A space solar cell array sail deployment mechanism

Abstract

The application discloses a space solar cell array sail deployment mechanism and belongs to the technical field of space solar cell arrays, characterized in that the space solar cell array sail deployment mechanism comprises a connecting support module for connecting a satellite, a rotating deployment module installed on the connecting support module, a pressing release module located on the upper surface of the rotating deployment module, and an avoiding deployment module located around the rotating deployment module; the avoiding deployment module comprises M avoiding deployment assemblies; the outer side of the pressing release module is connected with one end of the avoiding deployment assembly through a disconnectable assembly; the connecting support module is provided with a mounting interface connected with the rotating deployment module and the avoiding deployment assembly; the other end of the avoiding deployment assembly is connected with the connecting support module through a coil spring; and the rotating deployment module is internally provided with a flexible solar cell array sail. The space solar cell array sail deployment mechanism adopts a system integration design scheme, has the characteristics of large stiffness and high fundamental frequency in the launch section and the on-orbit section, and realizes large folding and unfolding ratios, power mass ratios and power volume ratios.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of space solar cell array, and particularly relates to a solar cell array sail deployment mechanism. BACKGROUND

[0002] In recent years, with the gradual increase of space missions, the demand of spacecraft for solar cell array power is getting larger and larger. This makes the traditional rigid solar cell array, due to its large volume, small folding and unfolding ratio, and the influence of the carrying envelope and the inability to greatly improve the solar cell array conversion efficiency, unable to meet the requirements of new high-power payloads for the required power of spacecraft. There are two ways to solve the above problems. One is to improve the light conversion efficiency of single solar cell components. According to relevant data at home and abroad, the average efficiency of the current mainstream three-junction gallium arsenide battery in space is about 30%, and the average efficiency of the latest products IMM and α / β of the American SolAero company is about 32%. Each 1% improvement in conversion efficiency will bring greater challenges to battery component technology. The second is to solve the problems of small folding and unfolding ratio and large mass of solar cell array structure and mechanism, and to develop new flexible deployment technology to replace the traditional rigid solar cell array, so as to realize larger on-orbit deployment area in the limited launch section envelope volume, and improve the power mass ratio and power volume ratio of the solar cell array.

[0003] At present, with the rapid development of flexible solar cell array technology, compared with the traditional rigid solar cell array, it has higher power mass ratio, power volume ratio and folding and unfolding ratio, etc. It has become the development trend of future high-power spacecraft, such as the circular / fan-shaped solar cell array of the American ATK company and the winding solar cell array (ROSA) of the DSS company, which will gradually replace the rigid solar cell array in deep space exploration and manned space. However, compared with the rigid solar cell array, the flexible solar cell array deployment technology has higher challenges and greater technical difficulties. The main performance is that the flexible structure deployment process has more degrees of freedom and randomness of movement than the rigid structure deployment, and it is difficult to realize the uniqueness and certainty of the deployment process. Moreover, compared with the rigid structure, the flexible structure is prone to local wrinkles, uneven stress and tearing and damage during movement.

[0004] At present, the related patents of spacecraft flexible solar array deployment mechanism are as follows:(1) A flexible solar wing elastic extension rod repeated deployment mechanism, which is driven by a motor to drive the rope and the memory alloy elastic rod to expand and fold the solar blanket on both sides synchronously, realizing the advantages of small folding envelope, light weight, high specific power and the like (patent application number 201811159478.3);(2) A flexible solar wing for satellite power supply and a two-degree-of-freedom storage device applied to the flexible solar wing, which adopts a flexible wing to carry solar cells, and through the installation and steering mechanism at the bottom, the flexible wing can be rotated to track the nonlinear motion of the sun to improve the power generation efficiency (patent application number 201610202262.5);(3) A passive flexible solar wing deployment and folding guide mechanism, which adopts a passive steel wire rope guide principle to make the flexible solar blanket orderly expand to avoid swinging in the vertical hinge line direction during the solar wing deployment and folding (patent application number 201610631584.1);(4) A flexible solar wing with a scissor-type deployment mechanism, which realizes the advantages of light weight, high stiffness, high storage ratio, and insensitivity to the gap between the internal hinges of the mechanism through the coupling design of the carbon fiber scissor lever mechanism and the solar cell array (patent application number 202110327501.0);(5) A secondary deployment fan-shaped solar wing, which realizes the advantages of high storage ratio and folding and unfolding ratio based on the folding fan-shaped gradual rotation and expansion mode (patent application number 202110824902.7);(6) A space station flexible solar wing deployment mechanism, which realizes the advantages of high stiffness and large expansion ratio by driving the two sides of the stacked solar cell array to gradually expand through the three-prism extension arm (patent application number 201510939315.7);(7) A high deployment and folding ratio flexible solar wing deployment mechanism, which realizes the advantages of small folding volume, long deployment distance, and high deployment and folding ratio by driving the solar blanket assembly to move with the scissor lever assembly (patent application number 202110783411.2);(8) An on-orbit flexible solar cell array deployment device for spacecraft, which expands the four supporting rods of the rectangular diagonal line by pneumatic method, and then expands the flexible cell array sail structure (patent application number 201611237253.6);(9) A winding type deployable solar cell array, which realizes the on-orbit deployment verification of the flexible super-power solar wing by driving the middle flexible solar blanket structure to gradually expand through the synchronous winding extension of the two-sided carbon fiber thin-walled rod structure. Among them, the deployment mechanism can also be applied to replace the middle flexible winding blanket structure with a "Z" shaped stacked type (patent numbers US9611056B1, US9604737B2, US10239642B1).

[0005] The flexible solar array deployment mechanisms involved in the above patents involve inflatable deployment, elastic thin-walled rod structure deployment, and flexible film deployment driven by rigid scissor mechanism, all of which are helpful to realize the stable and reliable deployment of flexible structure on orbit. However, there are still some deficiencies, which are specifically shown as follows:

[0006] (1) The high stiffness and large aspect ratio requirements of solar arrays during launch and deployment in orbit remain a constraint for future high-power spacecraft applications. In the space environment, deploying a large-area flexible solar array structure inevitably leads to a decrease in system stiffness and a lower fundamental frequency, making it prone to frequency coupling with the overall satellite structure and attitude and orbit control system, affecting the adjustment of the satellite's attitude. How to achieve a high aspect ratio and power-to-mass ratio while maintaining system stiffness is the technological development path for large flexible attachments in future spacecraft.

[0007] (2) The uncertainty of the flexible structure's deployment process can easily lead to deployment failures and other problems, which in turn affect the on-orbit performance of the solar array. Due to the large number of local unit degrees of freedom in the large-scale flexible and large-deformation structure, the deployment process is prone to uncertainties, which can cause uneven stress on the flexible body, resulting in wrinkles, excessive local stress, or even tearing, thus causing the on-orbit deployment of the solar array to fail.

[0008] (3) Failure to consider systematic integrated design leads to excessive mass, resulting in a decrease in the power-to-mass ratio of the solar array and reduced on-orbit efficiency. A design approach for flexible structure deployment mechanisms should be considered from the perspective of system integration to reduce system mass and thereby improve the power-to-mass ratio and power-to-volume ratio of the solar array. Summary of the Invention

[0009] To address the above-mentioned technical deficiencies, this invention provides a space solar cell array sail deployment mechanism. It adopts a system integration design scheme and, while achieving a large unfolding ratio, power-to-mass ratio, and power-to-volume ratio, features high stiffness and high fundamental frequency in both the launch and on-orbit sections.

[0010] To achieve the above-mentioned technical objectives, the present invention is implemented through the following technical solution:

[0011] The purpose of this invention is to provide a space solar array sail deployment mechanism, comprising:

[0012] Connection support module for connecting satellites;

[0013] A rotating and deployable module installed on the connecting support module;

[0014] The clamping and releasing module is located on the upper surface of the rotating deployment module;

[0015] The avoidance deployment modules are located around the rotating deployment module; among which:

[0016] The avoiding unfolding module comprises M avoiding unfolding assemblies, M being a natural number not less than 4; the outer side of the compression releasing module is connected with one end of the avoiding unfolding assembly through a disconnectable assembly; the connecting support module is provided with mounting interfaces connected with the rotating unfolding module and the avoiding unfolding assembly; the other end of the avoiding unfolding assembly is connected with the connecting support module through a coil spring; the rotating unfolding module is internally mounted with a flexible solar cell array sail.

[0017] Preferably, the rotating unfolding module comprises a central driving rotating shaft and a motor driving the central driving rotating shaft to rotate, both ends of the central driving rotating shaft are connected with an upper guide disc and a lower guide disc through deep groove ball bearings, and four rollers are arranged between the upper guide disc and the lower guide disc; the lower guide disc is connected with the connecting support module through the central driving rotating shaft.

[0018] Preferably, the roller is a hollow thin-walled cylindrical structure, and a rectangular through groove is arranged on the roller in the radial direction from top to bottom.

[0019] Preferably, the compression releasing module comprises a cross-shaped compression base, four compression surfaces are arranged at four ends of the compression base, four guide wheel supports are arranged at the central position of the upper surface of the compression base, one guide wheel and a deep groove ball bearing are mounted on each guide wheel support, the disconnectable assembly comprises a compression rope and a shearing mechanism, one end of the compression rope is fixedly connected with the avoiding unfolding assembly, the other end of the compression rope is sequentially connected with a fixed fulcrum through the compression surface and the guide wheel, and a positioning groove connected with the avoiding unfolding module is formed in the compression surface.

[0020] Preferably, a friction coating is applied to the bottom surface of the positioning groove.

[0021] Preferably, the avoiding unfolding assembly comprises a U-shaped frame composed of a compression connecting base, a connecting plate and a lower mounting base connected in sequence; a guide roller assembly is arranged between the compression connecting base and the lower mounting base; a rotating pin shaft is mounted on the lower mounting base, a coil spring is mounted on the rotating pin shaft, and shaft sleeves are mounted at both ends of the rotating pin shaft.

[0022] Preferably, the guide roller assembly comprises a guide cylinder, and the guide cylinder is connected with the compression connecting base and the lower mounting base through deep groove ball bearings at both ends of the guide cylinder.

[0023] Preferably, the flexible solar cell array sail comprises:

[0024] four isosceles trapezoidal structure quadrant solar cell arrays;

[0025] two support ropes perpendicular to each other and coplanar;

[0026] a connecting wire assembly for connecting the quadrant solar cell array and the support rope; wherein:

[0027] In the unfolded state, the upper bottom of the four-quadrant solar cell array is spliced into a small square, and the lower bottom of the four-quadrant solar cell array is spliced into a large square; the connecting support rope is connected to the through hole in the connecting device assembly.

[0028] Preferably: each quadrant solar cell array is composed of M trapezoidal solar cell arrays; M is a natural number greater than 0; the trapezoidal solar cell array comprises a trapezoidal frame structure, a trapezoidal flexible blanket and a solar cell array piece; wherein: the solar cell array piece is bonded to the trapezoidal flexible blanket, and the trapezoidal flexible blanket is bonded to the trapezoidal frame structure; the trapezoidal frame structure comprises two mutually parallel longitudinal beams, and N spokes are connected between the two longitudinal beams, N being a natural number greater than 1; the end surface of the longitudinal beam is a "herringbone" structure, and the trapezoidal frame structure is made of carbon fiber laminated plate; the connecting device assembly comprises an upper connecting device and a lower connecting device bonded to each other; wherein: two through holes are formed in the bonding surface of the upper connecting device and the lower connecting device; one through hole is a rectangular hole, and the other through hole is a circular hole; the spokes on both sides of the trapezoidal frame structure pass through the rectangular hole, and the support rope passes through the circular hole.

[0029] Preferably: the flexible solar cell array sail surface adopts the Icarus in-plane folding mode, and after forming a "cross" cross state, the four edges of the "cross" are wound on the roller in the rotating deployment module in a clockwise direction to form a wrapping structure. The present application has the advantages and technical effects that:

[0030] (1) The present application adopts an integrated modular design, and has the advantages of compact structure design, rapid installation and deployment with the whole satellite structure, large system stiffness in the launch stage, high fundamental frequency, etc. Moreover, the flexible sail surface structure is folded in the mechanism in an in-plane folding mode, which can more easily realize the advantage of large folding ratio compared with the traditional flexible deployment mechanism.

[0031] (2) The "cross" symmetric structure is adopted in addition to the guide arrangement, which improves the determinacy and uniqueness of the flexible structure during the deployment process. The guide mechanism based on the diagonal "cross" in-plane folding of the flexible sail surface structure greatly increases the stability and reliability of the flexible structure during the deployment process, effectively reduces the unevenness of the stress of the flexible structure, and avoids problems such as wrinkles and excessive local stress.

[0032] (3) The present application adopts a lightweight integrated design, which greatly reduces the weight of the deployment mechanism. Further, the present application realizes higher power mass ratio and power volume ratio of the system, and improves the efficiency of the solar cell array in on-orbit application. BRIEF DESCRIPTION OF DRAWINGS

[0033] Figure 1 It is a three-dimensional axial side view of the preferred embodiment of the present application;

[0034] Figure 2Front view of the preferred embodiment of the present invention;

[0035] Figure 3 Top view of the preferred embodiment of the present invention;

[0036] Figure 4 Structure diagram of the compression release module in the preferred embodiment of the present invention;

[0037] Figure 5 Top view of the rotation expansion module in the preferred embodiment of the present invention;

[0038] Figure 6 Structure diagram of the rotation expansion module in the preferred embodiment of the present invention;

[0039] Figure 7 Structure diagram of the upper and lower guide plates in the preferred embodiment of the present invention;

[0040] Figure 8 Relationship diagram of the rotation expansion module and the flexible solar cell array sail in the preferred embodiment of the present invention;

[0041] Figure 9 Structure diagram of the connecting support module in the preferred embodiment of the present invention;

[0042] Figure 10 Structure diagram of the avoidance expansion module in the preferred embodiment of the present invention;

[0043] Figure 11 Folding and gathering working principle view in the use process of the present invention;

[0044] Figure 12 Unfolding and deploying working principle view in the use process of the present invention;

[0045] Figure 13 Structure diagram of the flexible solar cell array sail in the use process of the present invention;

[0046] Figure 14 Structure diagram of the quadrant solar cell array in the preferred embodiment of the present invention;

[0047] Figure 15 Structure diagram of the trapezoidal solar cell array in the preferred embodiment of the present invention;

[0048] Figure 16 Front view of the trapezoidal frame structure in the preferred embodiment of the present invention;

[0049] Figure 17 Front view of the trapezoidal flexible blanket in the preferred embodiment of the present invention;

[0050] Figure 18 Structure diagram of the longitudinal beam in the preferred embodiment of the present invention;

[0051] Figure 19 Structure diagram of the connector assembly in the preferred embodiment of the application.

[0052] 1, compression release module, 2, rotating deployment module, 3, flexible solar array sail, 4, connecting support module, 5, avoidance deployment module; 101, compression base, 102, compression rope, 103, guide wheel support, 104, guide wheel; 105, deep groove ball bearing; 106, end nut; 201, upper guide disc, 202, roller, 203, lower guide disc, 204, central drive shaft; 301, flexible solar array sail structure; 401, whole star mounting base; 50, avoidance deployment assembly; 501, compression connecting seat, 502, connecting plate, 503, lower mounting seat, 504, guide cylinder, 505, rotating pin, 506, coil spring. DETAILED DESCRIPTION

[0053] In order to make the above-mentioned objectives, design control system and advantages of the application more clear and obvious, the application will be further described in detail below in combination with embodiments. It should be understood that the specific embodiments described herein are only used to explain the application and not to limit the application.

[0054] In order to overcome the problem that the existing flexible deployment mechanism system has low rigidity and is easy to couple with the spacecraft structure and attitude orbit control system to cause resonance, an integrated modular design is adopted, the structure design is compact, the whole star structure is quickly installed and deployed, the system has the advantages of large rigidity and high fundamental frequency in the launch section; at the same time, in order to overcome the problem that the existing flexible deployment mechanism is easy to cause film structure to wrinkle and stress concentration, and cannot realize a large folding and unfolding ratio, an in-plane folding mode based on the folding paper configuration is adopted to fold the flexible structure inside the mechanism, and a guide mechanism is additionally arranged outside to improve the certainty of the flexible structure deployment process, thereby realizing the large folding and unfolding ratio advantage of the flexible sail structure.

[0055] Please refer to Figures 1 to 19 A space solar array sail deployment mechanism, comprising:

[0056] A connecting support module 4 for connecting a satellite; a whole star mounting support 401 in the connecting support module is provided with a star body mounting interface 402, a rotating deployment module mounting interface, and an avoidance deployment module mounting interface 403;

[0057] A rotating deployment module 2 mounted on the connecting support module 4;

[0058] A compression release module 1 located on the upper surface of the rotating deployment module 2;

[0059] An avoidance deployment module 5 located around the rotating deployment module 2; wherein:

[0060] The avoidance deployment module 5 includes M avoidance deployment components, where M is a natural number not less than 4; the outer side of the clamping release module 1 is connected to one end of the avoidance deployment component via a detachable component; the connecting support module 4 is provided with an installation interface for connecting to the rotating deployment module 2 and the avoidance deployment components; the other end of the avoidance deployment component is connected to the connecting support module 4 via a coil spring 506; a flexible solar cell array sail 3 is installed inside the rotating deployment module 2.

[0061] In the above preferred embodiment:

[0062] The rotating deployment module 2 is located at the center of the entire solar array sail deployment mechanism and is also the core module of the mechanism. It has the clamping and releasing module 1 at its upper part, the avoidance deployment module 5 around it, the connecting support module 4 at its lower part, and the flexible solar array sail 3 structure inside.

[0063] The rotating deployment module 2 includes a central drive shaft 204 and a motor 207 that drives the central drive shaft 204 to rotate. The two ends of the central drive shaft 204 are connected to an upper guide plate 201 and a lower guide plate 203 via deep groove ball bearings. Four rollers 202 are arranged between the upper guide plate 201 and the lower guide plate 203. The lower guide plate 203 is connected to the connecting support module 4 via the central drive shaft 204. In other words, the rotating deployment module 2 includes: an upper guide plate 201, rollers 202, a central drive shaft 204, and a lower guide plate 203. The two ends of the central drive shaft 204 are respectively mounted to the upper guide plate 201 and the lower guide plate 203 via deep groove ball bearings, and four rollers 202 are evenly distributed and movably installed between the upper and lower guide plates. The rollers 202 are hollow thin-walled cylindrical structures with rectangular through grooves running radially from top to bottom. The upper and lower guide plates in the rotating deployment module 2 are provided with four evenly distributed and symmetrical "U"-shaped grooves 205 suitable for the diameter of the roller, which facilitates the installation of the roller inside and automatically pulls the roller out from the upper and lower guide plates after the flexible sail structure is deployed in place; the roller in the rotating deployment module is a hollow thin-walled cylindrical structure with a rectangular through groove from top to bottom in the radial direction, which facilitates the bonding and fixing of the flexible solar cell array sail structure inside; the upper and lower guide plates in the rotating deployment module 2 are provided with several weight-reducing holes 206;

[0064] The compression release module 1 comprises a cross-shaped compression base 101, four ends of the compression base 101 are provided with compression surfaces, the center of the upper surface of the compression base 101 is provided with four guide wheel supports 103, one guide wheel 104 and a deep groove ball bearing 105 are installed on each guide wheel support 103, the disconnectable assembly comprises a compression rope 102 and a shearing mechanism (such as scissors, or a mechanism and device with automatic shearing function, etc.), one end of the compression rope 102 is fixedly connected with the avoidance unfolding assembly, the other end of the compression rope 102 is sequentially connected with a fixed fulcrum through the compression surface and the guide wheel 104, the fixed fulcrum is located in the satellite cabin, a positioning groove is formed in the compression surface for connecting the avoidance unfolding module 5, and a friction coating is applied to the bottom surface of the positioning groove. That is, the compression release module 1 comprises the compression base 101, the compression rope 102, the guide wheel support 103, the guide wheel 104, the deep groove ball bearing 105 and the end nut 106. The guide wheel assembly located in the middle of the compression base comprises the guide wheel 104, the guide wheel support 103 and the deep groove ball bearing 105. The two ends of the guide wheel 104 are respectively installed with the deep groove ball bearing 105 and the two guide wheel supports 103. The compression base 101 in the compression release module 1 is a "cross" symmetric structure, four end surfaces of the "cross" are provided with rectangular positioning grooves 108 for restricting the compression connection position of the avoidance unfolding assembly and the compression base. The bottom surface of the positioning groove of the compression base 101 is coated with a high-friction coating to increase the friction of the surface to adapt to the large shearing load in the launch section. The guide wheel assembly is four groups, which are symmetrically arranged with the "cross" structure of the compression base, and the four avoidance unfolding assemblies in the avoidance unfolding module are connected with the compression release module through the compression rope.

[0065] The avoiding unfolding assembly includes a U-shaped frame composed of a compression connecting seat 501, a connecting plate 502 and a lower mounting seat 503 connected in sequence; wherein: a guide roller assembly is arranged between the compression connecting seat 501 and the lower mounting seat 503; the lower mounting seat 503 is provided with a rotating pin shaft 505 mounted thereon, the rotating pin shaft 505 is provided with a coil spring 506 mounted thereon, and the two ends of the rotating pin shaft 505 are provided with shaft sleeves 507. The avoiding unfolding module 5 includes four or more avoiding unfolding assemblies, and the avoiding unfolding assembly includes a compression connecting seat 501, a guide roller assembly, a connecting plate 502, a lower mounting seat 503, a coil spring 506, a rotating pin shaft 505 and a shaft sleeve 507. The guide roller assembly includes a guide cylinder 504 and a deep groove ball bearing. The two ends of the guide roller are respectively mounted in the compression connecting seat 501 and the lower mounting seat 503 through the deep groove ball bearings. The avoiding unfolding module includes four avoiding unfolding assemblies which are symmetrically and evenly distributed in the shape of a cross around the compression base and are connected to the compression release module through the compression rope and the end nut. The connecting plate in the avoiding unfolding assembly is connected to the compression connecting seat and the lower mounting seat by fasteners (such as screws) and has a "groove" shape. Increasing its own stiffness helps the guiding effect.

[0066] The guide roller assembly includes a guide cylinder 504, and the two ends of the guide cylinder 504 are connected to the compression connecting seat 501 and the lower mounting seat 503 through deep groove ball bearings.

[0067] The connecting support module 4 is arranged at the bottom of the rotating unfolding module and the avoiding unfolding module, and includes a whole star mounting support 401.

[0068] The flexible solar cell array sail surface 3 includes:

[0069] Four isosceles trapezoidal structure quadrant solar cell arrays 31;

[0070] Two support ropes 33 which are perpendicular to each other and coplanar;

[0071] A wire connector assembly 32 for connecting the quadrant solar cell array 31 and the support rope 33; wherein:

[0072] In the unfolded state, the upper bases of the four quadrant solar cell arrays 31 are spliced into a small square, and the lower bases of the four quadrant solar cell arrays 31 are spliced into a large square; the wire connector assembly 32 is provided with through holes for connecting the support rope 3.

[0073] Each quadrant solar cell array 31 has M trapezoidal solar cell arrays 310; M is a natural number greater than 0; the trapezoidal solar cell array 310 comprises a trapezoidal frame structure 3101, a trapezoidal flexible blanket 3102 and a solar cell array piece 3103; wherein: the solar cell array piece 3103 is bonded on the trapezoidal flexible blanket 3102, and the trapezoidal flexible blanket 3102 is bonded on the trapezoidal frame structure 3101; the trapezoidal frame structure 3101 comprises two mutually parallel longitudinal beams 3101-2, and N spokes 3101-1 are connected between the two longitudinal beams 3101-2, N is a natural number greater than 1; the end surface of the longitudinal beam 3101-2 is a "person" shape structure, and the trapezoidal frame structure 3101 is made of carbon fiber laminated plate; the connecting line component 32 comprises an upper connecting line 321 and a lower connecting line 322 which are bonded with each other; wherein: two through holes are opened on the bonding surface of the upper connecting line 321 and the lower connecting line 322; one through hole is a rectangular hole 323, and the other through hole is a circular hole 324; the spokes 3101-1 on both sides of the trapezoidal frame structure 3101 pass through the rectangular hole 323, and the support rope 33 passes through the circular hole 324.

[0074] The flexible solar cell array sail surface 3 adopts the Icarus in-plane folding mode, forms a "cross" cross state, and then winds the four edges of the "cross" in the clockwise direction on the roller 202 in the rotating and unfolding module 2, to form a wrapping structure. Figure 5 The figure of increasing the sail surface and the rotating and unfolding module is carried out in the

[0075] The flexible solar cell array sail surface structure can be stably and orderly unfolded through four guide wheels arranged in "cross" symmetry in the unfolding process

[0076] As Figure 4As shown, the compression release module 1 includes: compression seat 101, compression rope 102, guide wheel support 103, guide wheel 104, deep groove ball bearing 105, end nut 106. Compression seat 101 is a "cross" structure to increase its own stiffness. One end of the guide wheel 104 is installed in the middle of the two guide wheel supports 103 through the deep groove ball bearing 105, forming a compression guide wheel assembly, and four compression guide wheel assemblies are connected in the middle of the compression seat 101 through fasteners (such as screws), and finally the avoidance deployment module 500 and the compression seat 101 are connected by the compression rope 102. The function of the compression release module A is to provide high system stiffness in the launch segment, and to realize the release and separation of the avoidance deployment module E after the solar cell array sail structure is deployed in the orbit segment, and to complete the deployment of the flexible sail structure. (The compression method in this embodiment is to realize low-cost unlocking test on the ground, and the inexpensive rope is used for compression. When deployed, the release function can be realized by artificially cutting the rope. In actual satellite products, in order to improve the reliability of the compression connection and release separation function, a mature compression unlocking device such as a pyrotechnic device or a memory alloy device needs to be replaced)

[0077] As shown in Figure 2 , Figures 5 to 8 , the rotary deployment module 2 includes: upper guide disc 201, roller 202, lower guide disc 203, center drive shaft 204 and motor 207. The upper guide disc 201, the roller 202 and the lower guide disc 203 are located outside the satellite cabin, and the motor 207 is located inside the satellite cabin, and the interface between the two is shown as a horizontal dashed line 6 in Figure 2 ; both ends of the center drive shaft 204 are installed with the upper guide disc 201 and the lower guide disc 202 through bearings, and four rollers 202 are arranged on the periphery of the center drive shaft 204. Among them, the upper guide disc 201 and the lower guide disc 203 are of the same structure, and the surface is provided with four "U" type slot holes, and the four rollers 202 are movably installed between the upper guide disc 201 and the lower guide disc 203 and the periphery of the center drive shaft 204. The purpose of this design is that when the flexible solar cell array sail structure is deployed to the position, the four movable rollers 202 can be extracted from the middle of the upper guide disc 201 and the lower guide disc 203 into the avoidance deployment module 5, thereby realizing the deployment action of the flexible sail structure.

[0078] As shown in Figure 9 , the connection support module 4 is mainly composed of a whole satellite installation base 401, which is provided with a satellite installation interface, a rotary deployment module 2 installation interface and an avoidance deployment module E installation interface. The function of the connection support module 4 is to integrate other modules, so that the overall structure of the mechanism becomes more compact, and a favorable mechanical environment is provided in the launch segment.

[0079] As shown in Figure 10As shown in the figure, the avoidance and deployment module 5 includes: a pressing connection seat 501, a connecting plate 502, a lower mounting seat 503, a guide cylinder 504, a pin shaft 505, and a coil spring 506. Among them, both ends of the guide cylinder 504 are respectively installed with a pressing connection seat 501 and a lower mounting seat 503 through bearings, and are rigidly connected and strengthened through the connecting plate 502. The role of the avoidance and deployment module E is to provide guidance for the flexible sail structure during the deployment process, increase the stability and reliability of the flexible structure during the deployment process, effectively reduce the unevenness of the force on the flexible structure, and avoid problems such as wrinkles and excessive local stress.

[0080] The working process is as follows:

[0081] I. Principle of folding and winding of the solar array sail surface:

[0082] Fold and wind the flexible solar array sail surface 3 with a regular quadrilateral "hui" character structure ( Figure 11 The first figure on the left is the flat state), along the diagonal of the quadrilateral in the triangular area ( Figure 11 The second figure on the left is the folding process), and gradually fold and收拢 the solar array sail surface structure into a "cross" intersection state by means of in-plane folding ( Figure 11 The third figure on the left is the folding in place); Subsequently, the four sides of the solar array sail surface structure in the "cross" intersection state are gradually wound and wrapped along the diameters of the four drums ( Figure 11 The fourth figure on the left is the winding process), and finally the four drums are tightly wrapped inside, forming a completely wrapped state ( Figure 11 The first figure on the right is the winding completion). Thus, the folding and收拢 of the flexible solar array sail surface structure in the winding and deployment module are completed.

[0083] II. Principle of deployment of the solar array sail surface:

[0084] When the flexible solar array sail surface structure 3 is deployed, first, the motor drives the central shaft of the winding and deployment module to rotate counterclockwise, and then the central shaft drives the upper guide disk and the lower guide disk to rotate counterclockwise synchronously ( Figure 12 The second figure on the left is the deployment process). At this time, the solar array sail surface is extruded under the combined action of the guide cylinder 504 and the drum 202 until the solar array sail surface is deployed into a "cross" intersection state ( Figure 12 The third figure on the left is the deployment in place). At this time, the drum is disengaged from the upper guide disk and the lower guide disk under the pulling force of the flexible solar array sail surface. Subsequently, use the shearing mechanism to cut the pressing rope 102, so that the pressing and release module works, ending the locking constraint on the avoidance and deployment component. The avoidance and deployment component quickly expands under the action of the coil spring, releases the constraint on the flexible solar array sail surface, and finally the solar array sail surface is deployed layer by layer under its own elastic action ( Figure 12The fourth image on the left is a completed deployment to a square planar surface. Figure 12 The fifth image on the left is a completed deployment.

[0085] To sum up, the above is only a preferred embodiment of the present application, not for limiting the protection scope of the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A space solar cell array sail deployment mechanism, characterized by, The utility model relates to a kind of satellite connection support module (4) for connecting;Rotary deployment module (2) installed on the connection support module (4);Compression release module (1) is located on the upper surface of rotary deployment module (2);Avoidance deployment module (5) is located around rotary deployment module (2);Wherein: the avoidance deployment module (5) includes M avoidance deployment components, M is not less than 4 natural number;The outer side of the compression release module (1) and the one end of avoidance deployment component are connected by breakable component;The connection support module (4) is equipped with installation interface connected with rotary deployment module (2), avoidance deployment component;The other end of the avoidance deployment component is connected with connection support module (4) by coil spring (506);Rotary deployment module (2) is installed with flexible solar array sail (3) in it; The compression release module (1) includes: the cross-shaped structure compression base (101), the four end portions of the compression base (101) are provided with compression surface, the center position of the upper surface of the compression base (101) is provided with four guide wheel supports (103), one guide wheel (104) and deep groove ball bearing (105) are installed on each guide wheel support (103), the breakable component includes compression rope (102) and shearing mechanism;One end of the compression rope (102) is fixedly connected with avoidance deployment component, the other end of the compression rope (102) is sequentially connected with fixed fulcrum after passing through compression surface, guide wheel (104), the compression surface is provided with positioning groove connected with avoidance deployment module (5). The rotary deployment module (2) includes center drive shaft (204) and motor for driving center drive shaft (204) to rotate, the both ends of the center drive shaft (204) are connected with upper guide disc (201) and lower guide disc (203) through deep groove ball bearing, four rollers (202) are arranged between the upper guide disc (201) and the lower guide disc (203);The lower guide disc (203) is connected with connection support module (4) through center drive shaft (204). The roller (202) is hollow thin-walled cylindrical structure, and a rectangular through groove is arranged from top to bottom in the radial direction. The bottom surface of the positioning groove is coated with a friction coating. The avoidance deployment component includes a U-shaped frame composed of a compression connecting seat (501), a connecting plate (502), and a lower mounting seat (503) connected in sequence;Wherein: a guide roller assembly is arranged between the compression connecting seat (501) and the lower mounting seat (503);The lower mounting seat (503) is mounted with a rotating pin shaft (505) on the upper side, the rotating pin shaft (505) is mounted with a coil spring (506), and the both ends of the rotating pin shaft (505) are mounted with a shaft sleeve (507). The guide roller assembly includes a guide cylinder (504), and the both ends of the guide cylinder (504) are connected with the compression connecting seat (501) and the lower mounting seat (503) through deep groove ball bearings.

2. The space solar cell array unfurling mechanism according to claim 1, characterized in that: The flexible solar array sail (3) includes:

3. The space solar cell array unfurling mechanism according to claim 2, characterized in that: four isosceles trapezoidal structure quadrant solar array (31) 4. The space solar cell array unfurling mechanism according to claim 1, characterized in that: ​ 5. The space solar cell array unfurling mechanism according to claim 1, characterized in that: ​ 6. The space solar cell array unfurling mechanism according to claim 5, characterized in that: ​ 7. The space solar cell array unfurling mechanism according to claim 2, characterized in that: ​ ​ Two support ropes (33) which are perpendicular to each other and coplanar; A wire connector assembly (32) for connecting the quadrant solar cell array (31) and the support rope (33); wherein: In the unfolded state, the upper bottom of the four quadrant solar cell arrays (31) is spliced into a small square, and the lower bottom of the four quadrant solar cell arrays (31) is spliced into a large square; the wire connector assembly (32) is provided with a through hole for connecting the support rope (33).

8. The space solar cell array unfurling mechanism according to claim 7, characterized in that: Each quadrant solar cell array (31) is composed of M trapezoidal solar cell arrays (310); M is a natural number greater than 0; the trapezoidal solar cell array (310) includes a trapezoidal frame structure (3101), a trapezoidal flexible blanket (3102), and a solar cell array sheet (3103); wherein: the solar cell array sheet (3103) is bonded to the trapezoidal flexible blanket (3102), and the trapezoidal flexible blanket (3102) is bonded to the trapezoidal frame structure (3101); the trapezoidal frame structure (3101) includes two longitudinal beams (3101-2) parallel to each other, and N spokes (3101-1) are connected between the two longitudinal beams (3101-2), N is a natural number greater than 1; the end face of the longitudinal beam (3101-2) is a "chevron" structure, and the trapezoidal frame structure (3101) is made of carbon fiber laminated plate; the wire connector assembly (32) includes an upper wire connector (321) and a lower wire connector (322) bonded to each other; wherein: two through holes are provided on the bonding surface of the upper wire connector (321) and the lower wire connector (322); one through hole is a rectangular hole (323), and the other through hole is a circular hole (324); the spokes (3101-1) on both sides of the trapezoidal frame structure (3101) pass through the rectangular hole (323), and the support rope (33) passes through the circular hole (324).

9. The space solar cell array unfurling mechanism according to claim 8, characterized in that: The flexible solar cell array sail surface (3) adopts the Icarus face folding method, and after forming a "cross" state, the four edges of the "cross" are wound on the roller (202) in a clockwise direction to form a wrapping structure.

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