Satellite reel-type flexible solar wing deployment and retraction device

Abstract

The present invention relates to a satellite reel-type flexible solar wing deployment and collection device, comprising: a flexible solar wing assembly, including a solar wing reel, a flexible solar cell array and a support assembly, wherein the solar wing reel is used to roll up the flexible solar cell array, and the support assembly is connected to the flexible solar cell array; a flexible deployment and collection assembly, connected to the support assembly, the flexible deployment and collection assembly comprises a stretching arm, a stretching arm reel and an active drive roller, the stretching arm reel is used to roll up the stretching arm, the active drive roller is in contact with the surface of the stretching arm, the active drive roller can drive the stretching arm to gradually unfold from a rolled state and curl into a conical rod, and can drive the flexible solar cell array to unfold during the unfolding of the stretching arm; a shell, used to accommodate the flexible solar wing assembly and the flexible deployment and collection assembly; a drive assembly, arranged on the shell. The present invention has the advantages of high lightness, high power-to-weight ratio and strong versatility.

Description

Technical Field

[0001] The present invention mainly relates to the technical field of deployable structures in aerospace space, and in particular to a satellite reel-type flexible solar wing deployment and retraction device. Background Art

[0002] Spacecraft is the carrier for human deep space exploration, near-Earth asteroid exploration and other missions. Its energy sources mainly include chemical energy, nuclear energy and solar energy, among which solar energy is the most widely used energy source at present, and space solar array is the core power supply equipment of spacecraft. With the increasing number of human space activities, the expansion of space exploration missions and the increase of payload, the demand for electricity of spacecraft is increasing day by day, which will lead to a significant increase in the mass and envelope space of the currently widely used rigid solar wings, which cannot meet the "lightweight and miniaturization" requirements of large-scale launch and deployment of low-orbit satellites.

[0003] The aerospace technology field has begun to explore and apply flexible solar cell array technology. Compared with traditional rigid solar wings, flexible solar cell arrays have significant advantages such as light weight, small folded volume, and high storage ratio, showing great potential for the development of high-power solar wings in the future. At present, most spacecraft are still using relatively mature rigid solar wings and foldable flexible solar wings. The existing large rigid solar wings and foldable flexible solar wings have low expansion and contraction ratios and large weight and volume.

[0004] The roll-up flexible solar wing has a large power-to-weight ratio and can be deployed and retracted repeatedly, which can provide strong support for spacecraft to perform more complex space exploration missions. At present, the on-orbit deployment and retraction design of the roll-up flexible solar wing is still insufficient, especially in terms of lightweight design, which has not reached the ideal level, and has the problems of low lightweight degree and low deployment and retraction ratio. Summary of the invention

[0005] The technical problem to be solved by the present application is to provide a satellite reel-type flexible solar wing deployment and retraction device, which has the advantages of high lightness, high power-to-weight ratio, and strong versatility. The satellite reel-type flexible solar wing deployment and retraction device has a high deployment and retraction ratio and a small weight and volume, and can meet the high mass-to-power and volume-to-power requirements of the satellite solar array for the future constellation construction of "multiple satellites in one rocket".

[0006] The technical solution adopted by the present application to solve the above-mentioned technical problems is a satellite reel-type flexible solar wing deployment and retraction device, comprising: a flexible solar wing assembly, including a solar wing reel, a flexible solar cell array and a support assembly, the solar wing reel is used to wind up the flexible solar cell array, and the support assembly is connected to the flexible solar cell array; a flexible deployment and retraction assembly, connected to the support assembly, the flexible deployment and retraction assembly comprises an extension arm, an extension arm reel and an active drive roller, the extension arm reel is used to wind up the extension arm, the active drive roller is in contact with the surface of the extension arm, the active drive roller can drive the extension arm to gradually unfold from a wound state and curl into a conical rod, and can drive the flexible solar cell array to unfold during the unfolding process of the extension arm; a shell, used to accommodate the flexible solar wing assembly and the flexible deployment and retraction assembly; a drive assembly, arranged on the shell, the drive assembly is used to drive the solar wing reel to rotate, drive the extension arm reel to rotate, and drive the active drive roller to rotate.

[0007] In one embodiment of the present application, the flexible solar wing assembly further includes a first bearing assembly, which is respectively arranged at both ends of the solar wing reel, and the first bearing assembly includes a self-lubricating radial spherical bearing.

[0008] In one embodiment of the present application, the support assembly includes: a connecting rope, a hanging bracket, a first hook, an elastic member and a battery array hanging plate. The flexible solar cell array is connected to the battery array hanging plate through the connecting rope, and the battery array hanging plate is connected to the hanging bracket through the elastic member. The first hook is arranged at the top of the hanging bracket.

[0009] In one embodiment of the present application, the flexible expansion and contraction assembly also includes a tensioning wheel, a coil spring and a driven pressure roller. The driven pressure roller is in contact with the surface of the extension arm, and the driven pressure roller and the active drive roller are used to guide and press the extension arm to store strain energy; the surfaces of the tensioning wheel and the extension arm are in contact with each other, the coil spring is connected to the tensioning wheel, and the coil spring is used to provide pressure to the tensioning wheel to press the extension arm.

[0010] In one embodiment of the present application, the flexible expansion and contraction assembly also includes a second bearing assembly, a third bearing assembly and a fourth bearing assembly, the second bearing assembly is respectively arranged at both ends of the extension arm reel; the third bearing assembly is respectively arranged at both ends of the driven pressure roller; the fourth bearing assembly is respectively arranged at both ends of the active drive roller.

[0011] In one embodiment of the present application, the flexible deployment assembly further includes a cantilever bracket, the cantilever bracket is connected to the top end of the extension arm, a second hook is provided on the cantilever bracket, and the second hook is connected to the support assembly.

[0012] In one embodiment of the present application, the shell includes a box assembly, the box assembly includes a hollow first chamber and a second chamber, the first chamber is used to accommodate the flexible solar wing assembly, and the second chamber is used to accommodate the flexible deployment assembly.

[0013] In one embodiment of the present application, the shell also includes a box cover assembly, which is connected to the box body assembly, and is provided with an extension groove, an extension hole and a clamping device. The flexible solar cell array can extend outward through the extension groove; the extension arm can extend outward through the extension hole; the clamping device is connected to the extension arm, and the clamping device is used to clamp the extension arm after the extension arm is unfolded or rolled into place.

[0014] In one embodiment of the present application, a first travel switch is provided on the clamping device, and the first travel switch is used to send a first prompt signal after the extension arm is unfolded or rolled into place; a second travel switch is provided on the extension groove, and the second travel switch is used to send a second prompt signal after the flexible solar cell array is unfolded or rolled into place.

[0015] In one embodiment of the present application, the driving assembly includes an ultrasonic motor and a coupling, there are multiple driving assemblies, and the driving assemblies are connected to the solar wing reel, the extension arm reel, and the active drive roller in a one-to-one correspondence.

[0016] The technical solution of the present application can maintain the stability of the flexible solar cell array when it is deployed in orbit by connecting the support assembly and the flexible solar cell array; the rollable extension arm cooperates with the active drive roller to achieve a smooth transition of the extension arm from a rolled state to a tapered rod, thereby driving the effective deployment of the flexible solar cell array, simplifying the deployment process, and improving the reliability and efficiency of deployment; by accommodating the flexible solar wing assembly and the flexible deployment assembly in a protective shell, the entire deployment device can be miniaturized to facilitate launch into orbit. Before the satellite is launched, the flexible solar cell array is in a rolled-up state and has a small rolled-up volume. After the satellite enters orbit, the flexible solar cell array can be deployed under the action of the flexible deployment assembly, and the deployment process is controllable. The deployed length of the flexible solar cell array is not less than 20 meters, and it has a certain rigidity after deployment. The flexible solar cell array can be rolled up under the action of the flexible deployment assembly to achieve repeated deployment.

[0017] This application adopts a parallel modular design, which can effectively utilize the installation space compared to the series design, while minimizing the number of mechanical components. It has a simple structure, high reliability, and strong versatility, and can realize repeated deployment and retraction of satellite solar wings; this application adopts a rolled-up flexible solar cell array, which is small in size when rolled up, and can be unfolded into a large-area solar cell array after the satellite enters orbit to ensure the satellite's high-power electricity needs; the extension arm of this application can be made of composite material shape memory polymer, and the extension arm adopts a conical variable cross-section design. After being deployed in place, the largest diameter surface is locked to ensure the deployment stiffness requirements and avoid buckling instability. The overall structure of the deployment and retraction device of this application is miniaturized and lightweight. Through a rocket launch mission, multiple satellites equipped with deployment and retraction devices can be sent into orbit at the same time, thereby meeting the large-scale launch and deployment needs of "one rocket, multiple satellites". BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, the specific implementation methods of the present application are described in detail below with reference to the accompanying drawings, wherein:

[0019] Figure 1 This is a schematic diagram of the overall structure of a satellite reel-type flexible solar wing deployment and retraction device according to an embodiment of the present application;

[0020] Figure 2 is a schematic diagram of a flexible solar wing assembly in an embodiment of the present application;

[0021] Figure 3 is a schematic diagram of a bearing assembly in one embodiment of the present application;

[0022] Figure 4 is a schematic diagram of a flexible deployment assembly in an embodiment of the present application;

[0023] Figure 5 is a schematic diagram of a box cover assembly in one embodiment of the present application;

[0024] Figure 6 is a schematic diagram of a box assembly in one embodiment of the present application;

[0025] Figure 7 It is a schematic diagram of a satellite reel-type flexible solar wing deployment and retraction device in a retracted state in one embodiment of the present application;

[0026] Figure 8 It is a schematic diagram of the unfolded state of a satellite roll-up flexible solar wing unfolding and retracting device in one embodiment of the present application.

[0027] Description of the accompanying drawings in the specific implementation manner:

[0028] 1. Flexible solar wing assembly; 100. Support assembly; 101. Solar wing reel; 102. First bearing assembly; 103. Flexible solar cell array; 104. Connecting rope; 105. Suspension bracket; 106. First hook; 107. Elastic member; 108. Solar array hanging plate; 2. Flexible unfolding and retracting assembly; 201. Extension arm; 202. Extension arm reel; 203. Tensioning wheel; 204. Coil spring; 205. Driven pressing roller; 206. Active driving roller; 207. Cantilever bracket; 208. Second hook; 209. Second bearing assembly; 210. Third bearing assembly; 211. Fourth bearing assembly; 3. Box cover assembly; 300. Shell; 301. Extension groove; 302. Extension hole; 303. Clamping device; 4. Box assembly; 401. First chamber; 402. Second chamber; 5. First drive assembly; 6. Second drive assembly; 7. Third drive assembly; 800. Drive assembly. DETAILED DESCRIPTION

[0029] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, the specific implementation methods of the present application are described in detail below with reference to the accompanying drawings.

[0030] In the following description, many specific details are set forth to facilitate a full understanding of the present application, but the present application may also be implemented in other ways different from those described herein, and therefore the present application is not limited to the specific embodiments disclosed below.

[0031] As shown in this application and claims, unless the context clearly indicates an exception, the words "a", "an", "an" and / or "the" do not refer to the singular and may also include the plural. Generally speaking, the terms "include" and "comprise" only indicate the inclusion of the steps and elements that have been clearly identified, and these steps and elements do not constitute an exclusive list. The method or device may also include other steps or elements.

[0032] In the description of the present application, it should be understood that the directions or positional relationships indicated by directional words such as "front, back, up, down, left, right", "lateral, vertical, perpendicular, horizontal" and "top, bottom" are usually based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description. Unless otherwise specified, these directional words do not indicate or imply that the device or element referred to must have a specific direction or be constructed and operated in a specific direction, and therefore cannot be understood as limiting the scope of protection of the present application; the directional words "inside and outside" refer to the inside and outside relative to the contours of each component itself.

[0033] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0034] In addition, it should be noted that the use of words such as "first" and "second" to define components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above words have no special meaning and cannot be understood as limiting the scope of protection of this application. In addition, although the terms used in this application are selected from well-known and commonly used terms, some terms mentioned in the specification of this application may be selected by the applicant at his or her discretion, and their detailed meanings are explained in the relevant parts of the description of this article. In addition, it is required to understand this application not only by the actual terms used, but also by the meaning implied by each term.

[0035] The following describes the embodiments of the present application based on the accompanying drawings. However, the embodiments shown below are examples of satellite reel-type flexible solar wing deployment and retraction devices for embodying the technical ideas of the present application, and the satellite reel-type flexible solar wing deployment and retraction devices of the present application are not specific to the following contents. Furthermore, in order to facilitate the understanding of the scope of the claims, this specification assigns numbers corresponding to the components shown in the embodiments to the components shown in the "Claims" and "Contents of the Invention" columns. However, the components shown in the claims are by no means specified as the components of the embodiments. In particular, the size, material, shape, and relative configuration of the constituent components recorded in the embodiments, if there is no specific record, is not intended to limit the scope of the present application to only these, but is only an illustrative example.

[0036] However, the dimensions or positional relationships of the components shown in the drawings are sometimes exaggerated for the purpose of clarifying the description. Furthermore, in the following description, for the same names and symbols, representing the same or homogeneous components, it is appropriate to omit their detailed description. Furthermore, the various elements constituting the present application may be in the form of a plurality of elements constituted by the same components so that one component serves as a plurality of elements, or conversely, it may be realized by a plurality of components sharing the function of a component. In addition, the contents described in some embodiments and implementation methods may also be utilized in other embodiments, implementation methods, etc. In addition, in this specification, "on" is not limited to the case where it is formed in contact with the upper surface, but also includes the case where it is formed separately on the upper surface, and is also used to include the meaning of the existence of an intervening layer between layers.

[0037] The present application proposes a satellite roll-up flexible solar wing deployment and retraction device, which can be used in scenarios where there is a need for small and lightweight, and can be deployed or retracted in orbit after being launched into orbit.

[0038] Figure 1 is a schematic diagram of the overall structure of a satellite reel-type flexible solar wing deployment and retraction device according to an embodiment of the present application, Figure 2 is a schematic diagram of a flexible solar wing assembly in an embodiment of the present application, Figure 4 Schematic diagram of a flexible deployment assembly in an embodiment of the present application. Figure 1, Figure 2 and Figure 4 As shown, the satellite roll-up flexible solar wing deployment and retraction device of this embodiment includes: a flexible solar wing assembly 1, including a solar wing reel 101, a flexible solar cell array 103 and a support assembly 100, the solar wing reel 101 is used to wind up the flexible solar cell array 103, and the support assembly 100 is connected to the flexible solar cell array 103; a flexible deployment and retraction assembly 2, connected to the support assembly 100, the flexible deployment and retraction assembly 2 includes an extension arm 201, an extension arm reel 202 and an active drive roller 206, the extension arm reel 202 is used to wind up the extension arm 201, the active drive roller 206 is in contact with the surface of the extension arm 201, the active drive roller 206 can drive the extension arm 201 to gradually unfold from a wound state and curl into a conical rod, and can drive the flexible solar cell array 103 to unfold during the unfolding process of the extension arm 201.

[0039] Figure 7 Schematic diagram of the satellite reel-type flexible solar wing deployment and retraction device in the retracted state in one embodiment of the present application. Figure 1 and Figure 7 As shown, the satellite reel-type flexible solar wing deployment and retraction device further includes: a housing 300 for accommodating the flexible solar wing assembly 1 and the flexible deployment and retraction assembly 2; a driving assembly 800, which is arranged on the housing 300, and is used to drive the solar wing reel 101 to rotate, the extension arm reel 202 to rotate, and the active drive roller 206 to rotate. Exemplarily, the flexible solar cell array 103 may adopt a thin film structure (i.e., a flexible thin film solar cell array), or adopt other bendable and retractable structures, and the present application does not limit the type of the flexible solar cell array 103.

[0040] refer to Figure 1 and Figure 4 As shown, for example, the extension arm 201 of the present application can be made of a composite material, Shape Memory Polymer Composites (SMPC). In order to take into account both the light weight and the rigidity requirements after deployment, the extension arm 201 can be designed as a variable cross-section open thin-walled tube, that is, Figure 4 The tapered variable cross-section design shown in the figure can also be called a "C-shaped" rod design. After the extension arm 201 is deployed, the largest diameter surface is locked with the box cover assembly 3, which can ensure the rigidity requirement when deployed; the extension arm 201 is wound on the extension arm reel 202 in an undeformed state, thereby storing strain energy for deformation.

[0041] The technical solution of the present application can maintain the stability of the flexible solar cell array 103 when it is deployed in orbit by connecting the support assembly 100 and the flexible solar cell array 103; the rollable extension arm 201 cooperates with the active drive roller 206 to achieve a smooth transition of the extension arm 201 from a rolled state to a conical rod, thereby driving the effective deployment of the flexible solar cell array 103, simplifying the deployment process, and improving the reliability and efficiency of deployment; by accommodating the flexible solar wing assembly 1 and the flexible deployment assembly 2 in a protective shell 300, the entire deployment device can be miniaturized to facilitate launch into orbit.

[0042] refer to Figure 7 As shown, before the satellite is launched, the flexible solar cell array 103 is in a rolled-up state and has a small rolled-up volume. Figure 8 Schematic diagram of the satellite reel-type flexible solar wing deployment device in the unfolded state in one embodiment of the present application, with reference to Figure 8 As shown, after the satellite enters orbit, the flexible solar cell array 103 can be unfolded under the action of the flexible unfolding and retracting assembly 2, and the unfolding process is controllable. The unfolded length of the flexible solar cell array 103 is not less than 20 meters, and has a certain rigidity after unfolding. The flexible solar cell array 103 can be rolled up under the action of the flexible unfolding and retracting assembly 2 to achieve repeated unfolding and retracting.

[0043] The present application adopts a parallel modular design, which can effectively utilize the installation space compared to the series design, while minimizing the number of mechanical components. It has a simple structure, high reliability, and strong versatility, and can realize repeated deployment and retraction of satellite solar wings. The present application adopts a rolled-up flexible solar cell array 103, which has a small volume in the rolled-up state and can be unfolded into a large-area solar cell array after the satellite enters orbit to ensure the satellite's high-power electricity needs. The extension arm 201 of the present application can be made of a composite material shape memory polymer. The extension arm 201 adopts a conical variable cross-section design. After being deployed into place, the surface with the largest diameter is locked to ensure the deployment stiffness requirements and avoid buckling instability.

[0044] The overall structure of the deployment and collection device of the present application is miniaturized and lightweight. Through a single rocket launch mission, multiple satellites equipped with deployment and collection devices can be sent into orbit at the same time, thereby meeting the large-scale launch and deployment needs of "multiple satellites in one rocket".

[0045] Figure 3 Schematic diagram of a bearing assembly in one embodiment of the present application. Figure 2 and Figure 3 As shown, in some embodiments, the flexible solar wing assembly 1 further includes a first bearing assembly 102, and the first bearing assembly 102 is respectively arranged at both ends of the solar wing reel 101, and the first bearing assembly 102 includes a self-lubricating radial spherical bearing.

[0046] For example, in order to achieve a large expansion-contraction ratio of the solar cell array, the span of the solar wing reel 101 can be set larger. When the space environment has an uneven temperature field along the axis direction and produces a temperature gradient, it is inevitable that the coaxiality deviation at both ends of the solar wing reel 101 will occur, which can easily cause the traditional rolling bearing to get stuck. In this application, the first bearing assembly 102 is set as a self-lubricating radial spherical bearing, such as Figure 3 As shown, the self-lubricating radial spherical plain bearing can bear radial force and axial force at the same time, and has the characteristics of large load capacity, good temperature adaptability, impact resistance, corrosion resistance, wear resistance, self-aligning, self-lubrication, etc., which can effectively avoid bearing seizure.

[0047] refer to Figure 2 As shown, in some embodiments, the support assembly 100 includes: a connecting rope 104, a hanging bracket 105, a first hook 106, an elastic member 107 and a battery array hanging plate 108, the flexible solar cell array 103 is connected to the battery array hanging plate 108 through the connecting rope 104, the battery array hanging plate 108 is connected to the hanging bracket 105 through the elastic member 107, and the first hook 106 is arranged at the top of the hanging bracket 105. Exemplarily, the connecting rope 104 can be a steel wire rope or other metal rope. The elastic member 107 can be a spring, an elastic rope, an elastic band, etc. The connection method of the support assembly 100 and the flexible solar cell array 103 of the present application can ensure that the flexible solar cell array 103 is evenly stressed during the unfolding process and does not deform.

[0048] Here, an example is used to illustrate the composition of the flexible solar wing assembly 1.

[0049] refer to Figure 2 As shown, the flexible solar cell array 103 is wound on the solar wing reel 101, and the top of the flexible solar cell array 103 and the bottom of the battery array hanging plate 108 are both provided with buckles (not shown in the figure), and the connecting rope 104 (such as a steel wire rope) passes through the buckle to connect the flexible solar cell array 103 and the battery array hanging plate 108. The top of the battery array hanging plate 108 and the bottom of the suspension bracket 105 are both provided with threaded holes (not shown in the figure), and the two ends of the elastic member 107 (such as a spring) connect the battery array hanging plate 108 and the suspension bracket 105 through threads. The top of the suspension bracket 105 has a threaded hole (not shown in the figure) connected to the first hook 106. A first bearing assembly 102 (such as a self-lubricating radial spherical bearing) is respectively provided at both ends of the solar wing reel 101. The above components are connected in the above manner to form a flexible solar wing assembly 1.

[0050] refer to Figure 4As shown, in some embodiments, the flexible stowage assembly 2 also includes a tensioning wheel 203, a coil spring 204 and a driven pressure roller 205. The driven pressure roller 205 is in contact with the surface of the extension arm 201. The driven pressure roller 205 and the active drive roller 206 are used to guide and press the extension arm 201 to store strain energy (the strain energy is used to deform the sheet-like extension arm into a cone); the tensioning wheel 203 is in contact with the surface of the extension arm 201, the coil spring 204 is connected to the tensioning wheel 203, and the coil spring 204 is used to provide pressure to the tensioning wheel 203 to press the extension arm 201.

[0051] Exemplarily, the driven clamping roller 205 and the active driving roller 206 can simultaneously realize the functions of driving the extension arm 201 to unfold and guiding the clamping. The front end of the extension arm 201 can apply strain energy to the undeformed part of the extension arm 201 again through the driven clamping roller 205 and the active driving roller 206, so as to ensure that the strain energy of the extension arm 201 is released smoothly after passing through the driven clamping roller 205 and the active driving roller 206, and can become a "C-shaped" rod with a smaller opening after deformation. The tensioning wheel 203 relies on the coil spring 204 to provide pressure, so that the extension arm 201 can be kept tightly wound on the extension arm reel 202 during the extension and retraction process, ensuring that its strain energy is not released prematurely.

[0052] Continue to refer Figure 4 As shown, in some embodiments, the flexible stowage assembly 2 further includes a second bearing assembly 209, a third bearing assembly 210 and a fourth bearing assembly 211, wherein the second bearing assembly 209 is respectively arranged at both ends of the extension arm reel 202; the third bearing assembly 210 is respectively arranged at both ends of the driven pressing roller 205; and the fourth bearing assembly 211 is respectively arranged at both ends of the active driving roller 206. Exemplarily, the second bearing assembly 209, the third bearing assembly 210 and the fourth bearing assembly 211 can be adopted as follows Figure 3 The self-lubricating radial spherical plain bearing shown in the figure. The present application does not limit the specific types of the first bearing assembly 102 , the second bearing assembly 209 , the third bearing assembly 210 and the fourth bearing assembly 211 .

[0053] In some embodiments, the flexible stowage assembly 2 further includes a cantilever bracket 207, the cantilever bracket 207 is connected to the top of the extension arm 201, and a second hook 208 is provided on the cantilever bracket 207, and the second hook 208 is connected to the support assembly 100. Exemplarily, the present application connects the second hook 208 to the first hook 106 of the support assembly 100, and during the process of the extension arm 201 being extended, the flexible solar cell array 103 can be synchronously driven to extend.

[0054] Here, an example is used to illustrate the composition of the flexible deployment component 2.

[0055] refer to Figure 4As shown, the extension arm 201 is wound on the extension arm reel 202 in an undeformed state, thereby storing strain energy. The tension wheel 203 provides pressure through the coil spring 204 installed thereon, and can always keep the extension arm 201 in the retracted state pressed during the retracting process to ensure that its strain energy is not released prematurely. The front end of the extension arm 201 applies strain energy to the undeformed part of the extension arm 201 again through the driven pressing roller 205 and the active driving roller 206, ensuring that the strain energy of the extension arm 201 is smoothly released after passing through the driven pressing roller 205 and the active driving roller 206, and can become a "C-shaped" rod with a smaller opening after deformation. The top of the extension arm 201 is connected to a cantilever bracket 207, and a threaded hole (not shown) on the cantilever bracket 207 is connected to the second hook 208. A second bearing assembly 209 (such as a self-lubricating radial spherical bearing) is respectively provided at both ends of the extension arm reel 202. The third bearing assembly 210 and the fourth bearing assembly 211 are respectively disposed at both ends of the driven pressing roller 205 and the active driving roller 206. The above assemblies are connected in the above manner to form a flexible unfolding and retracting assembly 2.

[0056] Figure 6 Schematic diagram of a box assembly in one embodiment of the present application. Figure 6 As shown, in some embodiments, the housing 300 includes a box assembly 4, which includes a hollow first chamber 401 and a second chamber 402, wherein the first chamber 401 is used to accommodate the flexible solar wing assembly 1, and the second chamber 402 is used to accommodate the flexible unfolding assembly 2. Exemplarily, the box assembly 4 can provide positioning and installation functions for the solar wing reel 101, the extension arm reel 202, the active drive roller 206, the driven pressure roller 205, the tension wheel 203, and the drive assembly 800.

[0057] Figure 5 Schematic diagram of a box cover assembly in one embodiment of the present application. Figure 5 As shown, in some embodiments, the shell 300 also includes a box cover assembly 3, which is connected to the box body assembly 4, and is provided with an extension slot 301, an extension hole 302 and a clamping device 303. The flexible solar cell array 103 can extend outward through the extension slot 301; the extension arm 201 can extend outward through the extension hole 302; the clamping device 303 is connected to the extension arm 201, and the clamping device 303 is used to clamp the extension arm 201 after the extension arm 201 is unfolded or rolled into place, thereby generating a certain support stiffness.

[0058] In some embodiments, a first travel switch (not shown) is provided on the clamping device 303, and the first travel switch is used to send a first prompt signal after the extension arm 201 is unfolded or rolled into place; a second travel switch (not shown) is provided on the extension slot 301, and the second travel switch is used to send a second prompt signal after the flexible solar cell array 103 is unfolded or rolled into place. Exemplarily, the first prompt signal and the second prompt signal can be a "deployed into place" signal or a "rolled into place" signal.

[0059] refer to Figure 2 , Figure 4 and Figure 7 As shown, in some embodiments, the drive assembly 800 includes an ultrasonic motor (not shown) and a coupling (not shown), and there are multiple drive assemblies, which are connected to the solar wing reel 101, the extension arm reel 202, and the active drive roller 206 one by one.

[0060] For example, Figure 7 3 driving components are shown, namely, the first driving component 5, the second driving component 6, and the third driving component 7. The first driving component 5 is connected to the extension arm reel 202, the second driving component 6 is connected to the active driving roller 206, and the third driving component 7 is connected to the solar wing reel 101. By arranging ultrasonic motors in each driving component, the structure of the driving component can be simplified and the weight can be reduced. The driving component is not affected by the magnetic field and does not need lubrication under vacuum, thereby improving environmental adaptability.

[0061] The following introduces the status of each component in the satellite roll-up flexible solar wing deployment and retraction device of the present application before and after the satellite launch.

[0062] refer to Figure 7 As shown, before the satellite is launched, the rolled-up flexible solar wing assembly 1 and the flexible unfolding assembly 2 are installed according to the positioning positions on the box assembly 4, the top of the suspension bracket 105 is extended from the extension slot 301 on the box cover assembly 3, the top of the extension arm 201 is extended from the extension hole 302 on the box cover assembly 3, the cantilever bracket 207 is installed and the second hook 208 is connected to the first hook 106. At this time, the state before the satellite launch is ready.

[0063] refer to Figure 1 and Figure 8As shown, after the satellite is launched into orbit, it receives the remote control command of "satellite solar panels unfolding" from the ground station. At this time, the second drive component 6 is powered on and drives the active drive roller 206 to rotate through the coupling. When the active drive roller 206 rotates, friction is generated between it and the extension arm 201, thereby driving the extension arm 201 to extend upward. At this time, the extension arm 201 is curled into a "C-shaped" rod with a smaller opening due to the release of strain energy through the driven clamping roller 205 and the active drive roller 206. The cantilever bracket 207 pulls the suspension bracket 105 to move upward, thereby causing the flexible solar cell array 103 to unfold.

[0064] The characteristics of the satellite reel-type flexible solar wing deployment device during deployment include:

[0065] (1) Under the pressure provided by the coil spring 204, the tension wheel 203 always presses the undeployed extension arm 201 wound on the extension arm reel 202 to ensure that the strain energy stored in the extension arm 201 is not released before it is deployed.

[0066] (2) The driven clamping roller 205 and the active driving roller 206 can not only provide friction for the extension arm 201 to extend upward, but also play a clamping and guiding role.

[0067] (3) After the extension arm 201 is deployed, it can be curled into a "C-shaped" rod with a smaller opening under the action of strain energy, and as the extension arm 201 stretches upward, the curling radius increases. After fully deployed, the bottom of the extension arm 201 contacts and is clamped by the clamping device 303 on the box cover assembly 3, thereby providing a certain rigidity to prevent the "C-shaped" rod from buckling and becoming unstable due to excessive deployment length. At the same time, the travel switch is triggered to send a "deployment in place lock" signal, the second drive assembly 6 stops and self-locks, and the flexible solar wing deployment process ends.

[0068] The satellite reel-type flexible solar wing deployment and retraction device of the present application also has the characteristic of repeatable deployment and retraction, and can realize the recovery of the satellite flexible battery array. When the "satellite solar panel retraction" remote control command from the ground station is received, the second drive assembly 6 reverses, and the first drive assembly 5 and the third drive assembly 7 respectively rotate in the direction of tightening the extension arm 201 and the flexible solar cell array 103. At this time, the flexible solar cell array 103 and the extension arm 201 can be retracted, and the flexible solar cell array 103 and the extension arm 201 are respectively wound on the solar wing reel 101 and the extension arm reel 202. When the battery array hanging plate 108 contacts the travel switch on the extension slot 301, a "reeling in place lock" signal is sent, the first drive assembly 5 and the third drive assembly 7 are powered off and stopped, the second drive assembly 6 stops and self-locks, and the flexible solar wing retraction process ends.

[0069] Although the above disclosure discusses some currently useful embodiments through various examples, it should be understood that such details are for illustrative purposes only, and the appended claims are not limited to the disclosed embodiments, but rather, the claims are intended to cover all modifications and equivalent combinations that are consistent with the essence and scope of the embodiments of the present application. For example, although the system components described above can be implemented by hardware devices, they can also be implemented only by software solutions, such as installing the described system on an existing server or mobile device.

[0070] Similarly, it should be noted that in order to simplify the description disclosed in this application and thus help understand one or more embodiments, in the above description of the embodiments of this application, multiple features are sometimes combined into one embodiment, figure or description thereof. However, this disclosure method does not mean that the features required by the object of this application are more than the features mentioned in the claims. In fact, the features of the embodiments are less than all the features of the single embodiment disclosed above.

[0071] In some embodiments, numbers describing the number of components and attributes are used. It should be understood that such numbers used for the description of the embodiments are modified by the modifiers "about", "approximately" or "substantially" in some examples. Unless otherwise specified, "about", "approximately" or "substantially" indicate that the numbers are allowed to vary by ±20%. Accordingly, in some embodiments, the numerical parameters used in the specification and claims are approximate values, which can be changed according to the required features of individual embodiments. In some embodiments, the numerical parameters should take into account the specified significant digits and adopt the method of general digit retention. Although the numerical domains and parameters used to confirm the breadth of the range in some embodiments of the present application are approximate values, in specific embodiments, the setting of such numerical values ​​is as accurate as possible within the feasible range.

[0072] Although the present application has been described with reference to the current specific embodiments, ordinary technicians in this technical field should recognize that the above embodiments are only used to illustrate the present application, and various equivalent changes or substitutions may be made without departing from the spirit of the present application. Therefore, as long as the changes and modifications to the above embodiments are within the essential spirit of the present application, they will fall within the scope of the claims of the present application.

Claims

1. A satellite reel-type flexible solar wing deployment and retraction device, characterized in that: include: A flexible solar wing assembly comprises a solar wing reel, a flexible solar cell array and a support assembly, wherein the solar wing reel is used to reel up the flexible solar cell array, and the support assembly is connected to the flexible solar cell array; the support assembly comprises: a connecting rope, a hanging bracket, a first hook, an elastic member and a battery array hanging plate, the flexible solar cell array is connected to the battery array hanging plate through the connecting rope, the battery array hanging plate is connected to the hanging bracket through the elastic member, and the first hook is arranged at the top of the hanging bracket; wherein buckles are arranged at the top of the flexible solar cell array and the bottom of the battery array hanging plate, and the connecting rope passes through the buckles to connect the flexible solar cell array and the battery array hanging plate; A flexible unfolding and retracting assembly is connected to the supporting assembly, the flexible unfolding and retracting assembly comprises an extending arm, an extending arm reel and an active driving roller, the extending arm reel is used to reel up the extending arm, the active driving roller is in contact with the surface of the extending arm, the active driving roller can drive the extending arm to gradually unfold from a wound state and curl into a conical rod, and can drive the flexible solar cell array to unfold during the unfolding of the extending arm; the flexible unfolding and retracting assembly also comprises a tensioning wheel, a coil spring and a driven pressing roller, the driven pressing roller is in contact with the surface of the extending arm, the driven pressing roller and the active driving roller are used to guide and press the extending arm to store strain energy; the tensioning wheel is in contact with the surface of the extending arm, the coil spring is connected to the tensioning wheel, and the coil spring is used to provide pressure to the tensioning wheel to press the extending arm; A shell, used to accommodate the flexible solar wing assembly and the flexible deployment assembly; A driving assembly is arranged on the shell, and the driving assembly is used to drive the solar wing reel to rotate, drive the extension arm reel to rotate, and drive the active drive roller to rotate.

2. The satellite reel-type flexible solar wing deployment and retraction device according to claim 1, characterized in that: The flexible solar wing assembly also includes a first bearing assembly, which is respectively arranged at both ends of the solar wing reel, and the first bearing assembly includes a self-lubricating radial spherical bearing.

3. The satellite reel-type flexible solar wing deployment and retraction device according to claim 1, characterized in that: The flexible expansion and contraction assembly also includes a second bearing assembly, a third bearing assembly and a fourth bearing assembly. The second bearing assembly is respectively arranged at both ends of the extension arm reel; the third bearing assembly is respectively arranged at both ends of the driven pressure roller; and the fourth bearing assembly is respectively arranged at both ends of the active drive roller.

4. The satellite reel-type flexible solar wing deployment and retraction device according to claim 1, characterized in that: The flexible stowage assembly further comprises a cantilever bracket, the cantilever bracket is connected to the top end of the extension arm, a second hook is arranged on the cantilever bracket, and the second hook is connected to the support assembly.

5. The satellite reel-type flexible solar wing deployment and retraction device according to claim 1, characterized in that: The shell includes a box assembly, and the box assembly includes a hollow first chamber and a second chamber. The first chamber is used to accommodate the flexible solar wing assembly, and the second chamber is used to accommodate the flexible deployment assembly.

6. The satellite reel-type flexible solar wing deployment and retraction device according to claim 5, characterized in that: The housing further comprises a box cover assembly, the box cover assembly is connected to the box body assembly, the box cover assembly is provided with an extension slot, an extension hole and a clamping device, and the flexible solar cell array can extend outward through the extension slot; The extension arm can extend outward through the extension hole; The clamping device is connected to the extension arm, and is used to clamp the extension arm after the extension arm is unfolded or rolled into place.

7. The satellite reel-type flexible solar wing deployment and retraction device according to claim 6, characterized in that: The clamping device is provided with a first travel switch, and the first travel switch is used to send a first prompt signal after the extension arm is unfolded or rolled into place; the extension groove is provided with a second travel switch, and the second travel switch is used to send a second prompt signal after the flexible solar cell array is unfolded or rolled into place.

8. The satellite reel-type flexible solar wing deployment and retraction device according to claim 1, characterized in that: The driving assembly includes an ultrasonic motor and a coupling. There are multiple driving assemblies, and the driving assemblies are connected to the solar wing reel, the extension arm reel, and the active driving roller in a one-to-one correspondence.

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