assembly 2, the connecting rib 23 synchronously and orderly pulls the flexible thin-film substrate from a folded state to a fully unfolded working state, ensuring the synchronicity and flatness of the thin-film substrate unfolding and avoiding the asynchronous, interference, or thin-film stress concentration problems that may arise from traditional independent support rod systems. Secondly, the radially extending connecting rib 23 and the arc-shaped shell 21 body form a stable reinforcing structure, enhancing the bending stiffness and stability of the arc-shaped shell 21. Simultaneously, it directly and efficiently transfers the loads on the thin-film substrate (such as thermal stress, vibration inertial forces, etc.) to the arc-shaped shell 21, which serves as the main load-bearing structure, and the entire nested assembly 2, resulting in a clear and concise force flow path and high structural efficiency. Furthermore, it eliminates the need for additional, independent support frames, significantly reducing the number of parts and assembly interfaces, not only reducing weight but also reducing potential assembly errors and connection failure points, thus improving overall reliability.

[0059] Furthermore, the geometric parameters (such as height and thickness) of the connecting rib 23 can be flexibly designed according to the size and stiffness requirements of the solar array. The diameter of the solar wing can be increased by lengthening the connecting rib, and a higher solar wing span-to-retraction ratio can be achieved by setting the connecting rib 23 as a foldable mast.

[0060] In one embodiment of the present invention, the arc-shaped nested component 2 includes a first arc-shaped shell, a second arc-shaped shell, a third arc-shaped shell, a fourth arc-shaped shell, a fifth arc-shaped shell, and a sixth arc-shaped shell, which are concentrically nested from the inside out. The unfolding and retraction of the arc-shaped nested component 2 are driven by the telescopic deformation of the driving member 1, and exhibit a graded chain motion.

[0061] See Figure 1 , Figure 5 and Figure 6 As shown, specifically during the deployment process: after the drive component 1 is preheated, it enters the first push stroke of the formal deployment stage. At this time, the locking component 31 is still heated, maintaining a high-temperature flat plate state. The drive component 1 is gradually heated, causing it to change shape from a compressed spiral spring at a low temperature to a stretched spiral spring at a high temperature. Since the first and sixth shells are connected to both ends of the drive component 1 respectively, and the sixth shell is the largest and outermost shell arranged from smallest to largest and fixed to the spacecraft, the sixth shell is connected to the fifth shell via a guide mating pair (mortise and tenon type), and so on, to the first shell. During the gradual stretching of the drive component 1, the slider 222 on the first shell is pushed to slide in an arc along the guide rail 221 on the second shell until the slider 222 reaches the end of the guide rail 221; this is the first push stroke. After the first push stroke, the relative positions of the first and second housings no longer change due to the push stroke limitation of the guide rail 221 and the slider 222. However, as the driving member 1 gradually stretches, the first housing is still subjected to a pushing force, which is transmitted to the second housing through the first housing. This causes the slider 222 on the second housing to slide in an arc along the guide rail 221 on the third housing until the end of the guide rail 221. This is the second push stroke. This process is repeated to divide the entire dynamic deployment mode into five push strokes. Before the first push stroke begins, the power-activated locking member 31 remains flat. After the fifth push stroke ends, heating of the locking member 31 stops, causing it to reach a low temperature and lock. The final deployment state is reached after the fifth push stroke. Before the first push stroke begins, the power-activated locking member 31 remains flat. After the fifth push stroke ends, the locking member 31 enters the mating sleeve 32, heating of the locking member 31 stops, causing it to reach a low temperature. At this time, the locking part of the locking member 31 can be arrow-shaped and matches the locking cavity shape of the mating sleeve 32. At this time, the locking member 31 and the mating sleeve 32 are locked.

[0062] During the retraction process: After the locking member 31 is released, the heating of the drive member 1 is stopped, allowing it to gradually cool down. The spiral spring, stretched at high temperature, gradually transforms into a compressed spiral spring at low temperature. Similarly, since the first and sixth housings are connected to both ends of the drive member 1, as the heated drive member 1 gradually retracts, it pulls the slider 222 on the first housing to slide in an arc along the guide rail 221 on the second housing until the slider 222 reaches the other end of the guide rail 221. This is the first return stroke. After the first return stroke, the relative positions of the first and second housings no longer change due to the return stroke limitation of the guide rail 221 and the slider 222. However, as the drive member 1 gradually retracts, the first housing is still under tension, which is transmitted to the second housing, causing the slider 222 on the second housing to slide in an arc along the guide rail 221 on the third housing until the end of the guide rail 221. This is the second return stroke. This process is repeated to divide the entire dynamic retraction mode into five return strokes.

[0063] On the other hand, the present invention also provides a spaceborne control unit, mounted on a spacecraft and communicatively connected to a ground-based master control unit. The spaceborne control unit includes a command receiving and transmitting module and a status monitoring and feedback module. The command receiving and transmitting module is used to receive control commands from the ground-based master control unit and generate drive signals according to the control commands to apply external excitation to the drive component 1 of the circular solar wing deployment and retraction mechanism as described above. The status monitoring and feedback module is used to monitor the deployment and retraction status of the arc-shaped nested component 2 of the circular solar wing deployment and retraction mechanism and send feedback signals to the ground-based master control unit. The feedback signals are used to enable the ground-based master control unit to generate updated control commands to adjust the deployment and retraction process of the arc-shaped nested component 2.

[0064] It should be noted that the command receiving and transmission module ensures that the ground control intentions can be accurately and reliably parsed and converted into excitation signals for the drive component 1 by the satellite system, realizing remote command control of the deployment and retraction actions. More importantly, the status monitoring and feedback module can acquire and report the precise deployment and retraction status of the arc-shaped nested component 2 in real time, enabling the ground master control end to make decisions based on real and timely telemetry data, rather than operating blindly. This status feedback-based control mode allows ground personnel or automatic control algorithms to assess the health of the deployment and retraction process in real time. Once an anomaly is detected, rapid intervention can be made by sending updated control commands (such as adjusting excitation parameters, pausing, or switching to retraction mode) for dynamic intervention and strategy adjustment. This effectively addresses the risks caused by space environment interference or accidental deviations of the deployment and retraction mechanism itself, improving the success rate and safety of the mission. Therefore, this onboard control unit not only achieves precise drive of the circular solar array deployment and retraction mechanism, but also, by introducing status feedback, endows the entire circular solar array with a high level of intelligence, environmental adaptability, and mission reliability. This is the core guarantee for the successful application of this lightweight, highly reliable solar array in complex space missions.

[0065] Furthermore, the present invention provides a circular solar array, including the circular solar array deployment and retraction mechanism as described above, and / or the spaceborne control unit as described above. The beneficial effects of a circular solar array on the prior art are the same as those of the circular solar array deployment and retraction mechanism or the spaceborne control unit described above, and will not be repeated here.

[0066] While the present invention has been disclosed above, its scope of protection is not limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention, and all such changes and modifications will fall within the scope of protection of the present invention.

Claims

1. A circular solar wing deployment and retraction mechanism, characterized in that, include: The driving element (1) is an integrated driving element made of shape memory material; Arc-shaped nested assembly (2), the arc-shaped nested assembly (2) includes at least two arc-shaped shells (21) that are concentrically nested in sequence through guide mating pairs. The arc-shaped shells (21) extend in an arc shape. The two ends of the driving member (1) are respectively connected to the arc-shaped shells (21) at the beginning and end of the arc-shaped nested assembly (2). Self-locking component (3), the self-locking component (3) is disposed at the end of the arc-shaped nested component (2); The driving component (1) is used to generate a stretching deformation in response to external excitation, so as to drive the arc-shaped nested component (2) so that each arc-shaped shell (21) slides relative to each other along the guide mating pair, thereby realizing the hierarchical expansion or contraction of the arc-shaped nested component (2); the self-locking component (3) is used to lock the arc-shaped nested component (2) when it is fully expanded, and when the arc-shaped nested component (2) is fully expanded, its multiple arc-shaped shells (21) together form a ring.

2. The circular solar wing deployment and retraction mechanism according to claim 1, characterized in that, The shape memory material is a bidirectional shape memory polymer; the driving member (1) changes from a first form to a second form under the external excitation to provide the unfolding driving force of the arc-shaped nested component (2); the driving member (1) returns from the second form to the first form after the external excitation is removed to provide the closing driving force of the arc-shaped nested component (2).

3. The circular solar wing deployment and retraction mechanism according to claim 2, characterized in that, The driving component (1) is an elastic member, and is one of the following: spring-shaped, negative Poisson's ratio arc-shaped push rod-shaped, or corrugated tube-shaped.

4. The circular solar panel deployment and retraction mechanism according to claim 1, characterized in that, The self-locking component (3) includes a locking element (31) and a mating sleeve (32); The locking member (31) is disposed at the head end of the arc-shaped nested assembly (2) as the unfolding propulsion end, and the mating sleeve (32) is disposed at the tail end of the arc-shaped nested assembly (2); The locking element (31) is made of a bidirectional shape memory material and is used to change between a locked and a released state in response to temperature changes in order to engage or disengage with the mating sleeve (32).

5. The circular solar panel deployment and retraction mechanism according to claim 4, characterized in that, The locking member (31) includes a locking part, which in the locked state is presented as a hook, arrow or boss for engaging with the mating sleeve (32).

6. The circular solar wing deployment and retraction mechanism according to claim 5, characterized in that, The locking element (31) is integrally formed with the arc-shaped shell (21) at the head end of the arc-shaped nesting assembly (2) by 4D printing additive manufacturing.

7. The circular solar panel deployment and retraction mechanism according to claim 1, characterized in that, The guide mating pair includes a guide rail (221) disposed on the inner side wall of the arc-shaped housing (21) and a slider (222) disposed on the outer side wall of another arc-shaped housing (21) adjacent to the arc-shaped housing (21), and the slider (222) and the guide rail (221) are in sliding fit.

8. The circular solar wing deployment and retraction mechanism according to claim 1, characterized in that, Each of the arcuate shells (21) has a connecting rib (23) extending radially outward on its outer arcuate wall surface, the connecting rib (23) being used to connect and support the flexible thin film substrate of the solar cell.

9. A spaceborne control unit, characterized in that, Mounted on the spacecraft and communicating with the ground-based main control unit, the onboard control unit includes: The instruction receiving and transmitting module is used to receive control instructions from the ground master control terminal and generate drive signals according to the control instructions to apply external excitation to the drive component (1) of the circular solar wing deployment and retraction mechanism as described in any one of claims 1 to 8. The status monitoring and feedback module is used to monitor the deployment and retraction status of the arc-shaped nested component (2) of the circular solar wing deployment and retraction mechanism, and send feedback signals to the ground main control terminal. The feedback signal is used to generate updated control commands for the ground control terminal, so as to adjust the extension and retraction process of the arc-shaped nested component (2).

10. A circular solar panel, characterized in that, It includes the circular solar array deployment and retraction mechanism as described in any one of claims 1 to 8, and / or includes the spaceborne control unit as described in claim 9.

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