A two-dimensional deployed solar wing and spacecraft

Abstract

The application relates to a two-dimensionally unfolded solar wing and a spacecraft, the two-dimensionally unfolded solar wing comprising a first sailboard, a second sailboard and a third sailboard, the first sailboard being in a quadrilateral structure, a root hinge for hinging with one side of a star body and an inter-board triggering mechanism for cooperating with a triggering rod on the one side of the star body being arranged on a first side edge of the first sailboard, a first locking piece for cooperating with the inter-board triggering mechanism to be locked or unlocked being arranged on one side edge of the second sailboard, and a second locking piece for cooperating with the inter-board triggering mechanism to be locked or unlocked being arranged on one side edge of the third sailboard; a second side edge and a third side edge of the first sailboard are respectively connected with two ends of the first side edge, the second side edge is hinged with one side edge of the second sailboard through a first inter-board hinge, and the third side edge is hinged with one side edge of the third sailboard through a second inter-board hinge; in a folding state, the second sailboard and the third sailboard are respectively folded on two side edges of the first sailboard through the inter-board hinges. The application can reduce the difficulty of the spacecraft attitude adjustment.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, specifically to a two-dimensional deployable solar array and spacecraft. Background Technology

[0002] Solar panels, an indispensable part of spacecraft, primarily provide power. Due to their large size, they are folded before launch and unfold after the spacecraft enters orbit. A common unfolding pattern is along one side in a "Z" shape, with all solar panels on a single plane. For spacecraft with high power consumption, the unfolded area is large, resulting in a greater distance from the celestial body and thus a larger moment of inertia for the solar panels, making it more difficult to adjust the overall attitude of the spacecraft. Summary of the Invention

[0003] In order to solve one or more technical problems existing in the prior art, the present invention provides a two-dimensional deployable solar array and spacecraft.

[0004] The technical solution of this invention to solve the above-mentioned technical problems is as follows: This invention provides a two-dimensional deployable solar panel, including a first solar panel, a second solar panel, and a third solar panel. The first solar panel has a quadrilateral structure. A root hinge for hinged to one side of a celestial body and an inter-panel triggering mechanism for cooperating with a trigger rod on one side of the celestial body are installed on the first side of the first solar panel. A first locking member is provided on one side of the second solar panel to lock or unlock in cooperation with the inter-panel triggering mechanism. A second locking member is provided on one side of the third solar panel to lock or unlock in cooperation with the inter-panel triggering mechanism. The second and third sides of the first solar panel are respectively connected to the two ends of the first side. The second side is hinged to one side of the second solar panel through the first inter-panel hinge, and the third side is hinged to one side of the third solar panel through the second inter-panel hinge.

[0005] In the closed state, the second solar panel is folded onto one side of the first solar panel via the first inter-panel hinge, and the third solar panel is folded onto the other side of the first solar panel via the second inter-panel hinge. The inter-panel triggering mechanism is locked to the first locking member and the second locking member respectively. The first solar panel can be folded onto one side of the celestial body via the root hinge. In the deployed state, the first solar panel is deployed via the root hinge and triggers the inter-panel triggering mechanism. The inter-panel triggering mechanism releases the locks on the first locking member and the second locking member, allowing the second solar panel to deploy under the action of the first inter-panel hinge, and the third solar panel to deploy under the action of the second inter-panel hinge.

[0006] The beneficial effects of this invention are as follows: In the two-dimensional deployable solar array of this invention, after unlocking, all solar panels deploy simultaneously under the action of the root hinge. After the deployment approaches the angle where the root hinge is locked, the inter-panel triggering mechanism is triggered and releases the constraint on other solar panels. The other solar panels then deploy and lock under the action of the inter-panel hinge. The entire solar array is located on one side of the star, with the first solar panel located on one side of the star, and the second and third solar panels located on both sides of the first solar panel. This type of two-dimensional deployable solar array can greatly reduce the rotational inertia of the spacecraft, thereby reducing the difficulty of spacecraft attitude adjustment.

[0007] Based on the above technical solution, the present invention can be further improved as follows.

[0008] Furthermore, the root hinge, the first inter-plate hinge, and the second inter-plate hinge each include a male hinge, a female hinge, a spiral spring, and a rotating shaft. The male hinge and the female hinge are hinged together by the rotating shaft. The spiral spring is sleeved on the rotating shaft and its inner end is fixedly connected to the rotating shaft. The outer end of the spiral spring is connected to the male hinge. In the closed state, the spiral springs on the root hinge, the first inter-plate hinge, and the second inter-plate hinge are all in an energy-storing state.

[0009] The beneficial effect of adopting the above-mentioned further solution is that by setting up a male hinge, a female hinge, a spiral spring and a rotating shaft, the male hinge and the female hinge can be opened in the energy storage state of the spiral spring, thereby opening the sail.

[0010] Furthermore, the root hinge, the first inter-plate hinge, and the second inter-plate hinge each include a locking frame and an arc-shaped slide rail. The arc-shaped slide rail is fixed on the male hinge and arranged coaxially with the rotation shaft. The locking frame is mounted on the female hinge via a torsion spring, and the free end of the locking frame can be pressed against the arc-shaped slide rail under the action of the torsion spring. When the male and female hinges are closed relative to each other, the free end of the locking frame abuts against the arc-shaped slide rail near one end. During the relative unfolding of the male and female hinges, the free end of the locking frame can move along the arc-shaped slide rail.

[0011] The beneficial effect of adopting the above-mentioned further solution is that, by setting a locking frame and an arc-shaped slide rail, when the male hinge and the female hinge are opened relative to each other, the free end of the locking frame can slide along the arc-shaped slide rail.

[0012] Furthermore, a limiting groove is provided on the male hinge, which is located at the other end of the arc-shaped slide rail. When the male hinge and the female hinge are unfolded to a set position, the free end of the locking frame moves along the arc-shaped slide rail and is engaged in the limiting groove.

[0013] The beneficial effect of adopting the above-mentioned further solution is that by setting a limiting groove, when the male hinge and the female hinge are opened to the set position, the free end of the locking frame can be inserted into the limiting groove, thereby limiting the male hinge and the female hinge in the open state.

[0014] Furthermore, the locking frame has a rectangular frame, one end of which is hinged to the female hinge via a pivot, a torsion spring is sleeved on the pivot, and the free end of the locking frame is provided with a roller that can roll along the arc-shaped slide rail; the pivot, the rotating shaft, and the roller are all arranged in parallel.

[0015] The free end of the locking frame is also provided with a contact rod arranged coaxially with the roller. A limit switch is fixed on the male hinge. When the male hinge and the female hinge are unfolded to a set position, the contact rod presses the button of the limit switch and indicates that the position is reached.

[0016] The beneficial effect of adopting the above-mentioned further solution is that by setting rollers, the free end of the locking frame can slide along the arc-shaped slide rail.

[0017] Furthermore, the free end of the female hinge is provided with a first U-shaped snap-fit ​​member, and the free end of the male hinge is provided with a second U-shaped snap-fit ​​member. The snap-fit ​​groove of the first U-shaped snap-fit ​​member faces the side away from the rotation axis and is arranged parallel to the rotation axis. The snap-fit ​​groove of the second U-shaped snap-fit ​​member faces the side away from the rotation axis and is arranged parallel to the rotation axis.

[0018] The beneficial effect of adopting the above-mentioned further solution is that by setting the U-shaped clip, it is convenient to connect and fix it to the windsurfing board.

[0019] Furthermore, an L-shaped mounting plate is snapped into the first U-shaped snap-fit ​​of the root hinge. The L-shaped mounting plate includes two vertically fixed plates, one of which is snapped into the first U-shaped snap-fit ​​of the root hinge, and the other is arranged parallel to the rotation axis of the root hinge and is used to fix it to the star.

[0020] The beneficial effect of adopting the above-mentioned further solution is that by setting an L-shaped mounting plate, it is convenient to connect and fix it to the star.

[0021] Furthermore, a first connecting member is fixed on the rotation axis of the first inter-plate hinge, and a second connecting member is fixed on the rotation axis of the second inter-plate hinge. The first connecting member and the second connecting member are arranged correspondingly along a direction perpendicular to the rotation axis of the second inter-plate hinge, and a rope is provided between the first connecting member and the second connecting member. The female hinge is fixedly connected to the rotation axis, and the male hinge is rotatably connected to the rotation axis.

[0022] The beneficial effect of adopting the above-mentioned further solution is that by setting a rope between the first connector and the second connector, the consistency of the folding and unfolding of the second sail can be achieved.

[0023] Furthermore, the inter-plate triggering mechanism includes a locking rod, a first spring, a slider, and a connecting cylinder. One end of the connecting cylinder is a closed structure, and the other end of the connecting cylinder is provided with a first locking block for locking the first sailboard. The slider is slidably connected inside the connecting cylinder. The locking rod extends from the closed end of the connecting cylinder into the connecting cylinder and is fixedly connected to the slider. A first spring is provided between the slider and the other end of the connecting cylinder. A first limiting hole and a second limiting hole are provided oppositely arranged on the outer peripheral sidewall of the connecting cylinder.

[0024] The first locking member includes a first limiting rod and a second locking block for locking the second sail. One end of the first limiting rod is connected to the second locking block, and the other end of the first limiting rod extends radially into the first limiting hole along the connecting cylinder and can be adapted to lock with the slider. The second locking member includes a second limiting rod and a third locking block for locking the third sail. One end of the second limiting rod is connected to the third locking block, and the other end of the second limiting rod extends radially into the second limiting hole along the connecting cylinder and can be adapted to lock with the slider.

[0025] The beneficial effect of adopting the above-mentioned further solution is that: the inter-plate triggering mechanism is provided with a locking rod, a first spring, a slider and a connecting cylinder. When the triggering rod presses the locking rod, the locking rod compresses the first spring and causes the slider to release the locking limit of the first limit rod and the second limit rod, thereby realizing the opening of the second and third sails connected by the first and second limit rods relative to the first sail.

[0026] Furthermore, the first snap-fit ​​block has a second snap-fit ​​groove for snapping the second sail, the second snap-fit ​​groove facing away from the first limiting rod and perpendicular to the first limiting rod, and the second snap-fit ​​block has a third snap-fit ​​groove for snapping the third sail, the third snap-fit ​​groove facing away from the second limiting rod and perpendicular to the second limiting rod.

[0027] The present invention also provides a spacecraft, including a two-dimensional deployable solar array as described above, and a celestial body. One side of the celestial body is hinged to the first side of the first solar panel via a root hinge. The side of the celestial body is also provided with a trigger rod that cooperates with the inter-panel triggering mechanism. The side of the celestial body is also provided with a locking and releasing mechanism. A locking rod is vertically fixed on the side of the second solar panel near the first solar panel. Both the first and third solar panels have through holes for the locking rod to pass through. When the first, second, and third solar panels are in a folded and closed state on the celestial body, the locking rod passes through the through holes on the first and third solar panels and is locked by the locking and releasing mechanism.

[0028] The beneficial effects of the present invention are as follows: In the spacecraft of the present invention, after the solar array is unlocked, the solar panels deploy simultaneously. After the inter-panel triggering mechanism is triggered, the restriction on the remaining solar panels is released. The remaining solar panels deploy and lock under the force of the inter-panel hinge, thereby achieving the purpose of overall two-dimensional deployment of the solar array. Attached Figure Description

[0029] Figure 1 This is a three-dimensional structural diagram of a two-dimensionally deployed solar array in its closed state according to the present invention;

[0030] Figure 2 This is a three-dimensional structural diagram illustrating the deployment process of a two-dimensional solar array according to the present invention. Figure 1 ;

[0031] Figure 3 This is a three-dimensional structural diagram illustrating the deployment process of a two-dimensional solar array according to the present invention. Figure 2 ;

[0032] Figure 4 This is a three-dimensional structural diagram of a two-dimensionally deployed solar array according to the present invention.

[0033] Figure 5 for Figure 4 Enlarged structural diagram of section A in the middle;

[0034] Figure 6 for Figure 4 Enlarged structural diagram of section B in the middle;

[0035] Figure 7 for Figure 4 Enlarged structural diagram of section C;

[0036] Figure 8 This is a three-dimensional structural diagram of the first inter-plate hinge of the present invention in its unfolded state;

[0037] Figure 9 This is a three-dimensional structural diagram of the first inter-plate hinge of the present invention in the closed state;

[0038] Figure 10This is a three-dimensional structural diagram of the inter-plate triggering mechanism, the first locking member, and the second locking member of the present invention.

[0039] Figure 11 This is a schematic cross-sectional view of the inter-plate triggering mechanism, the first locking member, and the second locking member of the present invention. Figure 1 ;

[0040] Figure 12 This is a schematic cross-sectional view of the inter-plate triggering mechanism, the first locking member, and the second locking member of the present invention. Figure 2 .

[0041] The attached diagram lists the components represented by each number as follows:

[0042] 1. Celestial body; 11. First sailboard; 12. Second sailboard; 13. Third sailboard; 14. First side; 15. Second side; 16. Third side; 17. Trigger rod; 18. Through hole;

[0043] 2. Root hinge; 21. First inter-plate hinge; 22. Second inter-plate hinge; 23. Limit switch; 24. First connector; 25. Second connector; 26. Contact rod;

[0044] 3. Inter-plate triggering mechanism; 31. First locking element; 32. Second locking element; 33. Locking rod; 34. First spring; 35. Slider; 36. Connecting cylinder; 37. First locking block; 38. First limiting hole; 39. Second limiting hole; 391. First limiting rod; 392. Second locking block; 393. Second limiting rod; 394. Third locking block; 395. Second spring; 396. Third spring;

[0045] 4. Male hinge; 41. Female hinge; 42. Spiral spring; 43. Rotary shaft; 44. Locking frame; 45. Arc-shaped slide rail; 46. Limiting groove; 47. Rotary shaft; 48. Torsion spring; 49. Roller; 491. L-shaped mounting plate; 492. First U-shaped snap-fit ​​connector; 493. Second U-shaped snap-fit ​​connector; 494. Connecting rod;

[0046] 5. Locking release mechanism; 51. Locking rod. Detailed Implementation

[0047] The principles and features of the present invention are described below. The examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0048] Example 1

[0049] like Figures 1-12As shown, a two-dimensional deployable solar panel of this embodiment includes a first solar panel 11, a second solar panel 12, and a third solar panel 13. The first solar panel 11 has a quadrilateral structure. A root hinge 2 for hinged to one side of a satellite 1 and an inter-panel triggering mechanism 3 for cooperating with a trigger rod 17 on one side of the satellite 1 are installed on the first side 14 of the first solar panel 11. A first locking member 31 is provided on one side of the second solar panel 12 to lock or unlock in cooperation with the inter-panel triggering mechanism 3. A second locking member 32 is provided on one side of the third solar panel 13 to lock or unlock in cooperation with the inter-panel triggering mechanism 3. The second side 15 and the third side 16 of the first solar panel 11 are respectively connected to the two ends of the first side 14. The second side 15 is hinged to one side of the second solar panel 12 through the first inter-panel hinge 21, and the third side 16 is hinged to one side of the third solar panel 13 through the second inter-panel hinge 22.

[0050] In the closed state, the second sail 12 is folded onto one side of the first sail 11 via the first inter-panel hinge 21, and the third sail 13 is folded onto the other side of the first sail 11 via the second inter-panel hinge 22. The inter-panel triggering mechanism 3 is locked in place with the first locking member 31 and the second locking member 32 respectively. The first sail 11 can be folded onto one side of the celestial body via the root hinge 2. In the unfolded state, the first sail 11 unfolds via the root hinge 2 and triggers the inter-panel triggering mechanism 3. The inter-panel triggering mechanism 3 releases the locks on the first locking member 31 and the second locking member 32, causing the second sail 12 to unfold under the action of the first inter-panel hinge 21, and the third sail 13 to unfold under the action of the second inter-panel hinge 22.

[0051] In this embodiment, the two-dimensional deployable solar panel can consist of multiple deployable solar panels. The solar panel connected to the root hinge, when folded, is located in the middle of the remaining solar panels. The solar panels to be deployed on both sides are connected via inter-panel hinges. The number of solar panels connected to the root hinge can be one or more. In this embodiment, the first, second, and third solar panels can be positioned on the same plane after deployment.

[0052] In this embodiment, the solar panels of the two-dimensional solar array are stacked together in the folded state and pressed against the surface of the planet by the force of the locking and releasing mechanism. At the same time, the root hinge is connected to the first solar panel in the middle. When the locking and releasing mechanism is unlocked, all solar panels unfold simultaneously under the force of the root hinge. When the root hinge approaches the locked state, the inter-panel triggering mechanism is triggered and releases the limit between each solar panel. The remaining solar panels unfold under the force of the inter-panel hinge. To ensure the consistency of the unfolding angle of the remaining solar panels, a rope linkage mechanism can be installed on the inter-panel hinge on the same side to ensure the synchronous unfolding of the remaining solar panels. After each solar panel is unfolded to the correct position, the inter-panel hinge locks and maintains the unfolded state.

[0053] In this embodiment, the two-dimensional deployable solar array, after unlocking, deploys all solar panels simultaneously under the action of the root hinge. After the deployment approaches the angle where the root hinge is locked, the inter-panel triggering mechanism is triggered and releases the constraint on other solar panels. The other solar panels then deploy and lock under the action of the inter-panel hinge. This type of two-dimensional deployable solar array can greatly reduce the rotational inertia of the spacecraft, thereby reducing the difficulty of spacecraft attitude adjustment.

[0054] Example 2

[0055] Based on Embodiment 1, this embodiment provides a preferred structure for the root hinge 2, the first inter-plate hinge 21, and the second inter-plate hinge 22.

[0056] like Figures 1-9 As shown, in this embodiment, the root hinge 2, the first inter-plate hinge 21, and the second inter-plate hinge 22 each include a male hinge 4, a female hinge 41, a spiral spring 42, and a rotating shaft 43. The male hinge 4 and the female hinge 41 are hinged together by the rotating shaft 43. The spiral spring 42 is sleeved on the rotating shaft 43, with its inner end fixedly connected to the rotating shaft 43, and its outer end connected to the male hinge 4. In the closed state, the spiral springs 42 on the root hinge 2, the first inter-plate hinge 21, and the second inter-plate hinge 22 are all in an energy-storing state. By providing the male hinge, the female hinge, the spiral spring, and the rotating shaft, the male and female hinges can be opened in the energy-storing state of the spiral spring, thereby opening the sail.

[0057] like Figures 5-9 As shown, in a further embodiment, the root hinge 2, the first inter-plate hinge 21, and the second inter-plate hinge 22 each include a locking frame 44 and an arc-shaped slide rail 45. The arc-shaped slide rail 45 is fixed on the male hinge 4 and coaxially arranged with the rotation shaft 43. The locking frame 44 is mounted on the female hinge 41 via a torsion spring 48, and the free end of the locking frame 44 can be pressed against the arc-shaped slide rail 45 under the action of the torsion spring 48. When the male hinge 4 and the female hinge 41 are closed relative to each other, the free end of the locking frame 44 abuts against one end of the arc-shaped slide rail 45. During the relative unfolding of the male hinge 4 and the female hinge 41, the free end of the locking frame 44 can move along the arc-shaped slide rail 45. By setting the locking frame and the arc-shaped slide rail, when the male hinge and the female hinge are opened relative to each other, the free end of the locking frame can slide along the arc-shaped slide rail.

[0058] like Figure 8 and Figure 9As shown, in a preferred embodiment, the male hinge 4 is further provided with a limiting groove 46, which is located at the other end of the arc-shaped slide rail 45. When the male hinge 4 and the female hinge 41 are unfolded to a set position, the free end of the locking frame 44 moves along the arc-shaped slide rail 45 and engages in the limiting groove 46. By setting the limiting groove, when the male and female hinges are opened to the set position, the free end of the locking frame can be engaged in the limiting groove, thereby limiting the male and female hinges in the open state. After the hinges are unfolded to a certain angle, the locking frame is pressed into the limiting groove under the action of the torsion spring, realizing the locking of the hinges after they are unfolded. The power for unfolding the male and female hinges comes from the energy stored in the spiral spring itself. The inner ring of the spiral spring is connected to the female hinge through a rotating shaft, and the outer ring is connected to the male hinge through a connecting rod 494. When the constraints of the male and female hinges are released, the hinges unfold and lock under the action of the spiral spring.

[0059] like Figure 7 and Figure 8 As shown, specifically, the locking frame 44 has a rectangular frame. One end of the locking frame 44 is hinged to the female hinge 41 via a pivot 47. A torsion spring 48 is fitted on the pivot 47. The free end of the locking frame 44 is provided with a roller 49 that can roll along the arc-shaped slide rail 45. The pivot 47, the rotation shaft 43, and the roller 49 are all arranged in parallel. By providing the roller, it is convenient for the free end of the locking frame to slide along the arc-shaped slide rail. A contact rod 26 is also provided on one side of the free end of the locking frame 44, which is coaxially arranged with the roller 49. A limit switch 23 is fixed on the male hinge 4. When the male hinge 4 and the female hinge 41 are unfolded to a set position, the contact rod 26 presses the button of the limit switch 23 to indicate the position.

[0060] like Figures 7-9 As shown, in one specific embodiment, the free end of the female hinge 41 is provided with a first U-shaped snap-fit ​​member 492, and the free end of the male hinge 4 is provided with a second U-shaped snap-fit ​​member 493. The snap-fit ​​groove of the first U-shaped snap-fit ​​member 492 faces away from the rotation axis 43 and is arranged parallel to the rotation axis 43. The snap-fit ​​groove of the second U-shaped snap-fit ​​member 493 faces away from the rotation axis 43 and is arranged parallel to the rotation axis 43. By providing U-shaped snap-fit ​​members, it is convenient to connect and fix them to the sailboard.

[0061] like Figure 7 As shown, in one specific embodiment, an L-shaped mounting plate 491 is snapped into the first U-shaped snap-fit ​​member 492 of the root hinge 2. The L-shaped mounting plate 491 includes two vertically fixedly connected plates. One plate is snapped and fixed into the first U-shaped snap-fit ​​member 492 of the root hinge 2, and the other plate is arranged parallel to the rotation axis of the root hinge 2 and is used for fixed connection to the star body 1. By setting the L-shaped mounting plate, it is convenient to connect and fix it to the star body.

[0062] In this embodiment, the root hinge 2, the first inter-plate hinge 21, and the second inter-plate hinge 22 are all equipped with spiral springs, which can automatically unfold and lock in an unrestrained state. The unfolding angle of the root hinge is determined according to the actual state. For example, by setting the angle of the arc-shaped slide rail and the position of the limiting groove, the inter-plate unfolding angle is 180°.

[0063] Example 3

[0064] Based on Embodiment 1 or Embodiment 2, this embodiment provides a synchronous folding and unfolding scheme for a windsurfing system. For example... Figures 4-6 As shown, a first connecting member 24 is fixed to the rotation axis 43 of the first inter-plate hinge 21, and a second connecting member 25 is fixed to the rotation axis 43 of the second inter-plate hinge 22. The first connecting member 24 and the second connecting member 25 are arranged correspondingly along a direction perpendicular to the rotation axis 43 of the second inter-plate hinge 22, and a rope is provided between the first connecting member 24 and the second connecting member 25. The female hinge 41 is fixedly connected to the rotation axis 43, and the male hinge 4 is rotatably connected to the rotation axis 43. Both the first connecting member 24 and the second connecting member 25 can adopt a wheel structure coaxial with their respective rotation axes. By providing a rope between the first and second connecting members, the consistency of the folding and unfolding of the second and third sails can be achieved. The rope, the first connecting member, and the second connecting member constitute a rope linkage mechanism. Under the action of the rope linkage mechanism, the second and third sails unfold synchronously, and after unfolding, the second and third sails are located on opposite sides of the first sail.

[0065] Example 4

[0066] Based on any of the above embodiments, this embodiment provides a preferred structural form of the inter-plate triggering mechanism 3.

[0067] like Figures 10-12As shown, the inter-plate triggering mechanism 3 includes a locking rod 33, a first spring 34, a slider 35, and a connecting cylinder 36. One end of the connecting cylinder 36 is a closed structure, and the other end of the connecting cylinder 36 is provided with a first locking block 37 for locking the first sail 11. The slider 35 is slidably connected inside the connecting cylinder 36. The locking rod 33 extends from the closed end of the connecting cylinder 36 into the connecting cylinder 36 and is fixedly connected to the slider 35. A first spring 34 is provided between the slider 35 and the other end of the connecting cylinder 36. A first limiting hole 38 and a second limiting hole 39 are provided on the outer peripheral sidewall of the connecting cylinder 36, which are arranged opposite to each other. The first locking member 31 includes... A first limiting rod 391 and a second locking block 392 for locking the second sail 12 are included. One end of the first limiting rod 391 is connected to the second locking block 392, and the other end of the first limiting rod 391 extends radially into the first limiting hole 38 along the connecting cylinder 36 and can be fitted and locked with the slider 35. The second locking member 32 includes a second limiting rod 393 and a third locking block 394 for locking the third sail 13. One end of the second limiting rod 393 is connected to the third locking block 394, and the other end of the second limiting rod 393 extends radially into the second limiting hole 39 along the connecting cylinder 36 and can be fitted and locked with the slider 35. The inter-plate triggering mechanism is provided with a locking rod, a first spring, a slider, and a connecting cylinder. When the triggering rod presses the locking rod, the locking rod compresses the first spring and causes the slider to release the locking and limiting of the first limiting rod and the second limiting rod, thereby realizing the opening of the second sail and the third sail connected by the first limiting rod and the second limiting rod relative to the first sail.

[0068] like Figures 10-12 As shown, in a specific embodiment, the first snap-fit ​​block 37 has a second snap-fit ​​groove for snapping the second sail 12, the second snap-fit ​​groove facing away from the first limiting rod 391 and perpendicular to the first limiting rod 391. The second snap-fit ​​block 392 has a third snap-fit ​​groove for snapping the third sail 13, the third snap-fit ​​groove facing away from the second limiting rod 393 and perpendicular to the second limiting rod 393. Specifically, the second sail 12 can be fixed in the second snap-fit ​​groove, and the third sail 13 can be fixed in the third snap-fit ​​groove. When the inter-board triggering mechanism is in the locked state, the first sail, the second sail, and the third sail are in a parallel folded state.

[0069] Specifically, such as Figures 10-12As shown, the first limiting rod 391 slides through the second locking block 392 and a second spring 395 is sleeved on the end opposite to the locking rod 33. The second spring 395 is connected between one end of the first limiting rod 391 and the second locking block 392. The second limiting rod 393 slides through the third locking block 394 and a third spring 396 is sleeved on the end opposite to the locking rod 33. The third spring 396 is connected between one end of the second limiting rod 393 and the third locking block 394.

[0070] The inter-plate triggering mechanism in this embodiment is a purely mechanical triggering mechanism. Its components are interconnected with the sails that need to be deployed. After the trigger rod triggers the locking rod, the inter-plate triggering mechanism can release the constraints on the second and second sails. In this embodiment, the second spring 395 and the third spring 396 are always in a compressed state. One end of the first limiting rod 391 and one end of the second limiting rod 393 are provided with steps, which can limit the engagement of the slider 35 with the corresponding steps. The second spring 395 and the third spring 396 press the corresponding limiting rods and engage with the steps on the slider. When the locking rod 33 is pushed, the first spring 34 is compressed. At this time, the limiting rods disengage from the steps on the slider, thereby releasing the constraint of the limiting rods. Under the action of the second spring 395 and the third spring 396, the limiting rods can be quickly pulled out of the slider. This is equivalent to the second spring and the third spring pulling the first limiting rod 391 and the second limiting rod 393 out of the first limiting hole and the second limiting hole, respectively. When the solar panels are subjected to vibration under compressed conditions, the different amplitudes of each solar panel cause the first, second, and third locking blocks to vibrate. Furthermore, each solar panel is connected through an inter-panel triggering mechanism. To prevent excessive force generated by vibration displacement from acting on the inter-panel triggering mechanism, the limiting rod can move axially when the vibration produces different amplitudes on each solar panel.

[0071] Example 5

[0072] This embodiment provides a spacecraft, including a two-dimensional deployable solar array as described in any of the above embodiments, and a star body 1. One side of the star body 1 is hinged to the first side 14 of the first solar panel 11 via a root hinge 2. The side of the star body 1 is also provided with a trigger rod 17 that cooperates with the inter-panel trigger mechanism 3. The side of the star body 1 is also provided with a locking and releasing mechanism 5. A locking rod 51 is vertically fixed on the side of the second solar panel 12 near the first solar panel 11. The first solar panel 11 and the third solar panel 13 are both provided with through holes 18 for the locking rod 51 to pass through. When the first solar panel 11, the second solar panel 12 and the third solar panel 13 are in a folded and closed state on the star body 1, the locking rod 51 passes through the through holes 18 on the first solar panel 11 and the third solar panel 13 and is locked by the locking and releasing mechanism 5.

[0073] The locking and releasing mechanism 5 can be one or more, and can be a commonly used spacecraft mechanism, such as a split nut locking and releasing mechanism. After the locking and releasing mechanism 5 is unlocked, the three solar panels deploy simultaneously under the force of the root hinge. Before the inter-panel triggering mechanism is unlocked, the solar panels do not move relative to each other.

[0074] In this embodiment of the spacecraft, after the locking and releasing mechanism 5 is unlocked, the first solar panel drives the second and third solar panels to unfold relative to the celestial body under the action of the root hinge. After the root hinge unfolds to a certain angle, the inter-panel triggering mechanism unlocks and releases the constraint on the second and third solar panels. Under the action of the first inter-panel hinge and the second inter-panel hinge, the second and third solar panels unfold and lock relative to the first solar panel, thereby achieving the purpose of two-dimensional unfolding.

[0075] In this embodiment of the spacecraft, after the solar array is unlocked, the solar panels deploy simultaneously. After the inter-panel triggering mechanism is triggered, the restriction on the remaining solar panels is released. The remaining solar panels deploy and lock under the force of the inter-panel hinge, thereby achieving the purpose of overall two-dimensional deployment of the solar array.

[0076] In the description of this invention, it should be understood that the terms "inner", "outer", "axial", "radial", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0077] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0078] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0079] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0080] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0081] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A two-dimensional deployable solar array, characterized in that, The system includes a first solar panel, a second solar panel, and a third solar panel. The first solar panel has a quadrilateral structure. A root hinge for hinged to one side of the celestial body and an inter-panel triggering mechanism for engaging with a trigger rod on one side of the celestial body are installed on the first side of the first solar panel. A first locking member is provided on one side of the second solar panel to lock or unlock in cooperation with the inter-panel triggering mechanism. A second side and a third side of the first solar panel are respectively connected to the two ends of the first side. The second side is hinged to one side of the second solar panel via the first inter-panel hinge, and the third side is hinged to one side of the third solar panel via the second inter-panel hinge. In the closed state, the second solar panel is folded onto one side of the first solar panel via the first inter-panel hinge, and the third solar panel is folded onto the other side of the first solar panel via the second inter-panel hinge. The inter-panel triggering mechanism is locked to the first locking member and the second locking member respectively. The first solar panel can be folded onto one side of the celestial body via the root hinge. In the deployed state, the first solar panel is deployed via the root hinge and triggers the inter-panel triggering mechanism. The inter-panel triggering mechanism releases the locks on the first locking member and the second locking member, allowing the second solar panel to deploy under the action of the first inter-panel hinge, and the third solar panel to deploy under the action of the second inter-panel hinge. The inter-plate triggering mechanism includes a locking rod, a first spring, a slider, and a connecting cylinder. One end of the connecting cylinder is closed, and the other end of the connecting cylinder is provided with a first locking block for locking the first sail. The slider is slidably connected inside the connecting cylinder. The locking rod extends from the closed end of the connecting cylinder into the connecting cylinder and is fixedly connected to the slider. A first spring is provided between the slider and the other end of the connecting cylinder. A first limiting hole and a second limiting hole are opened on the outer peripheral sidewall of the connecting cylinder, which are arranged opposite to each other. The first locking member includes a first limiting rod and a second locking block for locking the second sail. One end of the first limiting rod is connected to the second locking block, and the other end of the first limiting rod extends radially into the first limiting hole along the connecting cylinder and can be adapted to lock the slider. The second locking member includes a second limiting rod and a third locking block for locking the third sail. One end of the second limiting rod is connected to the third locking block, and the other end of the second limiting rod extends radially into the second limiting hole along the connecting cylinder and can be adapted to lock the slider.

2. The two-dimensional deployable solar array according to claim 1, characterized in that, The root hinge, the first inter-plate hinge, and the second inter-plate hinge each include a male hinge, a female hinge, a spiral spring, and a rotating shaft. The male and female hinges are hinged together by the rotating shaft. The spiral spring is sleeved on the rotating shaft and its inner end is fixedly connected to the rotating shaft. The outer end of the spiral spring is connected to the male hinge. In the closed state, the spiral springs on the root hinge, the first inter-plate hinge, and the second inter-plate hinge are all in an energy-storing state.

3. The two-dimensional deployable solar array according to claim 2, characterized in that, The root hinge, the first inter-plate hinge, and the second inter-plate hinge each include a locking frame and an arc-shaped slide rail. The arc-shaped slide rail is fixed on the male hinge and arranged coaxially with the rotation shaft. The locking frame is mounted on the female hinge via a torsion spring, and the free end of the locking frame can be pressed against the arc-shaped slide rail under the action of the torsion spring. When the male and female hinges are closed relative to each other, the free end of the locking frame abuts against the arc-shaped slide rail near one end. During the relative unfolding of the male and female hinges, the free end of the locking frame can move along the arc-shaped slide rail. The male hinge is also provided with a limiting groove, which is located at the other end of the arc-shaped slide rail. When the male hinge and the female hinge are unfolded to a set position, the free end of the locking frame moves along the arc-shaped slide rail and gets stuck in the limiting groove.

4. The two-dimensional deployable solar array according to claim 3, characterized in that, The locking frame has a rectangular frame, one end of which is hinged to the female hinge via a pivot, a torsion spring is sleeved on the pivot, and the free end of the locking frame is provided with a roller that can roll along the arc-shaped slide rail; the pivot, the rotating shaft, and the roller are all arranged in parallel. The free end of the locking frame is also provided with a contact rod arranged coaxially with the roller. A limit switch is fixed on the male hinge. When the male hinge and the female hinge are unfolded to a set position, the contact rod presses the button of the limit switch and indicates that the position is reached.

5. The two-dimensional deployable solar array according to claim 2, characterized in that, The free end of the female hinge is provided with a first U-shaped snap-fit ​​component, and the free end of the male hinge is provided with a second U-shaped snap-fit ​​component. The snap-fit ​​groove of the first U-shaped snap-fit ​​component faces the side away from the rotation axis and is arranged parallel to the rotation axis. The snap-fit ​​groove of the second U-shaped snap-fit ​​component faces the side away from the rotation axis and is arranged parallel to the rotation axis.

6. The two-dimensional deployable solar array according to claim 2, characterized in that, An L-shaped mounting plate is snapped into the first U-shaped snap-fit ​​of the root hinge. The L-shaped mounting plate includes two vertically fixed plates. One plate is snapped into the first U-shaped snap-fit ​​of the root hinge, and the other plate is arranged parallel to the rotation axis of the root hinge and is used to fix it to the star.

7. The two-dimensional deployable solar array according to claim 2, characterized in that, A first connector is fixed on the rotation axis of the first inter-plate hinge, and a second connector is fixed on the rotation axis of the second inter-plate hinge. The first connector and the second connector are arranged correspondingly along a direction perpendicular to the rotation axis of the second inter-plate hinge, and a rope is provided between the first connector and the second connector. The female hinge is fixedly connected to the rotation axis, and the male hinge is rotatably connected to the rotation axis.

8. The two-dimensional deployable solar array according to claim 1, characterized in that, The first snap-fit ​​block has a second snap-fit ​​groove for snapping the second sail, the second snap-fit ​​groove facing away from the first limiting rod and perpendicular to the first limiting rod. The second snap-fit ​​block has a third snap-fit ​​groove for snapping the third sail, the third snap-fit ​​groove facing away from the second limiting rod and perpendicular to the second limiting rod.

9. A spacecraft, characterized in that, The system includes a two-dimensional deployable solar array as described in any one of claims 1 to 8, and further includes a celestial body. One side of the celestial body is hinged to the first side of the first solar panel via a root hinge. The side of the celestial body is also provided with a trigger rod that cooperates with the inter-panel triggering mechanism. The side of the celestial body is also provided with a locking and releasing mechanism. A locking rod is vertically fixed on the side of the second solar panel near the first solar panel. Both the first and third solar panels have through holes for the locking rod to pass through. When the first, second, and third solar panels are in a folded and closed state on the celestial body, the locking rod passes through the through holes on the first and third solar panels and is locked by the locking and releasing mechanism.

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