A device for automatically locking a satellite after it is deployed and retracted

Abstract

The present invention discloses a satellite automatic locking device after deployment and retraction, belonging to the field of aerospace equipment. A satellite automatic locking device after deployment and retraction comprises a first solar wing panel, a second solar wing panel is arranged on one side of the first solar wing panel, a protective frame is installed at the bottom of the first solar wing panel, and solar panels are installed on the surfaces of the first solar wing panel and the second solar wing panel, and also comprises: an adjustment component, which is arranged on the bottom surface of the first solar wing panel and is used to adjust the deployment angle of the second solar wing panel; a support component; the present invention can adjust the extension angle between the first solar wing panel and the second solar wing panel when in use through the mutual cooperation of the adjustment component, the support component and the support component, thereby adjusting the irradiation angle between the solar panel and the sun, fully absorbing solar energy, and having a stable structure, and is suitable for locking and limiting within the angle adjustment range.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace equipment, and in particular to a device for automatically locking a satellite after it is unfolded and retracted. Background Art

[0002] The solar panels of micro-nano satellites are in a folded state during the launch phase, and are deployed and locked after the satellite-rocket separation to ensure the energy supply of the entire satellite. During the launch phase, the deployment and locking device and the clamping device fix the solar panels on the satellite body to achieve a high-rigidity connection between the solar panels and the entire satellite, ensuring that the solar panels and other accessories can withstand the complex environment of impact, vibration and overload during the launch phase without being damaged; after the satellite-rocket separation, the unlocking function is completed according to the program control or remote control command to release the constraints on the solar cell array, and the deployment spring in the deployment and locking mechanism provides the driving torque, and the deployment and locking mechanism realizes the deployment and locking of the solar panels and provides a signal that the solar panels are deployed in place.

[0003] The solar panels installed on the solar wings of satellites are used to absorb solar energy and convert it into electrical energy to provide kinetic energy for the satellite. In the prior art, when the satellite solar wings are extended, most of them can only be locked and limited in the extended state. However, in actual use, the locking mechanism is inconvenient to adjust and control the deployment angle of the solar wings, resulting in poor radiation absorption effect of the solar panels on the solar wings during the operation of the satellite. Summary of the invention

[0004] The purpose of the present invention is to solve the problem that the locking mechanism used to lock the extension of the solar wing in the prior art is inconvenient to adjust the deployment angle of the solar wing panel, and to propose an automatic locking device after the satellite is deployed and retracted.

[0005] In order to achieve the above-mentioned objectives, the present invention adopts the following technical solutions: a device for automatically locking a satellite after unfolding and retracting, comprising a first solar wing panel, a second solar wing panel being arranged on one side of the first solar wing panel, a protective frame being installed on the bottom of the first solar wing panel, solar panels being installed on the surfaces of the first solar wing panel and the second solar wing panel, and also comprising: an adjustment component, arranged on the bottom surface of the first solar wing panel, for adjusting the unfolding angle of the second solar wing panel; a support component, located in the protective frame and installed on the bottom surface of the first solar wing panel, for limiting the support; a support component, arranged on the back side of the second solar wing panel, for supporting and reinforcing the second solar wing panel.

[0006] Preferably, the adjustment component includes a first driving part fixed to the bottom surface of the first solar wing panel, the output end of the first driving part is connected to a rotating shaft, the end of the rotating shaft passes through the protective frame and extends to the outside where a first rotating gear is fixed, the surface of the first rotating gear is meshed with a second rotating gear, a first connecting shaft is fixed at the axis of the second rotating gear, one end of the first connecting shaft is rotatably connected to the first solar wing panel through a bearing, the surface of the first connecting shaft is meshed with a third rotating gear, a second connecting shaft is fixed at the axis of the third rotating gear, the end of the second connecting shaft is rotatably connected to the first solar wing panel through a bearing, both ends of the second connecting shaft are fixed with connecting pieces, one end of the connecting piece is fixed with a fixed block, and the ends of the two fixed blocks are fixedly connected to the second solar wing panel.

[0007] Preferably, a linkage gear is fixed on the surface of the rotating shaft, a rack is meshed on the surface of the linkage gear, a support plate is fixed to one end of the rack, a groove is provided on the surface of the support plate, and an anti-sliding block is arranged inside the groove.

[0008] Preferably, a clamping block is provided above the support plate, a sliding rod is fixed on the top of the clamping block, a movable block is connected to the end of the sliding rod, the movable block is slidably connected in the support tube, a movable groove is provided on the inner wall of the support tube, a movable block is slidably connected in the movable groove, the movable block is fixedly connected to the movable block, an extrusion spring is fixed on the top surface of the movable block, the extrusion spring is fixedly connected to the inner wall of the support tube, a support rod is fixed on the top of the support tube, and the end of the support rod is connected to the second driving part.

[0009] Preferably, a slider is fixed to the top of the rack, support blocks are fixed to both side surfaces of the slider, the slider and the support blocks are slidably connected in a T-shaped slide groove, and the T-shaped slide groove is provided on the bottom surface of the first solar wing panel.

[0010] Preferably, the first solar wing panel and the second solar wing panel are of the same size, and the solar panels are symmetrically distributed on the surfaces of the first solar wing panel and the second solar wing panel.

[0011] Preferably, a mounting block is fixed to one side of the second driving part, a limiting block is fixed to one side of the mounting block, the limiting block is slidably connected in a limiting groove, and the limiting groove is provided on the back side of the second solar wing panel.

[0012] Preferably, a third driving unit is fixed to one end of the mounting block, and the third driving unit is fixedly mounted on a fixing plate, and one end of the fixing plate is fixedly connected to the second solar wing panel.

[0013] Preferably, a torsion spring is provided between the first solar wing panel and the second solar wing panel, a fixing piece is fixed to the end of the torsion spring, and the two fixing pieces are respectively mounted on the surfaces of the first solar wing panel and the second solar wing panel.

[0014] Preferably, a connecting portion is fixed to one end of the first solar wing panel, and a mounting shaft is rotatably arranged on the surface of the connecting portion via a bearing.

[0015] Compared with the prior art, the present invention provides a device for automatically locking a satellite after it is unfolded and retracted, which has the following beneficial effects:

[0016] 1. The satellite automatically locks the device after unfolding and retracting. By setting the adjustment component on the first solar wing panel, it is convenient to drive the second solar wing panel to rotate, adjust the extension angle between the first solar wing panel and the second solar wing panel, and then facilitate the adjustment of the irradiation angle of the solar panel, so as to better absorb solar energy and improve the working efficiency of the satellite.

[0017] 2. This kind of satellite automatically locks the device after unfolding and retracting. Through the cooperation between the adjustment component and the support component, during use, the support component is driven to operate, so that the support plate at one end of the support component extends from one end of the first solar wing panel, which has a good supporting effect on the extended state of the second solar wing panel, and limits the second solar wing panel, thereby maintaining the stability of the structure.

[0018] 3. This kind of satellite automatically locks after unfolding and retracting. Through the mutual cooperation of the supporting assembly and the supporting assembly, when the second solar wing panel is unfolded, the supporting assembly is used to support and protect the second solar wing panel, thereby improving the stopping effect of the second solar wing panel after extension, and adapting to the locking limit within the angle adjustment range, further improving the stability of the overall structure.

[0019] The parts not involved in the device are the same as the prior art or can be implemented by the prior art. The present invention can adjust the extension angle between the first solar wing panel and the second solar wing panel through the cooperation of the adjusting component, thereby adjusting the irradiation angle between the solar panel and the sun to fully absorb solar energy. At the same time, the structure is stable and suitable for locking and limiting within the angle adjustment range. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic diagram of the structure of a device for automatically locking a satellite after it is unfolded and retracted, as proposed by the present invention;

[0021] Figure 2 A schematic diagram of the side structure of a device for automatically locking a satellite after expansion and contraction proposed by the present invention;

[0022] Figure 3The invention proposes a device for automatically locking a satellite after it is unfolded and retracted. Figure 2 Schematic diagram of the AA section structure;

[0023] Figure 4 This is a rear view structural schematic diagram of a device for automatically locking a satellite after expansion and contraction proposed by the present invention;

[0024] Figure 5 This is a schematic diagram of the top view of the structure of a device for automatically locking a satellite after it is unfolded and retracted, as proposed by the present invention;

[0025] Figure 6 The invention proposes a device for automatically locking a satellite after it is unfolded and retracted. Figure 5 Schematic diagram of the structure of the middle BB section;

[0026] Figure 7 This is another rear view structural schematic diagram of a satellite automatic locking device after expansion and contraction proposed by the present invention;

[0027] Figure 8 The invention proposes a device for automatically locking a satellite after it is unfolded and retracted. Figure 7 Schematic diagram of the CC cross-section structure.

[0028] In the figure: 1, first solar wing panel; 2, second solar wing panel; 3, protection frame; 4, solar panel; 5, adjustment assembly; 501, first driving part; 502, rotating shaft; 503, first rotating gear; 504, second rotating gear; 505, first connecting shaft; 506, third rotating gear; 507, second connecting shaft; 508, connecting member; 509, fixing block; 6, supporting assembly; 601, linkage gear; 602, rack; 603, slider; 604, supporting block; 605, T-shaped slide groove; 606, support plate; 607, groove; 608, anti-sliding block; 7, support assembly; 701, tightening block; 702, slide rod; 703, movable block; 704, support cylinder; 705, moving block; 706, moving groove; 707, extrusion spring; 708, support rod; 709, second drive unit; 8, mounting block; 9, limit block; 10, limit groove; 11, third drive unit; 12, fixing plate; 13, torsion spring; 14, fixing piece; 15, connecting part; 16, mounting shaft. DETAILED DESCRIPTION

[0029] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0030] In the description of the present invention, it is necessary to understand that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0031] like Figure 1-8 As shown, a device for automatically locking a satellite after unfolding and retracting of the present invention comprises a first solar wing panel 1, a second solar wing panel 2 is arranged on one side of the first solar wing panel 1, a protective frame 3 is installed at the bottom of the first solar wing panel 1, and solar panels 4 are installed on the surfaces of the first solar wing panel 1 and the second solar wing panel 2, and also comprises: an adjusting component 5, which is arranged on the bottom surface of the first solar wing panel 1, and is used to adjust the unfolding angle of the second solar wing panel 2; a supporting component 6, which is located in the protective frame 3 and is installed on the bottom surface of the first solar wing panel 1, and is used to limit the support; a supporting component 7, which is arranged on the back of the second solar wing panel 2, and is used to support and reinforce the second solar wing panel 2.

[0032] By adopting the scheme of the present invention, the adjustment component 5 arranged on the first solar wing panel 1 can be used to conveniently drive the second solar wing panel 2 to rotate, so that the second solar wing panel 2 folded on the first solar wing panel 1 can be stretched out, and when rotating, the corresponding position between the solar panel 4 installed on the second solar wing panel 2 and the first solar wing panel 1 can be adjusted as needed to better receive the irradiation of sunlight and fully absorb solar energy, and the stability of the structure can be improved to avoid shaking of the wings during the stretching process.

[0033] In one embodiment, the adjustment component 5 includes a first driving part 501 fixed on the bottom surface of the first solar wing panel 1, the output end of the first driving part 501 is connected to a rotating shaft 502, the end of the rotating shaft 502 passes through the protective frame 3 and extends to the outside where a first rotating gear 503 is fixed, the surface of the first rotating gear 503 is meshed with a second rotating gear 504, a first connecting shaft 505 is fixed at the axis of the second rotating gear 504, one end of the first connecting shaft 505 is rotatably connected to the first solar wing panel 1 through a bearing, the surface of the first connecting shaft 505 is meshed with a third rotating gear 506, a second connecting shaft 507 is fixed at the axis of the third rotating gear 506, the end of the second connecting shaft 507 is rotatably connected to the first solar wing panel 1 through a bearing, both ends of the second connecting shaft 507 are fixed with connecting members 508, one end of the connecting member 508 is fixed with a fixing block 509, and the ends of the two fixing blocks 509 are fixedly connected to the second solar wing panel 2.

[0034] By adopting such a solution, the deployment angle between the second solar wing panel 2 and the first solar wing panel 1 can be adjusted, and the maximum angle is 180°. A solar panel 4 is arranged on the second solar wing panel 2, and the placement position of the solar panel 4 and the solar panel 4 on the first solar wing panel 1 is adjusted to better receive sunlight, so that it can fully absorb light energy and improve the utilization rate of light energy absorption.

[0035] In one embodiment, a linkage gear 601 is fixed to the surface of the rotating shaft 502, a rack 602 is meshed on the surface of the linkage gear 601, a support plate 606 is fixed to one end of the rack 602, a groove 607 is provided on the surface of the support plate 606, and an anti-sliding block 608 is arranged inside the groove 607.

[0036] By adopting such a scheme, the gear 601 is linked to mesh with the rack 602, thereby driving the rack 602 to move. When the rack 602 moves, it drives the support plate 606 to move, and the support plate 606 is moved to the end of the first solar wing panel 1 away from the first solar wing panel 1, so as to facilitate the support and limiting of the second solar wing panel 2, thereby cooperating with the support assembly 7 to improve the stability of the structure.

[0037] In one embodiment, a clamping block 701 is provided above the support plate 606, a sliding rod 702 is fixed on the top of the clamping block 701, a movable block 703 is connected to the end of the sliding rod 702, the movable block 703 is slidably connected in the support tube 704, a movable groove 706 is provided on the inner wall of the support tube 704, a movable block 705 is slidably connected in the movable groove 706, the movable block 705 is fixedly connected to the movable block 703, an extrusion spring 707 is fixed on the top surface of the movable block 703, the extrusion spring 707 is fixedly connected to the inner wall of the support tube 704, a support rod 708 is fixed on the top of the support tube 704, and a second driving part 709 is connected to the end of the support rod 708.

[0038] By adopting such a scheme, the sliding rod 702 at the end of the movable block 703 is driven to move, so that the locking block 701 at the end of the sliding rod 702 is inserted into the groove 607 for support and limitation, forming a triangular shape with the second solar wing panel 2. The structural characteristics are utilized to support the second solar wing panel 2 to improve its structural stability.

[0039] In one embodiment, a slider 603 is fixed to the top of the rack 602, and support blocks 604 are fixed to both sides of the slider 603. The slider 603 and the support block 604 are slidably connected in a T-shaped slide groove 605, and the T-shaped slide groove 605 is provided on the bottom surface of the first solar wing panel 1. With such a solution, the slider 603 and the support block 604 slide inside the T-shaped slide groove 605, which has a good limiting effect on the rack 602, and the support block 604 has a supporting effect, which improves the stability of the structure. A groove 607 is provided on the surface of the support plate 606, and an anti-sliding block 608 is provided in the groove 607, which has a good protective effect.

[0040] In one embodiment, the first solar wing panel 1 and the second solar wing panel 2 have the same size, and the solar panels 4 are symmetrically distributed on the surfaces of the first solar wing panel 1 and the second solar wing panel 2 .

[0041] In one embodiment, a mounting block 8 is fixed to one side of the second driving part 709, a limiting block 9 is fixed to one side of the mounting block 8, and the limiting block 9 is slidably connected in a limiting groove 10, and the limiting groove 10 is provided on the back of the second solar wing panel 2. With such a solution, when the second solar wing panel 2 is retracted, the second driving part 709 can be activated to drive the support tube 704 to move and retract, so as to prevent the support assembly 7 from exceeding the length range of the second solar wing panel 2, so that the support assembly 7 can be recovered into the satellite with the wings, which is convenient for the recovery and folding of the satellite.

[0042] In one embodiment, a third driving unit 11 is fixed to one end of the mounting block 8 , and the third driving unit 11 is fixedly mounted on a fixing plate 12 , and one end of the fixing plate 12 is fixedly connected to the second solar wing panel 2 .

[0043] In one embodiment, a torsion spring 13 is provided between the first solar wing panel 1 and the second solar wing panel 2, and a fixing member 14 is fixed to the end of the torsion spring 13, and the two fixing members 14 are respectively installed on the surface of the first solar wing panel 1 and the second solar wing panel 2. In one embodiment, a connecting portion 15 is fixed to one end of the first solar wing panel 1, and a mounting shaft 16 is rotatably provided on the surface of the connecting portion 15 through a bearing.

[0044] By adopting such a scheme, during the extension of the second solar wing panel 2, starting the third driving part 11 can drive the mounting block 8 to move, and then drive the supporting assembly 7 to move downward, so that the second solar wing panel 2 can better contact the supporting limit with the supporting assembly 6 when adjusting a larger extension angle, thereby ensuring the normal operation of the mechanism. Through the setting of the torsion spring 13, the connection between the first solar wing panel 1 and the second solar wing panel 2 is reversely supported to keep the second solar wing panel 2 running smoothly.

[0045] The embodiments of the present invention are described in detail below with reference to examples.

[0046] Embodiment 1:

[0047] Reference Figure 1-Figure 8 , a device for automatically locking a satellite after unfolding and retracting, comprising a first solar wing panel 1, a second solar wing panel 2 is arranged on one side of the first solar wing panel 1, a protective frame 3 is installed at the bottom of the first solar wing panel 1, and solar panels 4 are installed on the surfaces of the first solar wing panel 1 and the second solar wing panel 2, and also includes: an adjusting component 5, which is arranged on the bottom surface of the first solar wing panel 1 and is used to adjust the unfolding angle of the second solar wing panel 2; a supporting component 6, which is located in the protective frame 3 and is installed on the bottom surface of the first solar wing panel 1, and is used to limit the support; a supporting component 7, which is arranged on the back of the second solar wing panel 2, and is used to support and reinforce the second solar wing panel 2.

[0048] In the present invention, during use, the first solar wing panel 1 is connected and installed with the satellite body. When the satellite is running in the space orbit, the first solar wing panel 1 is driven to unfold from the inside of the first solar wing panel 1 by the power device on the satellite. When the second solar wing panel 2 connected to the first solar wing panel 1 is extended, the adjustment component 5 provided on the first solar wing panel 1 is used to conveniently drive the second solar wing panel 2 to rotate, and the second solar wing panel 2 folded on the first solar wing panel 1 is extended. During the rotation, the corresponding position between the solar panel 4 installed on the second solar wing panel 2 and the first solar wing panel 1 can be adjusted as needed to better receive the irradiation of sunlight and fully absorb solar energy. When sunlight irradiates the solar panel 4 on the second solar wing panel 2, the sunlight irradiated on the surface of the solar panel 4 is refracted and reflected to The surface of the solar panel 4 installed on the first solar wing panel 1 improves the absorption effect of the solar panel 4 and the working efficiency of the satellite. During use, the support component 6 is driven to operate by the adjustment component 5, and then the support plate 606 on the support component 6 is driven to move out from one end of the first solar wing panel 1, and the position of the second solar wing panel 2 after unfolding is supported and limited, thereby improving the stability of the structure and avoiding shaking of the wings during the extension process. When in use, when the back of the second solar wing panel 2 is provided with a support component 7, when the second solar wing panel 2 is extended and adjusted, it contacts the support plate 606 provided on the support component 6 to support and limit, thereby supporting and protecting the second solar wing panel 2, further improving the stability of the structure, and is suitable for support and limit protection within the angle adjustment range of the device, and is flexible and convenient to use.

[0049] Embodiment 2:

[0050] Reference Figure 1-Figure 8, a device for automatically locking a satellite after unfolding and retracting, comprising a first solar wing panel 1, a second solar wing panel 2 is arranged on one side of the first solar wing panel 1, a protective frame 3 is installed at the bottom of the first solar wing panel 1, and solar panels 4 are installed on the surfaces of the first solar wing panel 1 and the second solar wing panel 2, and also comprising: an adjusting component 5, arranged on the bottom surface of the first solar wing panel 1, for adjusting the unfolding angle of the second solar wing panel 2; a supporting component 6, located in the protective frame 3 and installed on the bottom surface of the first solar wing panel 1, for limiting the supporting position; a supporting component 7, arranged on the back side of the second solar wing panel 2, for supporting and reinforcing the second solar wing panel 2, the adjusting component 5 comprises a first driving part 501 fixed to the bottom surface of the first solar wing panel 1, and the output end of the first driving part 501 is connected to a rotating part A movable shaft 502, the end of the rotating shaft 502 passes through the protective frame 3 and extends to the outside to be fixed with a first rotating gear 503, the surface of the first rotating gear 503 is meshed with a second rotating gear 504, and a first connecting shaft 505 is fixed at the axis of the second rotating gear 504, one end of the first connecting shaft 505 is rotatably connected to the first solar wing panel 1 through a bearing, the surface of the first connecting shaft 505 is meshed with a third rotating gear 506, and a second connecting shaft 507 is fixed at the axis of the third rotating gear 506, and an end of the second connecting shaft 507 is rotatably connected to the first solar wing panel 1 through a bearing, both ends of the second connecting shaft 507 are fixed with connecting pieces 508, one end of the connecting piece 508 is fixed with a fixing block 509, and the ends of the two fixing blocks 509 are fixedly connected to the second solar wing panel 2.

[0051] In the present invention, the first driving part 501 can be replaced by a driving source such as a motor. When in use, the first driving part 501 is started to drive the rotating shaft 502 to rotate counterclockwise, and the rotating shaft 502 drives the first rotating gear 503 to rotate, and the first rotating gear 503 is meshed with the second rotating gear 504, driving the second rotating gear 504 to rotate clockwise, and the second rotating gear 504 is meshed with the third rotating gear 506, thereby driving the third rotating gear 506 to rotate counterclockwise, and the end of the second connecting shaft 507 is connected to the connecting member 508 to drive the connecting member 508 to rotate, and is connected and fixed to the second solar wing panel 2 through the fixing block 509, driving the second solar wing panel 2 to unfold, and adjusting the unfolding angle between the second solar wing panel 2 and the first solar wing panel 1, a solar panel 4 is arranged on the second solar wing panel 2, and the placement position of the solar panel 4 and the solar panel 4 on the first solar wing panel 1 is adjusted to facilitate better reception of sunlight, so that it can fully absorb light energy and improve the utilization rate of light energy absorption, wherein the maximum angle of the second solar wing panel 2 to extend and rotate is 180°.

[0052] Embodiment 3:

[0053] Reference Figure 1-Figure 8, a satellite automatic locking device after unfolding and retracting, comprising a first solar wing panel 1, a second solar wing panel 2 is arranged on one side of the first solar wing panel 1, a protective frame 3 is installed at the bottom of the first solar wing panel 1, and solar panels 4 are installed on the surfaces of the first solar wing panel 1 and the second solar wing panel 2, and also includes: an adjustment component 5, which is arranged on the bottom surface of the first solar wing panel 1, and is used to adjust the unfolding angle of the second solar wing panel 2; a support component 6, which is located in the protective frame 3 and is installed on the bottom surface of the first solar wing panel 1, and is used to limit the support; a support component 7, which is arranged on the back of the second solar wing panel 2, and is used to support and reinforce the second solar wing panel 2, the adjustment component 5 includes a first driving part 501 fixed to the bottom surface of the first solar wing panel 1, the output end of the first driving part 501 is connected to a rotating shaft 502, the end of the rotating shaft 502 passes through the protective frame 3 and extends to the outside to be fixed with a first rotating gear 503, the surface of the first rotating gear 503 is meshed with a second rotating gear 504, and the axis of the second rotating gear 504 is fixed with a first connecting shaft 505, One end of a connecting shaft 505 is rotatably connected to the first solar wing panel 1 through a bearing, a third rotating gear 506 is meshed on the surface of the first connecting shaft 505, a second connecting shaft 507 is fixed at the axis of the third rotating gear 506, an end of the second connecting shaft 507 is rotatably connected to the first solar wing panel 1 through a bearing, both ends of the second connecting shaft 507 are fixed with connecting pieces 508, one end of the connecting piece 508 is fixed with a fixing block 509, the ends of the two fixing blocks 509 are fixedly connected to the second solar wing panel 2, and the rotating shaft 502 A linkage gear 601 is fixed on the surface, a rack 602 is meshed on the surface of the linkage gear 601, a support plate 606 is fixed to one end of the rack 602, a groove 607 is provided on the surface of the support plate 606, an anti-sliding block 608 is provided inside the groove 607, a slider 603 is fixed on the top of the rack 602, support blocks 604 are fixed on both side surfaces of the slider 603, the slider 603 and the support block 604 are slidably connected in a T-shaped slide groove 605, and the T-shaped slide groove 605 is provided on the bottom surface of the first solar wing panel 1.

[0054] In the present invention, when in use, when the rotating shaft 502 rotates, a linkage gear 601 is installed on the surface of the rotating shaft 502, driving the linkage gear 601 to rotate synchronously, and the linkage gear 601 is meshed with the rack 602, thereby driving the rack 602 to move. When the rack 602 moves, it drives the support plate 606 to move, and moves the support plate 606 to the end of the first solar wing panel 1 away from the first solar wing panel 1, so as to facilitate the support and limiting of the second solar wing panel 2, thereby cooperating with the support assembly 7 to improve the stability of the structure, wherein the slider 603 and the support block 604 slide inside the T-shaped slide groove 605, which has a good limiting effect on the rack 602, and the support block 604 has a supporting effect, thereby improving the operational stability of the structure, and a groove 607 is provided on the surface of the support plate 606, and an anti-sliding block 608 arranged in the groove 607 has a good protective effect.

[0055] Embodiment 4:

[0056] A device for automatically locking a satellite after unfolding and retracting, comprising a first solar wing panel 1, a second solar wing panel 2 is arranged on one side of the first solar wing panel 1, a protective frame 3 is installed at the bottom of the first solar wing panel 1, and solar panels 4 are installed on the surfaces of the first solar wing panel 1 and the second solar wing panel 2, and also comprising: an adjustment component 5, arranged on the bottom surface of the first solar wing panel 1, for adjusting the unfolding angle of the second solar wing panel 2; a support component 6, located in the protective frame 3 and installed on the bottom surface of the first solar wing panel 1, for limiting the support; a support component 7, arranged on the back of the second solar wing panel 2, for supporting and reinforcing the second solar wing panel 2, the adjustment component 5 includes a fixed component 5 on the first solar wing panel 1, the output end of the first driving part 501 is connected with a rotating shaft 502, the end of the rotating shaft 502 passes through the protective frame 3 and extends to the outside to be fixed with a first rotating gear 503, the surface of the first rotating gear 503 is meshed with a second rotating gear 504, the axis of the second rotating gear 504 is fixed with a first connecting shaft 505, one end of the first connecting shaft 505 is rotatably connected to the first solar wing panel 1 through a bearing, the surface of the first connecting shaft 505 is meshed with a third rotating gear 506, the axis of the third rotating gear 506 is fixed with a second connecting shaft 507, the end of the second connecting shaft 507 is rotatably connected to the first solar wing panel 1 through a bearing, and the second Connecting members 508 are fixed at both ends of the connecting shaft 507, a fixing block 509 is fixed at one end of the connecting member 508, the ends of the two fixing blocks 509 are fixedly connected to the second solar wing panel 2, a linkage gear 601 is fixed on the surface of the rotating shaft 502, a rack 602 is meshed on the surface of the linkage gear 601, a support plate 606 is fixed at one end of the rack 602, a groove 607 is provided on the surface of the support plate 606, an anti-sliding block 608 is provided inside the groove 607, a tightening block 701 is provided above the support plate 606, a sliding rod 702 is fixed on the top of the tightening block 701, a movable block 703 is connected to the end of the sliding rod 702, and the movable block 703 is slidably connected to the support cylinder 704 Inside, a movable groove 706 is opened on the inner wall of the support cylinder 704, and a movable block 705 is slidably connected in the movable groove 706. The movable block 705 is fixedly connected to the movable block 703, and an extrusion spring 707 is fixed on the top surface of the movable block 703. The extrusion spring 707 is fixedly connected to the inner wall of the support cylinder 704, and a support rod 708 is fixed on the top of the support cylinder 704. The end of the support rod 708 is connected to the second driving part 709, and a slider 603 is fixed on the top of the rack 602. Support blocks 604 are fixed on both side surfaces of the slider 603. The slider 603 and the support block 604 are slidably connected in the T-shaped slide groove 605, and the T-shaped slide groove 605 is opened on the bottom surface of the first solar wing panel 1.

[0057] In the present invention, when in use, when the adjustment component 5 is in operation, the support plate 606 on the support component 6 is driven to move out from one end of the first solar wing panel 1. When the second solar wing panel 2 is extended and adjusted, the extrusion spring 707 inside the support cylinder 704 squeezes the movable block 703, driving the slide bar 702 at the end of the movable block 703 to move, so that the abutting block 701 at the end of the slide bar 702 is inserted into the groove 607 to support and limit, forming a triangular shape with the second solar wing panel 2. The characteristics of the structure are used to support the second solar wing panel 2 to improve its structural stability. When the second solar wing panel 2 is retracted, the second driving unit 709 can be activated to drive the support tube 704 to move and retract, so as to prevent the support assembly 7 from exceeding the length range of the second solar wing panel 2, and then it can be recovered into the satellite with the wings spread, so as to facilitate the recovery and folding of the satellite. When the second solar wing panel 2 is extended and adjusted to different unfolding angles, the support assembly 7 can always be in contact with the supporting assembly 6 to form a supporting protection, thereby further improving the stability of the structure. During the movement of the movable block 703, the movable block 705 slides inside the movable groove 706, which acts as a moving limit for the movable block 703.

[0058] Embodiment 5:

[0059] Reference Figure 1-Figure 8 , a satellite automatic locking device after unfolding and retracting, comprising a first solar wing panel 1, a second solar wing panel 2 is arranged on one side of the first solar wing panel 1, a protective frame 3 is installed at the bottom of the first solar wing panel 1, and solar panels 4 are installed on the surfaces of the first solar wing panel 1 and the second solar wing panel 2, and also includes: an adjustment component 5, which is arranged on the bottom surface of the first solar wing panel 1 and is used to adjust the unfolding angle of the second solar wing panel 2; a support component 6, which is located in the protective frame 3 and is installed on the bottom surface of the first solar wing panel 1 and is used to limit the support; a support component 7, which is arranged on the back of the second solar wing panel 2 and is used to support and reinforce the second solar wing panel 2, the first solar wing panel 1 and the second solar wing panel 2 are of the same size, and the solar panels 4 are symmetrically distributed and arranged on the first solar wing panel 1 and On the surface of the second solar wing panel 2, a mounting block 8 is fixed to one side of the second driving part 709, and a limiting block 9 is fixed to one side of the mounting block 8. The limiting block 9 is slidably connected in the limiting groove 10, and the limiting groove 10 is arranged on the back of the second solar wing panel 2. A third driving part 11 is fixed to one end of the mounting block 8, and the third driving part 11 is fixedly installed on a fixing plate 12. One end of the fixing plate 12 is fixedly connected to the second solar wing panel 2. A torsion spring 13 is arranged between the first solar wing panel 1 and the second solar wing panel 2, and a fixing piece 14 is fixed to the end of the torsion spring 13. The two fixing pieces 14 are respectively installed on the surfaces of the first solar wing panel 1 and the second solar wing panel 2. A connecting part 15 is fixed to one end of the first solar wing panel 1, and a mounting shaft 16 is rotated on the surface of the connecting part 15 through a bearing.

[0060] In the present invention, during the extension of the second solar wing panel 2, starting the third driving unit 11 can drive the mounting block 8 to move, and then drive the supporting assembly 7 to move downward, so that the second solar wing panel 2 can better contact the supporting assembly 6 to support and limit when adjusting a larger extension angle, thereby ensuring the normal operation of the mechanism. Through the setting of the torsion spring 13, the connection between the first solar wing panel 1 and the second solar wing panel 2 is reversely supported to keep the second solar wing panel 2 running smoothly, wherein the mounting shaft 16 can be connected and installed with the storage cavity in the satellite, so as to facilitate the first solar wing panel 1 and the second solar wing panel 2 to be retracted into the satellite body, wherein the second driving unit 709 and the third driving unit 11 can be driven by electric push rods instead.

[0061] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A satellite automatic locking device after unfolding and retracting, comprising a first solar wing panel (1), a second solar wing panel (2) being arranged on one side of the first solar wing panel (1), a protective frame (3) being installed at the bottom of the first solar wing panel (1), and solar panels (4) being installed on the surfaces of the first solar wing panel (1) and the second solar wing panel (2), characterized in that: Also includes: An adjustment component (5) is arranged on the bottom surface of the first solar wing panel (1) and is used to adjust the deployment angle of the second solar wing panel (2); A support assembly (6), located in the protection frame (3) and mounted on the bottom surface of the first solar wing panel (1), and used for limiting the position of the support; A support assembly (7) is arranged on the back side of the second solar wing panel (2) and is used to contact a support plate (606) arranged at one end of the support assembly (6) to support and limit the second solar wing panel (2) when the second solar wing panel (2) is extended and adjusted; The support assembly (7) comprises a clamping block (701) which is arranged above the support plate (606); a sliding rod (702) is fixed on the top of the clamping block (701); a movable block (703) is connected to the end of the sliding rod (702); the movable block (703) is slidably connected in the support tube (704); a movable groove (706) is provided on the inner wall of the support tube (704); a movable block (705) is slidably connected in the movable groove (706); the movable block (705) is fixedly connected to the movable block (703); a pressing spring (707) is fixedly connected to the top surface of the movable block (703); the pressing spring (707) is fixedly connected to the inner wall of the support tube (704); a support rod (708) is fixed on the top of the support tube (704); and a second driving unit (709) is connected to the end of the support rod (708).

2. The satellite automatic locking device after expansion and contraction according to claim 1, characterized in that: The adjustment component (5) comprises a first driving part (501) fixed to the bottom surface of the first solar wing panel (1); the output end of the first driving part (501) is connected to a rotating shaft (502); the end of the rotating shaft (502) passes through the protective frame (3) and extends to the outside to be fixed with a first rotating gear (503); the surface of the first rotating gear (503) is meshed with a second rotating gear (504); a first connecting shaft (505) is fixed at the axis of the second rotating gear (504); one end of the first connecting shaft (505) is connected to the protective frame (3) through a bearing. The first solar wing panel (1) is rotatably connected, the surface of the first connecting shaft (505) is meshed with a third rotating gear (506), a second connecting shaft (507) is fixed at the axis of the third rotating gear (506), the end of the second connecting shaft (507) is rotatably connected to the first solar wing panel (1) through a bearing, both ends of the second connecting shaft (507) are fixed with connecting pieces (508), one end of the connecting piece (508) is fixed with a fixing block (509), and the ends of the two fixing blocks (509) are fixedly connected to the second solar wing panel (2).

3. The satellite automatic locking device after expansion and contraction according to claim 2, characterized in that: A linkage gear (601) is fixed on the surface of the rotating shaft (502), a rack (602) is meshed on the surface of the linkage gear (601), a support plate (606) is fixed to one end of the rack (602), a groove (607) is provided on the surface of the support plate (606), and an anti-sliding block (608) is provided inside the groove (607).

4. The satellite automatic locking device after expansion and contraction according to claim 3, characterized in that: A slider (603) is fixed to the top of the rack (602), support blocks (604) are fixed to both side surfaces of the slider (603), the slider (603) and the support blocks (604) are slidably connected in a T-shaped slide groove (605), and the T-shaped slide groove (605) is provided on the bottom surface of the first solar wing panel (1).

5. The satellite automatic locking device after expansion and contraction according to claim 1, characterized in that: The first solar wing panel (1) and the second solar wing panel (2) have the same size, and the solar panels (4) are symmetrically distributed on the surfaces of the first solar wing panel (1) and the second solar wing panel (2).

6. The satellite automatic locking device after expansion and contraction according to claim 1, characterized in that: A mounting block (8) is fixed to one side of the second driving part (709), a limiting block (9) is fixed to one side of the mounting block (8), the limiting block (9) is slidably connected in a limiting groove (10), and the limiting groove (10) is provided on the back side of the second solar wing panel (2).

7. The satellite automatic locking device after expansion and contraction according to claim 6, characterized in that: A third driving part (11) is fixed to one end of the mounting block (8), and the third driving part (11) is fixedly mounted on a fixing plate (12), and one end of the fixing plate (12) is fixedly connected to the second solar wing panel (2).

8. The satellite automatic locking device after expansion and contraction according to claim 1, characterized in that: A torsion spring (13) is provided between the first solar wing panel (1) and the second solar wing panel (2), a fixing member (14) is fixed to the end of the torsion spring (13), and the two fixing members (14) are respectively mounted on the surface of the first solar wing panel (1) and the second solar wing panel (2).

9. The satellite automatic locking device after expansion and contraction according to claim 1, characterized in that: A connecting portion (15) is fixed to one end of the first solar wing panel (1), and a mounting shaft (16) is rotatably arranged on the surface of the connecting portion (15) via a bearing.

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