Lightweight high-rigidity flexible solar wing

Abstract

A light-weight high-rigidity flexible solar wing is composed of a stretching rod mechanism, a folding type flexible solar wing body, a scissor rod unfolding mechanism and a linkage unlocking pressing device, in the folded state, the flexible solar wing body and the scissor rod unfolding mechanism are located at the top of the stretching rod mechanism, and the light-weight design of the solar wing can be achieved through the specific light-weight high-rigidity structure setting characteristic; and the rigidity of the solar wing is improved by using a high-rigidity scissor rod unfolding mechanism.

Description

TECHNICAL FIELD

[0001] The present application relates to a light-weight high-rigidity flexible solar wing, and belongs to the technical field of solar wings of space vehicles. BACKGROUND

[0002] In space vehicles, the folding flexible solar wing is highly concerned due to its high storage ratio, but its weight advantage is insufficient, and its low rigidity limits its wide application, and a light-weight high-rigidity flexible solar wing scheme is urgently needed to meet the increasing demand for solar wings of low-orbit satellite constellations. SUMMARY

[0003] The technical problem solved by the present application is that, in view of the obvious rigidity, structure and weight defects of the traditional solar wing structure in the prior art, a light-weight high-rigidity flexible solar wing is proposed.

[0004] The present application solves the above technical problem by the following technical scheme: A light-weight high-rigidity flexible solar wing, comprising an extension rod mechanism, a scissors rod unfolding mechanism, a folding flexible solar wing and a linkage unlocking and pressing device, wherein: The folding flexible solar wing is in a folded state, one end of the extension rod mechanism is connected to a satellite body, the other end is connected to the scissors rod unfolding mechanism through the linkage unlocking and pressing device after being pressed and fixed, the scissors rod unfolding mechanism is arranged on the side of the folding flexible solar wing, and the extension rod mechanism and the linkage unlocking and pressing device are arranged at the bottom of the folding flexible solar wing.

[0005] The extension rod mechanism comprises a rotating shaft mechanism, a root hinge, a connecting rod, an inter-rod hinge, an end hinge, a swing shaft hinge, a swing shaft driving mechanism and an unfolding linkage device, wherein: The folding flexible solar wing is in an unfolded state, the rotating shaft mechanism is connected to a satellite cabin wall, the rotating shaft mechanism is connected to the root hinge, the root hinge is connected to the connecting rod, the connecting rod is connected to the inter-rod hinge and the end hinge, the swing shaft hinge and the swing shaft driving mechanism are installed on the end hinge, one end of the swing shaft driving mechanism and the swing shaft hinge is connected to the other end of the scissors rod unfolding mechanism, and the other end of the scissors rod unfolding mechanism is connected to the folding flexible solar wing.

[0006] The scissors rod unfolding mechanism comprises a scissors rod driving unit and a plurality of levels of scissors rods, wherein: The swing shaft driving mechanism, the swing shaft hinge and the scissor rod driving unit are connected at one end, the multi-stage scissor rod is folded and interconnected, and the other end of the scissor rod driving unit and the non-interconnected end of the multi-stage scissor rod are respectively connected with two ends of the folded flexible solar wing.

[0007] The folded flexible solar wing comprises a solar blanket substrate, a box plate and a solar cell circuit, the solar blanket substrates are arranged in a flat manner to form a solar wing plate structure, the box plates are arranged at two ends of the solar wing plate structure, and the solar cell circuit is arranged on each solar blanket substrate.

[0008] The linkage unlocking and pressing device comprises an unlocking assembly, a linkage unlocking mechanism, a pressing mechanism and a pressing support, the folded flexible solar wing is connected and fixed with the satellite side plate through the pressing support and a rotating shaft mechanism, the folded flexible solar wing is uniformly pressed and mounted on the pressing support, the folded flexible solar wing is stacked and pressed on the upper part of the pressing support, the stretching rod mechanism is fixed at one end of the star body and is stacked in the middle part after being unfolded and is pressed on the pressing support through the pressing mechanism, the pressing support is provided in a thin-walled conical structure to provide support stiffness, the linkage unlocking mechanism is arranged at the connection position of the pressing mechanism and the pressing support, and the unlocking assembly is connected with the linkage unlocking mechanism to drive the linkage unlocking mechanism to be unlocked.

[0009] When the linkage unlocking and pressing device receives the solar wing unlocking instruction sent by the satellite, the unlocking assembly operates to release the connection between the pressing mechanism and the pressing support through the linkage unlocking mechanism, and the scissor rod unfolding mechanism pops out the folded flexible solar wing through an internal driving source, and the unfolding process includes two times.

[0010] In the first unfolding process, the stretching rod mechanism is unfolded through the joint action of the root hinge, the rod hinge, the end hinge, the swing shaft driving assembly and the unfolding linkage mechanism, and the scissor rod unfolding mechanism and the folded flexible solar wing are pushed out forward by the stretching rod mechanism while being turned over by 90°.

[0011] After the first unfolding is completed, the scissor rod unfolding mechanism drives the folded flexible solar wing to be unfolded, the solar cell circuit of the unfolded folded flexible solar wing faces the sun, and the scissor rod unfolding mechanism arranged on the back of the folded flexible solar wing is arranged in a cross rod structure.

[0012] The driving source is arranged in the root hinge, the rod hinge and the end hinge to realize unfolding driving, the root hinge, the rod hinge and the end hinge are connected with each other through the unfolding linkage mechanism, the end hinge is connected with the swing shaft hinge, the swing shaft hinge and the swing driving mechanism are connected with the scissor rod unfolding mechanism to realize synchronous rotation of double axes, and the swing shaft driving mechanism is connected with the end hinge, the rod hinge and the root hinge to be unfolded. During the unfolding process, the swing shaft driving mechanism is used for controlling the rope release of the rope wheel of the swing shaft hinge, the end hinge is reeled in under the action of the internal driving source, and moves to the unfolding direction; the rope wheel on the other side of the end hinge is reeled in under the action of the internal driving source, and the inter-rod hinge moves to the unfolding direction; the rope wheel on the other side of the inter-rod hinge is reeled in under the action of the internal driving source, and the root hinge moves to the unfolding direction to realize the sequential unfolding of the hinges, and the unfolding speed of the folded flexible solar wing is realized by the speed control of the swing driving mechanism.

[0013] Compared with the prior art, the present application has the following advantages: (1) The flexible solar wing provided by the present application has the advantages of light weight, small volume in the folded state, good expandability, etc., and can fully meet the requirements of satellite configuration, and can be unfolded by the stretching rod mechanism to a distance away from the satellite, avoiding the shielding of the satellite to the solar wing and affecting the power generation efficiency. (2) The present application realizes the unfolding of the folded flexible solar wing through the scissor rod unfolding mechanism, and can realize the release of multiple compression point compression mechanisms through one unlocking element by using the linkage unlocking mechanism, and can realize the linkage unlocking release of the solar wing compression point by using a preset number of unlocking elements, and the solar wing unfolding process includes two stages of compression point unlocking, primary unfolding and secondary unfolding, both stages are controllable unfolding, which greatly reduces the impact on the satellite during the unfolding process. (3) The present application unlocks the solar wing compression point after the satellite enters the orbit, releases the constraint on the scissor mechanism and the box plate assembly, and the stretching rod mechanism is unfolded under the joint action of the hinge, swing shaft driving mechanism and unfolding linkage device, while the stretching rod mechanism unfolds outward, the swing shaft mechanism drives the scissor rod unfolding mechanism and the folded flexible solar wing to rotate into position, the swing shaft motor is mainly used to limit the unfolding speed of the stretching rod to prevent the hinge from being damaged due to too fast unfolding, and the swing shaft stops rotating when it is unfolded to the position, at this time the stretching rod is unfolded to the position, and the solar blanket is above the required distance from the satellite. (4) The present application is unfolded under the driving of the scissor rod unfolding mechanism, and gives a secondary unfolding signal when the flexible solar blanket is fully unfolded, and the sun tracking can be realized within the required range by the rotating shaft driving assembly and the swing shaft driving assembly respectively after the solar wing is unfolded. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 The present application provides a folded state side view; Figure 2 The present application provides a view towards the satellite solar wing mounting surface view; Figure 3 The present application provides an unfolded state side view; Figure 4 The view of the swing shaft swinging different angles is provided for the present application; Figure 5 The schematic diagram of the unlocked released state is provided for the present application; Figure 6 The schematic diagram of the one-time unfolding process is provided for the present application; Figure 7 The schematic diagram of the one-time unfolding to the position is provided for the present application; Figure 8 The schematic diagram of the secondary unfolding to the position is provided for the present application; Figure 9 The schematic diagram of the unfolding to the position is provided for the present application; Figure 10 The schematic diagram of the stretching rod mechanism is provided for the present application; Figure 11 The schematic diagram of the swing shaft is provided for the present application. DETAILED DESCRIPTION

[0015] A light-weight high-rigidity flexible solar wing is composed of a stretching rod mechanism, a folding flexible solar wing, a scissors lever unfolding mechanism and a linkage unlocking and pressing device. In the folded state, the flexible solar wing and the scissors lever unfolding mechanism are located at the top of the stretching rod mechanism. The specific light-weight high-rigidity structure setting feature can realize the light-weight design of the solar wing, and the high-rigidity scissors lever unfolding mechanism improves the rigidity of the solar wing.

[0016] The light-weight high-rigidity flexible solar wing has the following specific structure settings: In the folded state, the folding flexible solar wing is connected to the satellite body at one end of the stretching rod mechanism and is connected to the scissors lever unfolding mechanism through the linkage unlocking and pressing device after being pressed and fixed at the other end. The scissors lever unfolding mechanism is arranged on the side surface of the folding flexible solar wing, and the stretching rod mechanism and the linkage unlocking and pressing device are arranged at the bottom of the folding flexible solar wing. When the stretching rod mechanism and the scissors lever unfolding mechanism act, the folding point of the folding flexible solar wing is unlocked, and then the folding flexible solar wing is changed from the folded state to the unfolded state through the stretching rod mechanism and the scissors lever unfolding mechanism.

[0017] The stretching rod mechanism includes a rotating shaft mechanism, a root hinge, a connecting rod, an inter-rod hinge, an end hinge, a swing shaft hinge, a swing shaft driving mechanism and an unfolding linkage device, wherein: In the unfolded state, the folding flexible solar wing is connected to the satellite cabin wall through the rotating shaft mechanism, the rotating shaft mechanism is connected to the root hinge, the root hinge is connected to the connecting rod, and the connecting rod is connected to the inter-rod hinge and the end hinge, the swing shaft hinge and the swing shaft driving mechanism are installed on the end hinge, the swing shaft hinge and the swing shaft driving mechanism are connected to one end of the scissors lever unfolding mechanism at the other end, and the other end of the scissors lever unfolding mechanism is connected to the folding flexible solar wing.

[0018] The scissor bar unfolding mechanism comprises a scissor bar driving unit, a multi-stage scissor bar, wherein: The swing shaft hinge, the swing shaft driving mechanism and one end of the scissor bar driving unit are connected, the multi-stage scissor bar is folded and interconnected, and the other end of the scissor bar driving unit and the non-interconnected end of the multi-stage scissor bar are respectively connected with two ends of the folding flexible solar wing.

[0019] The folding flexible solar wing comprises a solar blanket base plate, a box plate and a solar cell circuit, the solar blanket base plates are arranged flat and connected to form a solar wing plate structure, the solar wing plate structure is provided with the box plates at two ends, and the solar cell circuit is laid on each solar blanket base plate.

[0020] The linkage unlocking and pressing device comprises an unlocking assembly, a linkage unlocking mechanism, a pressing mechanism and a pressing support, the folding flexible solar wing is connected and fixed with the satellite side plate through the pressing support and a rotating shaft mechanism, the folding flexible solar wing is uniformly pressed and mounted on the pressing support, the folding flexible solar wing is folded and pressed on the upper part of the pressing support, the stretching rod mechanism is fixed at one end of the star body and is folded and pressed on the pressing support through the pressing mechanism after the middle part, the pressing support is provided in a thin-walled conical cylinder structure to provide support stiffness, the linkage unlocking mechanism is arranged at the connection position of the pressing mechanism and the pressing support, and the unlocking assembly is connected with the linkage unlocking mechanism to release the linkage unlocking mechanism when unlocking.

[0021] When the linkage unlocking and pressing device receives the solar wing unlocking instruction sent by the satellite, the unlocking assembly acts, the connection between the pressing mechanism and the pressing support is released through the linkage unlocking mechanism, the scissor bar unfolding mechanism pops out the folding flexible solar wing through the internal driving source, and the unfolding process includes two times.

[0022] In the first unfolding process, the stretching rod mechanism is unfolded by the joint action of the root hinge, the inter-rod hinge, the end hinge, the swing shaft driving assembly and the unfolding linkage mechanism; the scissor bar unfolding mechanism and the folding flexible solar wing are pushed out forward while being turned over by 90°, and the two connecting rods change from the folded state to a straight line to realize the first unfolding.

[0023] After the first unfolding is completed, the scissor bar unfolding mechanism drives the folding flexible solar wing to unfold, and the solar cell circuit of the unfolded folding flexible solar wing faces the sun, and the scissor bar unfolding mechanism arranged on the back of the folding flexible solar wing is arranged in a back cross rod structure.

[0024] The driving source is arranged in the root hinge, the inter-rod hinge and the end hinge to realize unfolding driving, the root hinge, the inter-rod hinge and the end hinge are connected with each other through the unfolding linkage mechanism, the end hinge is connected with the swing shaft hinge, the swing shaft hinge and the swing driving mechanism are connected with the scissor bar unfolding mechanism to realize synchronous rotation of double axes, and the swing shaft driving mechanism and the end hinge are unfolded. During the unfolding process, the swing shaft driving mechanism is used to control the rope release of the rope wheel of the swing shaft hinge, the end hinge is reeled in under the action of the internal driving source, and moves to the unfolding direction; the rope wheel on the other side of the end hinge is released, the inter-rod hinge is reeled in under the action of the internal driving source, and moves to the unfolding direction; the rope wheel on the other side of the inter-rod hinge is released, the root hinge is reeled in under the action of the internal driving source, and moves to the unfolding direction to realize the sequential unfolding of each hinge, and the unfolding speed of the folding flexible solar wing is realized by the speed control of the swing driving mechanism.

[0025] Further description is made below in combination with the drawings of the specification and the preferred embodiments: Embodiment one: In the current embodiment, the solar wing is composed of 01 extension rod mechanism, 02 scissors rod unfolding mechanism, 03 folding flexible solar wing, and 04 linkage unlocking and compacting device. The 01 extension rod mechanism pushes the solar wing away from the satellite, the 02 scissors rod unfolding mechanism unfolds the 03 folding flexible solar wing, and the 04 linkage unlocking and compacting device is used to compact the solar wing and release it after entering the orbit.

[0026] As shown in Figure 1 , it is a side view of the folding state of the present application, as shown in Figure 2 , it is a view of the satellite solar wing mounting surface of the present application, the solar wing is connected and fixed with the satellite side plate through the 044 compacting support and the 011 rotating shaft mechanism, the entire solar wing structure is compactly installed on the 044 compacting support, the 03 folding flexible solar wing is compactly stacked on the upper part of the 044 compacting support, one end of the 01 extension rod mechanism is installed and fixed on the star body through the 011 rotating shaft mechanism, the middle part after stacking is compactly pressed on the 044 compacting support through the 043 compacting mechanism, the end is connected with the 02 scissors rod unfolding mechanism, and the 02 scissors rod unfolding mechanism is connected with the 03 folding flexible solar wing. That is, the 02 scissors rod unfolding mechanism is on the side of the 03 folding flexible solar wing, and the 01 extension rod mechanism and the 04 linkage unlocking and compacting device are on the lower side of the 03 folding flexible solar wing. The 044 compacting support is a thin-walled conical structure, which can provide greater support stiffness.

[0027] As shown in Figure 3The diagram shows a side view of the invention in its deployed state. After deployment, the solar array is connected to the satellite bulkhead via a 011 rotating shaft mechanism. The 011 rotating shaft mechanism is connected to a 012 root hinge, which in turn is connected to a 013 connecting rod, and further connected to a 014 inter-rod hinge and a 015 end hinge. A 016 swing shaft hinge and a 017 swing shaft drive mechanism are both mounted on the 015 end hinge. These two mechanisms are connected to a 021 scissor bar drive unit, and the remaining 022 multi-stage scissor bars are connected. The other ends of the 021 scissor bar drive unit and the 022 multi-stage scissor bars are respectively connected to both ends of the 03 foldable flexible solar array. The 033 solar cell circuit is laid on the 031 solar blanket substrate.

[0028] like Figure 4 The image shown is a view of the solar array of the present invention after it has been deployed into position, with the 017 swing axis drive mechanism swinging at different angles. The solar array supports simultaneous orientation of the rotation axis and the swing axis toward the sun.

[0029] like Figure 5 As shown, this is a schematic diagram of the unlocked state of the present invention. After the satellite issues the solar panel unlocking command, the solar panel 041 unlocking component is activated. The connection between the 043 clamping mechanism and the 044 clamping support is released through the 042 linkage unlocking mechanism. Under the action of the internal drive source of the 02 scissor bar unfolding mechanism, the solar panel pops out a certain distance.

[0030] like Figure 6 The diagram shown illustrates the deployment process of this invention. During deployment, the 01 extension rod mechanism is deployed in conjunction with the 012 root hinge, the 014 inter-rod hinge, the 015 end hinge, the 017 swing shaft drive assembly, and the 018 deployment linkage mechanism. The 02 scissor bar deployment mechanism and the 03 folding flexible solar panel are pushed forward by the 01 extension rod mechanism while rotating 90°.

[0031] like Figure 7 As shown, this is a schematic diagram of the invention unfolding into position in one go. After unfolding into position in one go, the 02 scissor bar unfolding mechanism and the 03 foldable flexible solar wing are rotated 90° under the action of the 017 swing shaft drive assembly. The 01 extension rod mechanism unfolds under the action of the 012 root hinge, the 014 inter-rod hinge, and the 015 end hinge. The two 013 connecting rods change from a folded state to a straight line.

[0032] like Figure 8 The diagram shown is a front view of the second deployment of the present invention. The second deployment is driven by the 02 scissor bar deployment mechanism to deploy the 03 foldable flexible solar wing. After deployment, the 033 solar cell circuit of the 03 foldable flexible solar wing faces the solar wing.

[0033] like Figure 9As shown, it is a schematic diagram of the present application, and the cross rod structure is a 02 scissor rod unfolding mechanism.

[0034] As shown, it is a schematic diagram of the present application, Figure 10 As shown, it is a schematic diagram of the present application, Figure 11 As shown, it is a schematic diagram of the present application.012 root hinge, 014 rod hinge, 015 end hinge have spring and other driving sources inside to achieve unfolding, 018 unfolding linkage mechanism connects 012 root hinge, 014 rod hinge, 015 end hinge with each other, and connects 015 end hinge with 016 swing shaft hinge, 016 swing shaft hinge and 017 swing driving mechanism are connected with 02 scissor rod unfolding mechanism, so that the two axes can rotate synchronously, and then 017 swing shaft driving mechanism and 015 end hinge realize linkage. During the unfolding process, the rope reel of 016 swing shaft hinge is released by 017 swing shaft driving mechanism, and 015 end hinge can be reeled under the action of the spring driving source inside, moving in the unfolding direction; then the rope reel of the other side of 015 end hinge is released, and 014 rod hinge can be reeled under the action of the spring driving source inside, moving in the unfolding direction; then the rope reel of the other side of 014 rod hinge is released, and 012 root hinge can be reeled under the action of the spring driving source inside, moving in the unfolding direction, thereby realizing the orderly unfolding of each hinge. The speed of 017 swing driving mechanism can control the speed of the first unfolding of the solar wing.

[0035] In this embodiment, the lightweight, high-stiffness flexible solar wing is composed of an unfolding rod mechanism, a folding flexible solar wing, a scissor rod unfolding mechanism, and a linkage unlocking and compression device. In the folded state, the flexible solar wing and the scissor rod unfolding mechanism are located at the top of the unfolding rod mechanism. This scheme has the advantages of light weight, small folded volume, good expandability, and can fully meet the requirements of satellite configuration.

[0036] The unfolding rod mechanism can extend the solar wing to a distance away from the star body, avoiding the shielding of the star body to the solar wing and affecting the power generation efficiency. The scissor rod unfolding mechanism can realize the unfolding of the folding flexible solar wing.

[0037] The linkage unlocking and compression device can realize the release of multiple compression point compression mechanisms by one unlocking element through the linkage unlocking mechanism. In this embodiment, two unlocking elements are used to realize the linkage unlocking and release of 12 solar wing compression points.

[0038] The solar wing unfolding process includes compression point unlocking, first unfolding, and second unfolding. Both stages are controllable unfolding, which greatly reduces the impact on the satellite during the unfolding process. In this embodiment, after the satellite is launched into orbit, the sun wing compression point is unlocked, the constraint on the scissors mechanism and the box plate assembly is released, the sun wing stretching rod mechanism is unfolded under the joint action of the hinge, the swing shaft driving mechanism and the unfolding linkage, in this process, the stretching rod mechanism is unfolded outwardly, at the same time, the swing shaft mechanism drives the scissors rod unfolding mechanism and the folded flexible sun wing to rotate to the position, the swing shaft motor is mainly used for limiting the unfolding speed of the stretching rod, preventing the damage of the sun blanket caused by the too fast unfolding of the hinge, when the swing shaft is unfolded to the position, the rotation is stopped, at this time, the stretching rod is unfolded to the position, and the distance between the sun blanket and the star body is above the required distance.

[0039] When the sun wing is unfolded once, the in-position signal is given, the sun wing is unfolded under the driving of the scissors rod unfolding mechanism, the flexible sun blanket is completely unfolded, the second unfolding in-position signal is given, after the sun wing is unfolded, the sun wing can be oriented to the sun in the required range through the rotation shaft driving assembly and the swing shaft driving assembly respectively.

[0040] Although the present application has been disclosed with the above preferred embodiments, it is not intended to limit the present application, any person skilled in the art can make possible changes and modifications to the technical solutions of the present application by using the disclosed methods and technical contents without departing from the spirit and scope of the present application, therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present application, which does not depart from the technical solutions of the present application, belongs to the protection scope of the technical solutions of the present application.

[0041] The contents not described in detail in the specification of the present application belong to the known technology of the person skilled in the art.

Claims

1. A lightweight, high-rigidity, flexible solar array, characterized in that: Includes an extension rod mechanism, a scissor bar deployment mechanism, a foldable flexible solar panel, and a linkage unlocking and clamping device, wherein: In the retracted state, one end of the extension rod mechanism is connected to the satellite body, and the other end is connected to the scissor bar deployment mechanism after being pressed and fixed by the linkage unlocking and clamping device. The scissor bar deployment mechanism is located on the side of the foldable flexible solar wing, and the extension rod mechanism and the linkage unlocking and clamping device are located at the bottom of the foldable flexible solar wing. Before the extension rod mechanism and the scissor bar deployment mechanism are activated, the retracted point of the foldable flexible solar wing is unlocked, thereby realizing the transformation of the foldable flexible solar wing from the retracted state to the deployed state.

2. The lightweight, high-rigidity, flexible solar array according to claim 1, characterized in that: The extension rod mechanism includes a rotating shaft mechanism, a root hinge, a connecting rod, inter-rod hinges, an end hinge, a swing shaft hinge, a swing shaft drive mechanism, and an extension linkage device, wherein: In its deployed state, the foldable flexible solar array is connected to the satellite bulkhead via a rotating shaft mechanism. The rotating shaft mechanism is connected to the root hinge, which in turn is connected to the connecting rod. The connecting rod is then connected to the inter-rod hinge and the end hinge. The swing shaft hinge and the swing shaft drive mechanism are both mounted on the end hinge. The other end of the swing shaft drive mechanism and the swing shaft hinge is connected to one end of the scissor bar deployment mechanism, which in turn is connected to the foldable flexible solar array.

3. The lightweight, high-rigidity, flexible solar array according to claim 2, characterized in that: The scissor bar deployment mechanism includes a scissor bar drive unit and a multi-stage scissor bar, wherein: The swing shaft drive mechanism and the swing shaft hinge are connected to one end of the scissor bar drive unit. The multi-stage scissor bars are folded and interconnected. The other end of the scissor bar drive unit and the non-interconnected end of the multi-stage scissor bars are respectively connected to the two ends of the foldable flexible solar panel.

4. The lightweight, high-rigidity, flexible solar array according to claim 2, characterized in that: The foldable flexible solar panel includes a solar blanket substrate, a box plate, and a solar cell circuit. The solar blanket substrates are laid flat and connected to form a solar panel structure. Box plates are provided at both ends of the solar panel structure, and the solar cell circuit is laid on each solar blanket substrate.

5. A lightweight, high-rigidity, flexible solar array according to claim 2, characterized in that: The linkage unlocking and clamping device includes an unlocking component, a linkage unlocking mechanism, a clamping mechanism, and a clamping support. The foldable flexible solar array is connected and fixed to the satellite side plate through the clamping support and the rotating shaft mechanism. The foldable flexible solar array is clamped and installed on the clamping support. The foldable flexible solar array is stacked and clamped on the upper part of the clamping support. The extension rod mechanism is fixed on the satellite body. After one end is stacked, the middle part is clamped on the clamping support through the clamping mechanism. The clamping support is set as a thin-walled conical structure to provide support rigidity. The linkage unlocking mechanism is set at the connection position between the clamping mechanism and the clamping support. The unlocking component is connected to the linkage unlocking mechanism to drive the linkage unlocking mechanism to unlock.

6. The lightweight, high-rigidity, flexible solar array according to claim 5, characterized in that: When the linkage unlocking and clamping device receives the solar panel unlocking command sent by the satellite, the unlocking component is activated, and the connection between the clamping mechanism and the clamping support is released through the linkage unlocking mechanism. The scissor bar unfolding mechanism pops out the foldable flexible solar panel through the internal drive source. The unfolding process includes two steps.

7. A lightweight, high-rigidity flexible solar array according to claim 6, characterized in that: During one deployment process, the extension rod mechanism is deployed in a coordinated manner by the root hinge, the inter-rod hinge, the end hinge, the swing shaft drive assembly, and the deployment linkage mechanism. At the same time, the scissor bar deployment mechanism and the foldable flexible solar panel are rotated 90° and pushed forward by the extension rod mechanism.

8. A lightweight, high-rigidity flexible solar array according to claim 7, characterized in that: After one deployment, the scissor bar deployment mechanism drives the foldable flexible solar array to unfold. After unfolding, the solar cell circuit of the foldable flexible solar array faces the sun. The scissor bar deployment mechanism on the back of the foldable flexible solar array unfolds into a cross bar structure.

9. A lightweight, high-rigidity flexible solar array according to claim 8, characterized in that: The root hinge, inter-rod hinge, and end hinge are all equipped with a drive source for deployment drive. The root hinge, inter-rod hinge, and end hinge are connected to each other through the deployment linkage mechanism, and the end hinge is connected to the swing axis hinge. The swing axis hinge and the swing drive mechanism are both connected to the scissor bar deployment mechanism to achieve synchronous rotation of the two axes. The swing axis drive mechanism is linked with the end hinge, inter-rod hinge, and root hinge for deployment. During deployment, the swing shaft drive mechanism controls the rope release of the swing shaft hinge pulleys, and the end hinges retract the rope under the action of the internal drive source, moving in the deployment direction; the rope releases the rope on the other side of the end hinge, and the inter-bar hinges retract the rope under the action of the internal drive source, moving in the deployment direction; the rope releases the rope on the other side of the inter-bar hinges, and the root hinges retract the rope under the action of the internal drive source, moving in the deployment direction, so as to realize that each hinge unfolds in sequence. The deployment speed of the folding flexible solar panel is achieved by the speed control of the swing drive mechanism.

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