Low-gravity surface folding type flexible array, antenna and unfolding method of low-gravity surface folding type flexible array

Abstract

The invention relates to a low-gravity surface folding type flexible array, an antenna and a folding and unfolding method of the low-gravity surface folding type flexible array. The device is mainly composed of a driving mechanism, a linear stretching mechanism, a folding flexible array, an antenna and a supporting structure. The driving mechanism is used for tracking the sun by the folding type flexible array, and the linear stretching mechanism is responsible for erecting and unfolding the folding type flexible array and the antenna. The folding flexible array comprises a flexible cell panel, a bottom box plate, a top box plate, a spring assembly and a flat cable, and can be kept tensioned in a low-gravity environment. The unfolding method comprises the steps that the linear stretching mechanism acts to unfold the folded flexible array and the antenna frame, and then the driving mechanism acts to rotate the flexible array and the antenna frame to a specified position. During repeated unfolding and folding, the linear stretching mechanism driving assembly provides torque, and vertical repeated unfolding and folding of the unfolding and folding truss are achieved. The device is simple in structure, has the advantages of being capable of being unfolded repeatedly, large in unfolding and folding ratio, light in weight and the like, and can be vertically unfolded reliably on the surface of a low-gravity planet and supported on a spacecraft platform.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of solar cell array and antenna, in particular to a low-gravity surface folding flexible array and antenna and a folding and unfolding method. BACKGROUND

[0002] With the development of space technology, the research and development of lunar base, lunar scientific research station, lunar space station, Mars base and the like urgently require space solar power station and communication, and spacecraft require more and more solar cell arrays and antennas. In order to receive more sunlight and erect the antenna, it is required to support the spacecraft body at a certain distance, to have a small folding envelope, a large unfolding area, a large antenna height, and to be capable of repeatedly stretching close to or away from the spacecraft body. The traditional rigid sailboard is once unfolded, has a large envelope, and does not have the capability of repeated stretching, which cannot meet the increasing demand. Therefore, it is urgently required to provide a folding flexible array and antenna which has the capability of repeated stretching, a large unfolding / folding ratio, a small folding envelope, a large unfolding area, a high antenna height, and light weight, and can reliably realize vertical unfolding and support on the spacecraft platform. SUMMARY

[0003] In view of the above technical bottleneck, the present application provides a low-gravity surface folding flexible array and antenna, comprising a driving mechanism (1), a linear stretching mechanism (2), a folding flexible array (3), an antenna (4) and a support structure (5). The driving mechanism (1) is a core power component of the whole device, and its lower end is stably connected with the spacecraft body, and its upper end is connected with the lower end of the linear stretching mechanism (2). The upper end of the linear stretching mechanism (2) is connected with the folding flexible array (3) and the antenna (4), and plays a key role in supporting and motion transmission. The support structure (5) is connected with the spacecraft body and the linear stretching mechanism (2), and the linear stretching mechanism (2) and the folding flexible array (3), respectively, to ensure the stability and reliability of the whole device. The driving mechanism (1) is used to drive the folding flexible array (3) to realize accurate tracking of the sun, so as to ensure that the flexible array can receive sunlight to the maximum extent, thereby improving the energy conversion efficiency. The linear stretching mechanism (2) is used to erect and unfold the folding flexible array (3) and the antenna (4) on the spacecraft body, so that the flexible array and the antenna can be away from the spacecraft body, obtain a better working environment and space, and facilitate the erection of the antenna and the optimization of signal transmission.

[0004] Optionally, the driving mechanism (1) comprises a driving transmission assembly (11), a fixed end (12) and a rotating end (13). The fixed end (12) is fixedly connected with the spacecraft body, so that the driving mechanism (1) can be stably supported on the spacecraft body during operation; The lower end of the driving transmission assembly (11) is connected with the fixed end (12), and the upper end is fixedly connected with the rotating end (13). The driving transmission assembly (11) provides the required torque for the rotation of the rotating end (13) through a specific transmission mechanism and power output, so as to realize the driving and attitude adjustment of the folding flexible array (3), and ensure that the flexible array can accurately track the position change of the sun to meet the energy demand of the spacecraft in different orbit positions and attitudes.

[0005] Optionally, the linear stretching mechanism (2) is composed of a driving assembly (21), a box body (22) and a folding truss (23); The box body (22) is rigidly connected with the rotating end (13) of the driving mechanism (1), so that the box body (22) can stably transmit motion and force under the action of the driving mechanism (1); The driving assembly (21) and the folding truss (23) are fixedly connected to the side and the inside of the box body (22) respectively, forming a compact and efficient power transmission and structural support system. In the initial state, the folding truss (23) is stored in the box body (22) to reduce the volume and space occupation in the folded state. When it is needed to be unfolded, the driving assembly (21) is started and provides power to drive the folding truss (23) to unfold along the vertical direction, so that the folding truss (23) extends out of the box body (22), thereby raising and unfolding the folding flexible array (3) and the antenna (4) to the predetermined working position, realizing the rapid deployment and effective work of the flexible array and the antenna.

[0006] Optionally, the folding flexible array (3) includes a flexible battery panel (31), a bottom box panel (32), a top box panel (33), a spring assembly (34) and a flat cable (35); The flexible battery panel (31) is connected by the spring assembly (34) and the flat cable (35) to form a foldable and elastic battery panel structure; The bottom box panel (32) is connected with the box body (22) of the linear stretching mechanism (2) and the flat cable (35); The top box panel (33) is connected with the folding truss (23) of the linear stretching mechanism (2) and the spring assembly (34), and the unfolding and folding of the battery panel are realized through the movement of the folding truss (23), and the spring assembly (34) is used to keep the flexible battery panel (31) in a tension state in a low-gravity environment; The flat cable (35) is used for power transmission and antenna (4) signal transmission.

[0007] In another aspect, the present application also provides a folding method for a low-gravity surface folding flexible array and antenna, which is applied to the low-gravity surface folding flexible array and antenna as claimed in any one of claims 1 to 4. In the initial state, the deployment and folding truss (23) of the linear stretching mechanism (2) is accommodated in the box body (22), the driving mechanism (1) is in the initial setting position, and the folding flexible array (3) is folded and closely attached to the bottom box plate (32) and the top box plate (33). The unfolding method comprises the following steps: S1: the linear stretching mechanism (2) is actuated, specifically, the driving assembly (21) is started and outputs power to drive the deployment and folding truss (23) to smoothly stretch out from the box body (22) along the vertical direction, to simultaneously elevate and unfold the folding flexible array (3) and the antenna (4) in the folded state to the predetermined height and position, to complete the preliminary deployment of the flexible array and the antenna in space, to create conditions for subsequent energy acquisition and signal transmission; S2: the driving mechanism (1) is actuated, specifically, the driving transmission assembly (11) is started and generates torque to drive the rotating end (13) to rotate, and then to drive the folding flexible array (3) and the antenna (4) connected thereto to rotate as a whole to the predetermined sun-facing orientation position, to ensure that the flexible battery panel (31) can face the sun direction to maximize the reception of sunlight and realize efficient energy conversion, and to ensure that the antenna (4) can perform signal transmission and reception according to the predetermined direction and attitude to meet the communication task requirements.

[0008] Optionally, the repeated deployment and folding method comprises the following steps: When the folding flexible array (3) and the antenna (4) need to be folded again, the driving assembly (21) of the linear stretching mechanism (2) is reversely actuated to output torque in the opposite direction to the deployment to drive the deployment and folding truss (23) to retract into the box body (22) along the vertical direction, to drive the folding flexible array (3) and the antenna (4) to simultaneously descend and fold until completely accommodated in the box body (22) to be in the initial folded state, to facilitate subsequent transfer, storage or re-deployment and other operations; When unfolded again, the driving assembly (21) is again actuated in the forward direction to drive the deployment and folding truss (23) to vertically stretch out of the box body (22) to elevate and unfold the folding flexible array (3) and the antenna (4) to the working position, to realize repeated use of the device, to meet the energy and communication requirements of the spacecraft in different mission stages or different working locations, to improve the flexibility and practicability of the device, and to reduce the use cost and resource consumption.

[0009] Thanks to the above technical solutions, the present application has the following beneficial effects compared with the prior art: The present application realizes the vertical unfolding and heightening of the folding flexible array and the antenna through the ingenious combination of the driving mechanism, the linear stretching mechanism and the folding flexible array, has a simple and compact structure and high integration, reduces the number of components and connection nodes, lowers the system complexity and failure risk, improves the reliability and maintainability of the system, facilitates the installation and deployment in the limited spacecraft space, and saves the valuable internal space resources of the spacecraft.

[0010] The components are combined with each other through stable connection modes, such as the connection between the driving mechanism and the spacecraft body, the connection between the linear stretching mechanism and the driving mechanism, and the connection between the folding flexible array and the linear stretching mechanism, which all adopt designs capable of ensuring reliable force transmission and attitude stability, thereby ensuring the stable work of the whole device in a low-gravity environment, avoiding failures such as energy transmission interruption and signal interference caused by problems such as structural looseness and vibration, providing a strong guarantee for the long-term stable operation of the spacecraft, and ensuring the reliable work of the solar cell array and the antenna in a complex space environment.

[0011] The linear stretching mechanism has the functions of heightening and unfolding the folding flexible array and the antenna and retracting them, and can realize repeated unfolding and retracting actions, thereby meeting the flexible configuration requirements of the energy and communication equipment of the spacecraft in different mission stages or different work sites. For example, during the landing, transfer or long-term residence of the spacecraft, the flexible array and the antenna can be unfolded or retracted at any time according to actual needs, which improves the use efficiency and flexibility of the equipment, reduces the task limitations and risks caused by the fixed and unchangeable equipment, prolongs the service life of the equipment, and reduces the configuration cost of repeated equipment.

[0012] The driving mechanism can drive the folding flexible array to track the sun, ensure that the flexible solar panel always faces the sun, thereby maximizing the reception of sunlight and improving the solar conversion efficiency, providing more sufficient energy support for the spacecraft, meeting the energy requirements of various devices on the spacecraft, and enhancing the energy autonomy and mission execution capability of the spacecraft, which is particularly important for the spacecraft in long-term on-orbit operation, and can effectively prolong the on-orbit working time.

[0013] The folding flexible array is particularly suitable for the surface of a low-gravity planet, and can be tensioned through the action of the spring assembly in a low-gravity environment, thereby ensuring the flatness and stability of the flexible solar panel, avoiding problems such as relaxation and wrinkling of the solar panel in a low-gravity environment, ensuring the power generation performance and service life of the solar panel, and also providing a good foundation for the stable work of the antenna, so that the antenna can maintain good signal transmission and reception performance, adapt to the special working conditions in a low-gravity environment, and widen the application range of the solar cell array and the antenna. BRIEF DESCRIPTION OF DRAWINGS

[0014] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following will briefly introduce the drawings needed in the embodiment description. Obviously, the drawings in the following description only constitute some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained from these drawings without any creative effort.

[0015] Fig. 1 is a schematic diagram of a low-gravity surface folded flexible array and antenna in a retracted state according to an embodiment of the present application; Fig. 2 is a schematic diagram of a low-gravity surface folded flexible array and antenna in an extended state according to an embodiment of the present application. DETAILED DESCRIPTION

[0016] The present application will be described in detail below with specific embodiments. The following embodiments will help those skilled in the art to further understand the present application, but do not limit the present application in any form. It should be noted that for those skilled in the art, without departing from the concept of the present application, a number of changes and improvements can also be made. These all belong to the protection scope of the present application.

[0017] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0018] In addition, the terms "first", "second" are only for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features defined with "first", "second" can explicitly or implicitly include one or more of the features. In the description of the present application, the meaning of "multiple" is two or more, unless otherwise specifically limited. In addition, the terms "mounting", "connecting", "connection" should be understood broadly, for example, it can be fixedly connected, or detachably connected, or integrally connected; it can be mechanically connected, or electrically connected; it can be directly connected, or indirectly connected through an intermediate medium, or the communication between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0019] Please refer to Figs. 1-2The embodiment provides a low-gravity surface folding flexible array and antenna, which is composed of a driving mechanism 1, a linear stretching mechanism 2, a folding flexible array 3, an antenna 4 and a supporting structure 5. The specific connection relationship is as follows: the lower end of the driving mechanism 1 is stably connected with the spacecraft body, and plays a role of fixed support; the upper end is connected with the lower end of the linear stretching mechanism 2, and is used for transmitting motion and force. The upper end of the linear stretching mechanism 2 is connected with the folding flexible array 3 and the antenna 4, and realizes the support and motion transmission of the flexible array and the antenna. The supporting structure 5 plays a key role in connection and stability, and connects the spacecraft body and the linear stretching mechanism 2, and ensures that the linear stretching mechanism 2 is stable and reliable in the motion process; meanwhile, the supporting structure 5 also connects the linear stretching mechanism 2 and the folding flexible array 3, and further enhances the stability of the whole device. The main function of the driving mechanism 1 is to drive the folding flexible array 3 to track the sun, so that the flexible array can always face the sun through precise rotating action, and the maximum solar energy can be obtained. The linear stretching mechanism 2 is used for erecting and unfolding the folding flexible array 3 and the antenna 4 on the spacecraft body, so that the flexible array and the antenna are far away from the spacecraft body, a better working environment and space are obtained, and the height erection of the antenna and the optimization of signal transmission are facilitated.

[0020] The driving mechanism 1 is specifically composed of a driving transmission assembly 11, a fixed end 12 and a rotating end 13. The fixed end 12 is fixedly connected with the spacecraft body, so that the driving mechanism 1 can stably rely on the spacecraft body during work. The lower end of the driving transmission assembly 11 is connected with the fixed end 12, and the upper end is fixedly connected with the rotating end 13. The driving transmission assembly 11 converts power into the rotating motion of the rotating end 13 through internal gear transmission, worm and gear transmission and other mechanical transmission modes, so as to provide the required torque for the sun orientation of the folding flexible array 3, realize the precise sun tracking function of the flexible array, and ensure the efficient utilization of solar energy.

[0021] The linear stretching mechanism 2 is composed of a driving assembly 21, a box body 22 and an unfolding and folding truss 23. The box body 22 is rigidly connected with the rotating end 13 of the driving mechanism 1, so that the box body 22 can stably transmit motion and force under the driving of the driving mechanism 1, and will not relatively displace or deform to affect the overall performance. The driving assembly 21 is installed on the side of the box body 22, and the unfolding and folding truss 23 is arranged in the interior of the box body 22. In the initial state, the unfolding and folding truss 23 is compactly stored in the interior of the box body 22, so that the volume and space occupation in the folded state are reduced, and transportation and storage are facilitated. When unfolding is needed, the driving assembly 21 starts and outputs power, drives the unfolding and folding truss 23 to stably stretch out from the box body 22 along the vertical direction through mechanical transmission modes (such as screw rod transmission, gear and rack transmission and the like), erects and unfolds the folding flexible array 3 and the antenna 4 to the predetermined working position, completes the rapid deployment of the flexible array and the antenna, and realizes the energy acquisition and signal transmission functions of the flexible array and the antenna.

[0022] The folding flexible array 3 mainly comprises a flexible battery panel 31, a bottom box panel 32, a top box panel 33, a spring assembly 34 and a flat cable 35. The flexible battery panel 31 has good flexibility and foldability, and is connected with the bottom box panel 32 and the top box panel 33 through the spring assembly 34 and the flat cable 35 to form a foldable and elastic battery panel structure. The bottom box panel 32 is connected with the box 22 of the linear stretching mechanism 2 and the flat cable 35, and plays a supporting and fixing role, and also serves as a connecting link between the battery panel and the linear stretching mechanism 2 to ensure the reliability of force transmission and signal transmission. The top box panel 33 is connected with the unfolding and folding truss 23 of the linear stretching mechanism 2 and the spring assembly 34, and the unfolding and folding of the battery panel is realized through the movement of the unfolding and folding truss 23, and the spring assembly 34 is used to keep the flexible battery panel 31 in a tensioned state in a low gravity environment to prevent the battery panel from relaxing and vibrating during work and affecting the performance. The flat cable 35 is used for power transmission and signal transmission of the antenna 4, and the unique flat structure design can adapt to the folding and unfolding of the flexible array while ensuring the signal transmission efficiency and reliability, avoiding cable winding and excessive stretching during movement, and ensuring the normal operation of the entire system.

[0023] The embodiment provides a folding flexible array and antenna unfolding method on a low gravity surface.

[0024] In the initial state, the unfolding and folding truss 23 of the linear stretching mechanism 2 is accommodated in the box 22, the driving mechanism 1 is in the initial set position, and the folding flexible array 3 is folded and closely attached to the bottom box panel 32 and the top box panel 33. The specific steps of the unfolding method are as follows: S1: The linear stretching mechanism 2 is actuated. After receiving the unfolding instruction, the driving assembly 21 is started to begin outputting power. The driving assembly 21 transmits power to the unfolding and folding truss 23 through internal transmission mechanisms such as motor driving screw rotation, nut movement along the screw, etc. to drive the unfolding and folding truss 23 to smoothly extend from the box 22 in the vertical direction. During the extension of the unfolding and folding truss 23, the folding flexible array 3 and the antenna 4 in the folded state are gradually elevated and unfolded to a predetermined height and position, and the preliminary deployment of the flexible array and the antenna in space is completed. At this time, the flexible battery panel 31 of the folding flexible array 3 is initially tensioned under the action of the spring assembly 34 to prepare for subsequent energy acquisition; the antenna 4 also leaves the box 22 and enters the predetermined initial working position along with the lifting of the unfolding and folding truss 23, and has basic signal receiving and transmitting capability.

[0025] S2: the driving mechanism 1 is in action. When the folding flexible array 3 and the antenna 4 are elevated to the predetermined position, the driving transmission assembly 11 of the driving mechanism 1 is started and generates torque. The fixed end 12 is firmly fixed on the spacecraft body, ensuring that the entire driving mechanism 1 is stable during the operation. The torque generated by the driving transmission assembly 11 drives the rotation of the rotating end 13 through the transmission between the fixed end 12 and the rotating end 13. The rotation of the rotating end 13 further drives the rotation of the linear stretching mechanism 2, the folding flexible array 3 and the antenna 4 as a whole around the rotation axis of the driving mechanism 1. By accurately controlling the torque output and rotation angle of the driving transmission assembly 11, the folding flexible array 3 and the antenna 4 are rotated to the specified sun-oriented position. At this time, the flexible battery panel 31 can face the sun direction and maximize the reception of sunlight, achieving efficient solar energy conversion and providing sufficient energy for the spacecraft; the antenna 4 is also adjusted to the best signal receiving and transmitting direction and attitude, ensuring the stability of the communication link and the good signal quality, meeting the communication and other task requirements of the spacecraft.

[0026] The specific steps of the repeated folding and unfolding method are as follows: Folding process: when the folding flexible array 3 and the antenna 4 need to be folded, the driving assembly 21 of the linear stretching mechanism 2 receives the folding instruction and reverses the action, outputting torque in the opposite direction to that during unfolding. The driving assembly 21 drives the folding and unfolding truss 23 to retract into the box body 22 along the vertical direction through the internal transmission mechanism. During the retraction process, the folding and unfolding truss 23 drives the folding flexible array 3 and the antenna 4 to descend and fold synchronously. The flexible battery panel 31 of the folding flexible array 3 gradually relaxes and finally adheres to the bottom box plate 32 and the top box plate 33 during the folding process, completing the folding action; the antenna 4 also returns to the initial folding position inside the box body 22 along with the descent of the folding and unfolding truss 23. The entire folding process is stable and orderly, and the components cooperate closely, ensuring that the device is compact in size after folding, facilitating subsequent transfer, storage or re-unfolding operations, and avoiding problems such as collision and damage of components during the folding process.

[0027] Unfolding process: if the folding flexible array 3 and the antenna 4 need to be unfolded again, the driving assembly 21 receives the unfolding instruction again and acts in the forward direction, driving the folding and unfolding truss 23 to vertically extend out of the box body 22 according to the same principle and method as the previous unfolding process. During the extension process, the folding and unfolding truss 23 elevates and unfolds the folding flexible array 3 and the antenna 4 to the working position, causing the flexible battery panel 31 to be tensioned again and start energy acquisition, and the antenna 4 to return to the best signal receiving and transmitting state, realizing the repeated use of the device and meeting the energy and communication needs of the spacecraft in different mission stages or different working locations, improving the flexibility and practicality of the device and reducing the task cost and resource consumption.

[0028] The specific examples are used in the description of the application to provide a thorough understanding of the application. The above embodiments are only used to help understand the core idea of the application. It should be pointed out that, for those skilled in the art, any obvious modifications, equivalent replacements or other improvements made without departing from the inventive concept should be included in the protection scope of the application.

[0029] Other embodiments of the application will be apparent to those skilled in the art from consideration of the specification and practice of the application disclosed herein. It is intended that the specification and examples be considered as exemplary only, with the true scope and spirit of the application being indicated by the following claims.

[0030] It should be understood that the application is not limited to the precise construction that has been described above and illustrated in the accompanying drawings, and that various modifications and changes can be made by those skilled in the art without departing from the scope of the application. The scope of the application is limited only by the appended claims.

[0031] It should be understood that "multiple" referred to herein means two or more. "And / or", which describes the association relationship of associated objects, means that there can be three relationships, for example, A and / or B can represent the following three cases: A exists alone, A and B exist together, and B exists alone. The character " / " generally represents that the associated objects before and after it are in an "or" relationship.

[0032] Those of ordinary skill in the art can understand that all or part of the steps of the above-mentioned embodiments can be completed by hardware, or by program instructions instructing relevant hardware to complete, and the program can be stored in a computer readable storage medium. The storage medium mentioned above can be a read-only memory, a magnetic disk or an optical disk, etc.

[0033] The above is only the preferred embodiment of the application, and is not used to limit the application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the application should be included in the protection scope of the application.

Claims

1. A low-gravity surface-folded flexible array and antenna, characterized by: It comprises a driving mechanism (1), a linear stretching mechanism (2), a folding flexible array (3), an antenna (4) and a supporting structure (5); The driving mechanism (1) is the core power component of the whole device, and its lower end is stably connected with the spacecraft body, and its upper end is connected with the lower end of the linear stretching mechanism (2); The upper end of the linear stretching mechanism (2) is connected with the folding flexible array (3) and the antenna (4), and plays a key role in supporting and motion transmission; the supporting structure (5) is connected with the spacecraft body and the linear stretching mechanism (2), and the linear stretching mechanism (2) and the folding flexible array (3) respectively, to ensure the stability and reliability of the whole device; The driving mechanism (1) is used to drive the folding flexible array (3) to realize accurate tracking of the sun, so as to ensure that the flexible array can maximize the reception of sunlight, thereby improving the energy conversion efficiency; The linear stretching mechanism (2) is used to erect and deploy the folding flexible array (3) and the antenna (4) on the spacecraft body, so that the flexible array and the antenna can be away from the spacecraft body, obtain a better working environment and space, and facilitate the erection of the antenna and the optimization of signal transmission.

2. The low-gravity surface-folded flexible array and antenna of claim 1, wherein: The driving mechanism (1) comprises a driving transmission assembly (11), a fixed end (12) and a rotating end (13); The fixed end (12) is fixedly connected with the spacecraft body, so that the driving mechanism (1) can stably rely on the spacecraft body during operation; The lower end of the driving transmission assembly (11) is connected with the fixed end (12), and the upper end is fixedly connected with the rotating end (13); the driving transmission assembly (11) provides the required torque for the rotation of the rotating end (13) through a specific transmission mechanism and power output, so as to realize the driving and attitude adjustment of the folding flexible array (3), and ensure that the flexible array can accurately track the position change of the sun to meet the energy demand of the spacecraft in different orbit positions and attitudes.

3. The low-gravity surface-folded flexible array and antenna of claim 1, wherein: The linear stretching mechanism (2) comprises a driving assembly (21), a box body (22) and a deployment and folding truss (23); The box body (22) is rigidly connected with the rotating end (13) of the driving mechanism (1), so that the box body (22) can stably transmit motion and force under the action of the driving mechanism (1); The driving assembly (21) and the deployment and folding truss (23) are fixedly connected to the side and the inside of the box body (22) respectively, forming a compact and efficient power transmission and structure support system; in the initial state, the deployment and folding truss (23) is stored in the box body (22) to reduce the volume and space occupation in the folded state; when it needs to be unfolded, the driving assembly (21) starts and provides power to drive the deployment and folding truss (23) to unfold along the vertical direction, so that the deployment and folding truss (23) extends out of the box body (22), thereby erecting and deploying the folding flexible array (3) and the antenna (4) to the predetermined working position, realizing the rapid deployment and effective work of the flexible array and the antenna.

4. The low-gravity surface-folded flexible array and antenna of claim 1, wherein: The folding flexible array (3) comprises a flexible battery panel (31), a bottom box panel (32), a top box panel (33), a spring assembly (34) and a flat cable (35); The flexible battery panel (31) is connected by the spring assembly (34) and the flat cable (35) to form a foldable and elastic battery panel structure; The bottom box panel (32) is connected with the box (22) of the linear stretching mechanism (2) and the flat cable (35); The top box panel (33) is connected with the unfolding and folding truss (23) of the linear stretching mechanism (2) and the spring assembly (34), and the unfolding and folding of the battery panel is realized by the movement of the unfolding and folding truss (23), and the flexible battery panel (31) is kept in a tension state in a low gravity environment by the elastic action of the spring assembly (34); The flat cable (35) is used for realizing power transmission and antenna (4) signal transmission.

5. A method of deploying and stowing a low-gravity surface-folded flexible array and antenna, comprising: The folding flexible array and antenna are applied to the low gravity surface folding flexible array and antenna in any one of claims 1 to 4, in an initial state, the unfolding and folding truss (23) of the linear stretching mechanism (2) is accommodated in the box (22), the driving mechanism (1) is in an initial setting position, the folding flexible array (3) is folded and closely attached to the bottom box panel (32) and the top box panel (33); the unfolding method comprises the following steps: S1: the linear stretching mechanism (2) is actuated, specifically, the driving assembly (21) is started and outputs power to drive the unfolding and folding truss (23) to smoothly stretch out from the box (22) along the vertical direction, to simultaneously elevate and unfold the folding flexible array (3) and the antenna (4) in the folded state to a predetermined height and position, to complete the preliminary deployment of the flexible array and the antenna in space, to create conditions for subsequent energy acquisition and signal transmission; S2: the driving mechanism (1) is actuated, that is, the driving transmission assembly (11) is started and generates torque to drive the rotating end (13) to rotate, and then the folding flexible array (3) and the antenna (4) connected thereto are rotated as a whole to a predetermined sun-facing orientation position, to ensure that the flexible battery panel (31) can face the sun direction to maximize the reception of sunlight and realize efficient energy conversion, and to ensure that the antenna (4) can perform signal transmission and reception according to a predetermined direction and attitude to meet the communication task requirements.

6. The method of deploying and stowing a low-gravity surface-folded flexible array and antenna of claim 5, wherein: The repeated unfolding and folding method comprises the following steps: When the folding flexible array (3) and the antenna (4) need to be folded again, the driving assembly (21) of the linear stretching mechanism (2) is reversely actuated to output torque in the opposite direction to the unfolding to drive the unfolding and folding truss (23) to retract into the box (22) along the vertical direction, to drive the folding flexible array (3) and the antenna (4) to simultaneously descend and fold until completely accommodated in the box (22) to be in an initial folded state, to facilitate subsequent transfer, storage or re-unfolding operation; When unfolded again, the driving assembly (21) is actuated again to drive the unfolding and folding truss (23) to vertically stretch out of the box (22) to elevate and unfold the folding flexible array (3) and the antenna (4) to a working position.

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