Ultra-light, ultra-high storage ratio flexible solar wing

Abstract

The present application relates to a kind of super-light, super-high storage ratio flexible solar wing, belong to solar wing device technical field;2 solar box blanket, 2 scissors pole, 2 single fork hinge, pressing device and lifting rod;Among them, lifting rod is placed axially horizontally;2 solar box blanket is symmetrically set in the two sides of lifting rod axially in parallel;2 solar box blanket relative side wall middle position, respectively install 1 scissors pole;The bottom of each scissors pole is equipped with 1 single fork hinge;2 single fork hinge is respectively with lifting rod butt joint from the two sides of lifting rod;The side wall of solar box blanket is according to pressing device;The clamping of solar box blanket structure is realized by pressing device;The flexible solar wing of the present application has the advantages such as light weight, small volume, good configuration expandability etc.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of solar wing devices, and relates to a super-light and super-high storage ratio flexible solar wing. BACKGROUND

[0002] With the development of space technology, the demand for power of a spacecraft is increasing, which will lead to a significant increase in the mass and envelope space of a rigid solar wing widely used at present, and new challenges are put forward to the solar wing.

[0003] A Starlink satellite developed by a foreign SpaceX company adopts a stacked launching mode, and a solar wing configured by the Starlink satellite must adapt to a small launching envelope to meet the launching requirement, so the Starlink satellite is provided with a solar wing adopting a scissors lever, and the solar wing has a very low envelope in a storage state. The power source for unfolding the solar wing is a root motor, and a direct driving lever unfolding mode is adopted, so that the motor driving torque and the strength of the root of the scissors lever are required to be high, and the actual use requirement cannot be met. SUMMARY

[0004] The application solves the technical problem of overcoming the shortcomings of the prior art and providing a super-light and super-high storage ratio flexible solar wing, which has the advantages of light mass, small storage volume, good configuration expandability and the like.

[0005] The technical solution of the application is as follows.

[0006] A super-light and super-high storage ratio flexible solar wing comprises two solar box blankets, two scissors levers, two single-fork hinges, a pressing device and a lifting rod.

[0007] The lifting rod is horizontally arranged in an axial direction, the two solar box blankets are symmetrically arranged in parallel in the axial direction on the two sides of the lifting rod, one scissors lever is arranged at the middle position of the side wall of each solar box blanket, one single-fork hinge is arranged at the bottom of each scissors lever, the two single-fork hinges are respectively connected to the lifting rod from the two sides of the lifting rod, the side wall of the solar box blanket is provided with the pressing device, and the pressing device is used to clamp the structure of the solar box blanket.

[0008] In the above super-light and super-high storage ratio flexible solar wing, the lifting rod is a double-rod folding structure, the two rods are connected through a hinge to realize relative rotation folding or unfolding of the two rods, the top of the lifting rod is connected to the two single-fork hinges through a hinge to realize rotation of the whole lifting rod relative to the single-fork hinges, and in an initial state, the lifting rod is rotated to a horizontal state in the axial direction.

[0009] In the above super-light and super-high storage ratio flexible solar wing, the solar box blanket comprises an upper solar panel, a lower solar panel, a solar blanket and a solar cell array.

[0010] The upper solar plate and the lower solar plate are both horizontally placed rectangular plate structures; the solar blanket is a flexible structure; the solar blanket is placed on the upper surface of the lower solar plate after being folded; a solar cell array is attached to the surface of the solar blanket; the upper solar plate is installed on the upper surface of the folded solar blanket; one end of the side wall of the solar blanket is fixedly connected to the side wall of the upper solar plate through a hinge; the other end of the side wall of the solar blanket is fixedly connected to the side wall of the lower solar plate through a hinge.

[0011] In the above-mentioned super-light and super-high storage ratio flexible solar wing, a guide rope is arranged perpendicularly to the folding direction of the solar blanket; the guide rope passes through the folding line of the solar blanket, and the two ends of the guide rope are connected to the upper solar plate and the lower solar plate respectively.

[0012] In the above-mentioned super-light and super-high storage ratio flexible solar wing, the upper solar plate and the lower solar plate both adopt a carbon fiber panel + aluminum honeycomb sandwich structure; springs are uniformly arranged at the joint of the upper solar plate and the solar blanket, and the springs uniformly distribute the tension on the solar blanket to realize the tensioning of the solar blanket after being unfolded.

[0013] In the above-mentioned super-light and super-high storage ratio flexible solar wing, the compression device is a memory alloy puller; the compression device is installed on an external celestial body; the memory alloy puller is a non-explosive compression release device.

[0014] In the above-mentioned super-light and super-high storage ratio flexible solar wing, the unfolding process of the solar wing is divided into three stages, which are, in sequence, the unfolding of the lifting rod, the unfolding of the solar blanket, and the unfolding of the solar blanket.

[0015] In the above-mentioned super-light and super-high storage ratio flexible solar wing, the process of the lifting rod unfolding stage is as follows:

[0016] The lifting rod is rotated to a vertical state through the hinge at the top; the two rods of the lifting rod are rotated to an unfolded state through the hinge, realizing the vertical unfolding state of the entire lifting rod.

[0017] In the above-mentioned super-light and super-high storage ratio flexible solar wing, the process of the solar blanket unfolding stage is as follows:

[0018] The two solar blankets are respectively rotated upward by 90° through the single-fork hinge, realizing the vertical relative arrangement of the two lower solar plates corresponding to the two solar blankets.

[0019] In the above-mentioned super-light and super-high storage ratio flexible solar wing, the process of the solar blanket unfolding stage is as follows:

[0020] The compression device is unlocked to release the solar blanket; the upper solar plate corresponding to the solar blanket is driven to move horizontally outward through the scissors rod; the solar blanket is unfolded by the upper solar plate; the solar blanket is guided during the unfolding process through the guide rope.

[0021] The advantages of this invention compared to the prior art are:

[0022] (1) By adopting a scissor-type deployment mechanism, the height of the solar array in the folded state is less than 150mm, while the deployed area can reach 34㎡, which is much larger than the size of traditional rigid and semi-rigid solar arrays.

[0023] (2) The solar array of the present invention achieves a T-shaped configuration after deployment through three deployment processes, which meets the overall requirements of the satellite;

[0024] (3) The solar array of the present invention achieves solar orientation within a range of ±90° and ±170° by means of A-axis and B-axis motors; it avoids the use of the previous SADA mechanism with slip ring and reduces the cost of use;

[0025] (4) By adopting a linkage release mechanism, the present invention realizes the release of multiple pressing points by a single release mechanism. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of the flexible solar panel structure of the present invention;

[0027] Figure 2 This is a schematic diagram of the solar panel structure of the present invention;

[0028] Figure 3 This is a schematic diagram of the unfolded solar panel blanket of the present invention;

[0029] Figure 4 This is a schematic diagram of the solar cell array of the present invention;

[0030] Figure 5 This is a schematic diagram of the spring of the present invention;

[0031] Figure 6 This is a schematic diagram of the unfolded lifting rod of the present invention;

[0032] Figure 7 This is a schematic diagram of the unfolded solar panel blanket of the present invention;

[0033] Figure 8 This is a schematic diagram of the unfolded solar blanket of the present invention. Detailed Implementation

[0034] The present invention will be further described below with reference to the embodiments.

[0035] This invention proposes a flexible solar array with a high retraction ratio suitable for stacked satellites. It employs a "lifting rod + two flexible battery arrays" scheme, which allows the battery arrays to be positioned away from the satellite body, reducing shading and impact on thermal control. In this scheme, the flexible battery panels on both sides utilize a rope-driven, high retraction ratio scissor-bar deployment mechanism, achieving a high deployment area while maintaining a small retraction envelope, making it particularly suitable for stacked satellites.

[0036] Ultralight, ultra-high storage ratio flexible solar panels, such as Figure 1 As shown, the structure specifically includes two solar panel blankets 1, two scissor bars 2, two single-fork hinges 3, a clamping device 4, and a lifting rod 5. The lifting rod 5 is horizontally positioned axially; the two solar panel blankets 1 are symmetrically arranged parallel to each other on both sides of the lifting rod 5; one scissor bar 2 is installed at the midpoint of the opposite sidewall of each of the two solar panel blankets 1; a single-fork hinge 3 is installed at the bottom of each scissor bar 2; the two single-fork hinges 3 connect to the lifting rod 5 from both sides; the sidewall of the solar panel blanket 1 is fitted with a clamping device 4; the clamping device 4 clamps the structure of the solar panel blanket 1.

[0037] In this invention, the lifting rod 5 is a double-rod folding structure; the two rods are connected by hinges to achieve relative rotational folding or unfolding of the two rods; the top of the lifting rod 5 is connected to two single-fork hinges 3 by hinges to achieve rotation of the lifting rod 5 as a whole relative to the single-fork hinges 3; in the initial state, the lifting rod 5 is rotated to an axially horizontal state.

[0038] like Figure 2 As shown, the solar blanket 1 includes an upper solar panel 6, a lower solar panel 8, a solar blanket, and a solar cell array. Both the upper solar panel 6 and the lower solar panel 8 are horizontally placed rectangular plate structures; the solar blanket is a flexible structure; the solar blanket is folded and placed on the upper surface of the lower solar panel 8; the solar cell array is attached to the surface of the solar blanket, such as... Figure 4 As shown. The upper solar panel 6 is installed on the upper surface of the folded solar blanket; one side wall of the solar blanket is fixedly connected to the side wall of the upper solar panel 6 by a hinge; the other side wall of the solar blanket is fixedly connected to the side wall of the lower solar panel 8 by a hinge.

[0039] like Figure 3 As shown, a guide rope is provided perpendicular to the crease of the sun blanket; the guide rope passes through the crease of the sun blanket, and the two ends of the guide rope are connected to the upper sun plate 6 and the lower sun plate 8 respectively.

[0040] Both the upper solar panel 6 and the lower solar panel 8 adopt a carbon fiber panel + aluminum honeycomb sandwich structure; at the joint between the upper solar panel 6 and the solar blanket, springs are evenly arranged to distribute the tension evenly on the solar blanket, thereby achieving tension after the solar blanket is unfolded. Figure 5 As shown.

[0041] The clamping device 4 of the present invention is a shape memory alloy breaker; the clamping device 4 is installed on an external celestial body; the shape memory alloy breaker is a non-pyrotechnic clamping release device.

[0042] The deployment process of the solar array is divided into three stages: the deployment of lifting rod 5, the deployment of solar box blanket 1, and the deployment of solar blanket.

[0043] like Figure 6 As shown, the process of the lifting rod 5 unfolding stage is as follows:

[0044] The lifting rod 5 is rotated to a vertical position via a hinge at the top; the two rods of the lifting rod 5 are rotated to an unfolded position via a hinge, so that the entire lifting rod 5 is in a vertically unfolded state.

[0045] like Figure 7 As shown, the process of unfolding the solar panel blanket 1 is as follows:

[0046] The two solar panel blankets 1 are rotated 90° upwards via a single fork hinge 3, so that the two lower solar panels 8 corresponding to the two solar panel blankets 1 are vertically opposite each other.

[0047] like Figure 8 As shown, the process of unfolding the sun blanket is as follows:

[0048] The clamping device 4 is unlocked, releasing the solar blanket 1; the upper solar panel 6 of the corresponding solar blanket 1 is driven to move horizontally outward by the scissor bar 2; the upper solar panel 6 drives the solar blanket to unfold; the solar blanket is guided by the guide rope during the unfolding process.

[0049] Solar arrays can be classified into different working modes according to their different working stages, such as clamping and locking, deployment, rapid orientation, tracking, and orbit control.

[0050] Compression and locking mode: The solar array is in a retracted and compressed state, adapting to the needs of assembly, testing, transportation and launch.

[0051] Deployment Modes: The solar panel clamping release device unlocks, and the solar panels unfold sequentially from the clamped and locked state and lock in place. There are three main deployment modes: single deployment, double deployment, and triple deployment.

[0052] Rapid orientation mode: The solar array's A and B axes rotate rapidly according to satellite commands to achieve solar orientation;

[0053] Tracking mode: The solar panels continuously rotate to track the direction of solar incidence, ensuring power generation efficiency;

[0054] Orbit control mode: During satellite ascent, descent, and orbit maintenance, the solar panels rotate and maintain the satellite at its minimum windward area.

[0055] The flexible solar panel of this invention mainly comprises a solar panel blanket 1, a scissor bar 2, a single-fork hinge 3, a clamping device 4, and a lifting rod 5, as shown below. Figure 1 As shown. The solar panel box 1 is the main structure, primarily consisting of solar panels and a solar blanket. The solar panels' main function is to house the solar blanket when the solar wings are retracted, and the sponge on the panel assembly provides relatively uniform pressure to the solar blanket. When the solar wings are deployed, the panels assist in tensioning the solar blanket, and provide interfaces for deployment / retraction guidance devices, solar blanket pre-tensioning springs, pressure release devices, and satellite-mounted solar sensors. The panel assembly mainly consists of an upper panel 6 and a lower panel 8, both constructed from a composite sandwich material of carbon fiber and aluminum honeycomb panels. To ensure a lightweight design, the upper panel uses an aluminum honeycomb + carbon fiber sandwich structure, with localized dense honeycomb and embedded parts at the pressure points. Embedded parts are installed on the sides of the substrate where load-bearing springs are mounted.

[0056] Secondly, the solar blankets are primarily manufactured by collecting multiple small solar cells and placing them on carbon fiber to form panels. Since each solar cell has a very small electromotive force, multiple solar cells are assembled in series to increase the voltage; multiple solar panels together are called a "solar array." The unfolding and retraction of the solar blankets are controlled by a guide device. Lead wires, through lead wire interfaces 9, are used to control the opening and closing of the solar blankets. Adjacent solar blankets are connected by inter-blanket hinges 10. The design of the inter-plate hinges between the solar panels on the flexible solar blankets references the inter-plate hinge design of the International Space Station and large flexible solar wings. The unfolding guide device ensures that the solar blankets unfold and retract in a certain order. The role of the unfolding guide device is particularly important during the retraction process; without the guide device to maintain the retraction order, it would be almost impossible for the solar blankets to retract into the box panel. During the unfolding process, the guide device also reduces the risk of disturbance and snagging caused by the unstable configuration of the solar blankets. The guide ropes ensure that the unfolding and retraction process of the solar blankets is approximately one-dimensional. Each solar blanket is designed with two sets of unfolding guide devices. The flexible solar array in this project does not require on-orbit retraction, thus simplifying the design. The deployment guide device is actually a friction resistance device, which keeps the guide rope under constant tension during deployment.

[0057] The unfolding guide ropes pass through the sides of the hinges between every other panel, and the sun blanket unfolds under the action of the guide ropes. The sun blanket tensioning device consists of evenly distributed springs at both ends of the sun blanket, with 20 evenly distributed springs at each end to achieve the most uniform tension distribution on the sun blanket.

[0058] The scissor bar 2 is a crucial driving component of the flexible solar array. It drives the flexible solar blanket to unfold and lock into a rigid support device. The scissor extension mechanism is stable and smooth during folding and lifting, and when retracted, it offers advantages such as compact structure and small footprint. The scissor bar mechanism uses a drive motor and rope to drive its unfolding. Before unfolding, the mechanism is pressed and retracted between satellites to ensure it does not accidentally unfold or fail during non-operational periods. At the start of the unfolding phase, the locking is released, providing initial force for the mechanism's unfolding. After unfolding, the mechanism is locked in place, providing sufficient rigidity and strength to support the solar array. It unfolds in a specified direction and at a predetermined speed, providing power and support for the flexible thin-film solar array.

[0059] The single-fork hinge 3 is mainly used to connect the A-axis and the scissor lever. It adopts the shaft system design of a traditional unfolding locking mechanism, integrating the configuration of two hinges into one. It also maintains self-locking, thus achieving locking. While ensuring locking reliability, it achieves a smaller envelope and weight.

[0060] The unlocking devices used in this solar array clamping device 4 are all shape memory alloy breakers. The clamping unit is installed on the satellite and includes a pre-tightening assembly, a clamping seat, a guide, and a clamping band. The shape memory alloy (SMA) breaker is a non-pyrotechnic clamping release device with advantages such as simple composition, low storage requirements, reliable performance, low cost, and reusability.

[0061] The lifting rod 5 is made of high-strength carbon fiber composite material, featuring light weight and high rigidity and strength, and consists of two sections connected by a root hinge. The bottom of the lifting rod is fixed by the root hinge. The two hinge structures are similar in principle to the single-fork hinge, both employing a traditional unfolding locking mechanism shaft design, achieving both self-locking and ensuring structural reliability.

[0062] This product primarily serves as the satellite's energy component. To meet the overall configuration requirements, the solar array is designed with a three-step deployment process. The solar array deployment process is as follows:

[0063] In retracted state: All components of the solar array are retracted and pressed against the satellite's sidewalls. Specifically, the left and right flexible solar array panels and solar blankets are pressed against the satellite by eight sets of tension-locking devices. The two scissor-type deployment drive mechanisms are each pressed against the satellite by three tension-locking devices. The central lifting rod is pressed against the satellite by two tension-locking devices, collectively bearing the load during satellite launch. Figure 1 As shown.

[0064] Deployment in one step: After the satellite enters orbit, all clamping points of the solar array unlock, and it deploys under the combined action of the root hinge, the inter-arm hinge, and the A-axis drive motor. When the lifting rod is about to deploy to its final position, the linkage between the A-axis motor and the inter-arm hinge is released, and the root hinge and inter-arm hinge connected to the lifting rod are locked. After the linkage between the A-axis motor and the inter-arm hinge is released, the solar array can be driven to rotate freely along the A-axis. For design simplification, the two solar arrays share a single A-axis.

[0065] Secondary Deployment: After the solar panels have been deployed once, the positioning linkage triggering device first releases the single-fork hinges connecting the two solar panels to the lifting rod. The two hinges have the same structure as the hinges between the rods. After being deployed 90°, they are locked to fix the position of the solar panels and prevent movement during deployment that could affect the deployment of the solar blanket.

[0066] Three-stage deployment: After the solar panels have completed their second deployment, the control system drives the motors on the scissor mechanisms of the two solar panels. The motors, via a rope mechanism, drive the scissor bars to deploy, simultaneously unfolding the flexible solar blanket. Once fully deployed, the motors stop rotating.

[0067] After the solar array is deployed, it can be oriented to the sun within the range of ±90° and ±170° by using the A-axis motor and B-axis motor respectively.

[0068] This invention employs a scissor-type deployment mechanism, resulting in a solar array with a folded height of less than 150mm and a deployed area of ​​up to 34㎡, significantly larger than traditional rigid and semi-rigid solar arrays. The solar array of this invention achieves a T-shaped configuration after deployment through a three-stage deployment process, meeting the overall requirements of the satellite.

[0069] The solar array of this invention achieves solar orientation within a range of ±90° and ±170° via A-axis and B-axis motors; it avoids the use of the previous SADA mechanism with slip rings and reduces the cost of use; the invention also achieves the release of multiple clamping points by a single release mechanism through the use of a linkage release mechanism.

[0070] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A flexible solar panel with an ultralight weight and ultra-high retractability, characterized in that: It includes 2 solar panel blankets (1), 2 scissor bars (2), 2 single-fork hinges (3), a clamping device (4), and a lifting rod (5); Among them, the lifting rod (5) is placed horizontally along the axis; two solar box blankets (1) are arranged symmetrically and parallel to each other on both sides of the lifting rod (5); a scissor bar (2) is installed at the middle position of the opposite side wall of the two solar box blankets (1); a single fork hinge (3) is installed at the bottom of each scissor bar (2); the two single fork hinges (3) are connected to the lifting rod (5) from both sides; a clamping device (4) is installed on the side wall of the solar box blanket (1); the clamping device (4) is used to clamp the structure of the solar box blanket (1); The lifting rod (5) is a double-rod folding structure; the two rods are connected by a hinge to realize relative rotation folding or unfolding of the two rods; the top of the lifting rod (5) is connected to two single-fork hinges (3) by a hinge to realize the rotation of the lifting rod (5) as a whole relative to the single-fork hinges (3); in the initial state, the lifting rod (5) is rotated to the axial horizontal state; The solar box blanket (1) includes an upper solar panel (6), a lower solar panel (8), a solar blanket, and a solar cell array; The upper solar panel (6) and the lower solar panel (8) are both rectangular plate structures placed horizontally; the solar blanket is a flexible structure; the solar blanket is folded and placed on the upper surface of the lower solar panel (8); a solar cell array is attached to the surface of the solar blanket; the upper solar panel (6) is installed on the upper surface of the folded solar blanket; one side wall of the solar blanket is fixedly connected to the side wall of the upper solar panel (6) by a hinge; the other side wall of the solar blanket is fixedly connected to the side wall of the lower solar panel (8) by a hinge. A guide rope is provided perpendicular to the crease of the sun blanket; the guide rope passes through the crease of the sun blanket, and the two ends of the guide rope are connected to the upper sun plate (6) and the lower sun plate (8) respectively; Both the upper solar panel (6) and the lower solar panel (8) adopt a carbon fiber panel + aluminum honeycomb sandwich structure; springs are evenly arranged at the joint between the upper solar panel (6) and the solar blanket, and the tension is evenly distributed on the solar blanket through the springs to achieve tension after the solar blanket is unfolded. The clamping device (4) is a shape memory alloy puller; the clamping device (4) is installed on an external celestial body; the shape memory alloy puller is a non-pyrotechnic clamping release device.

2. The ultralight, ultra-high retractability flexible solar panel according to claim 1, characterized in that: The deployment process of the solar array is divided into three stages: the deployment of the lifting rod (5), the deployment of the solar box blanket (1), and the deployment of the solar blanket.

3. The ultralight, ultra-high storage ratio flexible solar panel according to claim 2, characterized in that: The process of the lifting rod (5) unfolding is as follows: The lifting rod (5) is rotated to a vertical position via the hinge at the top; the two rods of the lifting rod (5) are rotated to an unfolded position via the hinge, so that the entire lifting rod (5) is in a vertical unfolded state.

4. The ultralight, ultra-high storage ratio flexible solar panel according to claim 3, characterized in that: The process of unfolding the solar box blanket (1) is as follows: Two solar panel blankets (1) are rotated 90° upwards via a single fork hinge (3) to achieve vertically opposite arrangement of the two lower solar panels (8) corresponding to the two solar panel blankets (1).

5. The ultralight, ultra-high storage ratio flexible solar panel according to claim 4, characterized in that: The process of unfolding the sun blanket is as follows: The clamping device (4) is unlocked to release the solar box blanket (1); the upper solar panel (6) of the corresponding solar box blanket (1) is driven to move horizontally outward by the scissor bar (2); the upper solar panel (6) drives the solar blanket to unfold; the solar blanket is guided by the guide rope during the unfolding process.

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