Satellite solar wing deployment mechanism

Abstract

The application discloses a satellite solar wing unfolding mechanism and belongs to the field of satellite solar wings. The satellite solar wing unfolding mechanism comprises a satellite main body, rotating solar wing main bodies arranged on the two sides of the satellite main body, unfolding assemblies arranged on the two sides of the satellite main body and used for driving the solar wing main bodies to unfold, and driving members arranged at the satellite main body and used for driving the unfolding assemblies to move. The unfolding of the solar wing main bodies facilitates the use of the solar wing main bodies. After the solar wing main bodies are unfolded, the inclination angle of the solar wing main bodies can be adjusted according to the irradiation of solar energy, the irradiation effect is ensured, the surface of the solar wing main bodies can be cleaned when the angle of the solar wing main bodies is adjusted, the absorption effect of solar energy is effectively improved, and the utilization efficiency of solar energy can be better ensured when the solar wing main bodies are used.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of satellite solar wing, and in particular to a satellite solar wing unfolding mechanism. BACKGROUND

[0002] The satellite solar wing, also known as a solar cell wing or a solar panel wing, is a device used in space to collect solar energy. It is usually composed of multiple solar panels that can convert solar energy into electrical energy for the satellite. The main function of the satellite solar wing is to provide power for the satellite, and also can power other systems of the satellite, such as communication, navigation and scientific instruments, etc. The solar wing will usually be unfolded after the satellite is launched into space to maximize the reception of solar radiation. When using the solar wing, it needs to be stowed before the satellite is launched and unfolded after the launch. An unfolding mechanism is needed during unfolding and stowing. However, the existing unfolding mechanism can only unfold the solar wing. When the solar wing absorbs solar energy, it is easy to be blocked by other satellites or deviate from the angle when the satellite moves, which affects the illumination effect of the sunlight. This causes the solar wing to be unable to fully absorb and convert solar energy in some cases, affecting the utilization rate of solar energy. The efficiency of the solar wing is closely related to the cleanliness of its surface. In the space environment, the satellite may accumulate dust, particles or other impurities, which may affect the collection efficiency of solar energy. SUMMARY

[0003] The purpose of the present application is to solve the problem that the dust cannot be cleaned in time and the position of the solar wing cannot be adjusted according to the position of the sun in the prior art, thereby affecting the absorption efficiency of the solar wing. A satellite solar wing unfolding mechanism is provided.

[0004] In order to achieve the above-mentioned purpose, the application adopts the following technical scheme:

[0005] A satellite solar wing unfolding mechanism, a support seat rotatable with the solar wing main body is arranged at the end face of the solar wing main body, a rotating motor driving the support seat to rotate is arranged at the side of the satellite main body, the unfolding assembly comprises a movable fixing seat arranged at the satellite main body, a support rod rotatably arranged at the side of the fixing seat, a connecting seat rotatably arranged at the end of the support rod, a rotating seat fixedly connected to the top of the connecting seat, a rotating strip rotatably arranged at the top of the rotating seat, the top of the rotating strip is fixed to the solar wing main body, and a photosensitive sensor is arranged at the satellite main body.

[0006] Preferably, a placing groove is arranged at the satellite main body, the fixing seat is arranged in the placing groove, a driving member is arranged at the satellite main body, and the driving member is used to drive the fixing seat to move up and down.

[0007] Preferably, the satellite body has a first built-in slot on the inner wall of the placement slot, the driving component is disposed in the first built-in slot, the driving component includes a servo motor installed in the first built-in slot, the end of the servo motor is equipped with a threaded rod, the surface of the threaded rod is threadedly connected to a threaded seat, and the threaded seat is connected to a fixed seat.

[0008] Preferably, a cleaning component is provided on top of the solar panel body of the satellite body, and a scraper is provided at the bottom of the cleaning component, the scraper being used to scrape away dust from the top of the solar panel body.

[0009] Preferably, the cleaning assembly includes a mounting base connected to the satellite body, a return spring installed on the inner wall of the mounting base, a moving block installed at the end of the return spring, a compression spring installed at the bottom of the moving block, and the end of the compression spring connected to a scraper.

[0010] Preferably, a guide rod is installed on the inner wall of the mounting base, the moving block is sleeved on the guide rod, and a telescopic rod is provided inside the compression spring. The ends of the telescopic rod are respectively connected to the moving block and the scraper.

[0011] Preferably, the satellite body has a mounting groove on its side for mounting a rotating motor.

[0012] Preferably, a connecting piece is installed on the surface of the solar panel body, and a limiting piece is installed on the side of the connecting piece, the limiting piece being connected through the scraper.

[0013] Preferably, the ends of the support rod are respectively connected to a first rotating rod and a second rotating rod, the first rotating rod being rotatably connected to the connecting seat, and the second rotating rod being rotatably connected to the fixed seat.

[0014] Preferably, the satellite body has a second built-in slot on the inner wall of the placement slot, and a limiting member is provided on the inner wall of the second built-in slot. The limiting member includes a slide rod installed on the inner wall of the second built-in slot, and a slider is slidably connected to the surface of the slide rod. The slider is connected to the fixed seat.

[0015] Compared with the prior art, the present invention provides a satellite solar array deployment mechanism, which has the following advantages:

[0016] 1. The satellite's solar array deployment mechanism uses a deployment component to drive the solar array body to deploy. During deployment, a photosensitive sensor detects the intensity of solar radiation, which triggers a rotating motor. With the cooperation of the support base, the solar array body rotates, allowing the tilt angle of the solar array to be adjusted according to the position of the sun, thereby ensuring the utilization efficiency of the solar array.

[0017] 2、The satellite solar wing unfolding mechanism, through the setting of the cleaning assembly and the scraper, can effectively clean every time the solar wing body adjusts the angle, thereby ensuring that the surface of the solar wing body will not be affected by the adhesion of dust when using the solar wing body, thereby effectively improving the utilization efficiency of the solar wing.

[0018] The parts not involved in the device are the same as or can be realized by the prior art. When the device is used, the solar wing body is unfolded, which facilitates the use of the solar wing body. After the solar wing body is unfolded, the inclination angle of the solar wing body can be adjusted according to the irradiation of solar energy, which ensures the irradiation effect. The surface of the solar wing body can be cleaned when the angle of the solar wing body is adjusted, which effectively improves the absorption effect of solar energy, thereby better ensuring the utilization efficiency of solar energy when the solar wing body is used. BRIEF DESCRIPTION OF DRAWINGS

[0019] Figure 1 A structural schematic view of a satellite solar wing unfolding mechanism is provided for the present application.

[0020] Figure 2 A structural side view of a satellite solar wing unfolding mechanism is provided for the present application.

[0021] Figure 3 A structural top view of a satellite solar wing unfolding mechanism is provided for the present application.

[0022] Figure 4 A structural back view of a satellite solar wing unfolding mechanism is provided for the present application.

[0023] Figure 5 A structural schematic view of a satellite solar wing unfolding mechanism driving member is provided for the present application.

[0024] Figure 6 A structural schematic view of a satellite solar wing unfolding mechanism cleaning assembly is provided for the present application.

[0025] Figure 7 A solar wing body and scraper connection schematic view of a satellite solar wing unfolding mechanism is provided for the present application.

[0026] Figure 8 A solar wing body and connecting seat connection schematic view of a satellite solar wing unfolding mechanism is provided for the present application.

[0027] In the drawings:

[0028] 1, satellite body; 11, mounting groove; 12, placing groove; 13, first built-in groove; 14, second built-in groove; 15, photosensitive sensor;

[0029] 2, solar wing body; 21, connecting piece; 22, limiting piece;

[0030] 3, unfolding assembly; 31, fixing seat; 32, supporting rod; 33, connecting seat; 34, rotating seat; 35, rotating strip; 36, first rotating rod; 37, second rotating rod;

[0031] 4, driving piece; 41, servo motor; 42, threaded rod; 43, threaded seat;

[0032] 5, rotating motor;

[0033] 6, cleaning assembly; 61, mounting seat; 62, guide rod; 63, reset spring; 64, moving block; 65, extrusion spring; 66, telescopic rod;

[0034] 7, scraper;

[0035] 8, supporting seat;

[0036] 9, limiting piece; 91, sliding rod; 92, sliding block. DETAILED DESCRIPTION

[0037] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, not all the embodiments of the present application.

[0038] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inner", "outer" and the like 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 the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, therefore it cannot be understood as a limitation of the present application.

[0039] Reference Figures 1-8The utility model provides a satellite solar wing unfolding mechanism, including satellite main body 1, the both sides of satellite main body 1 are provided with the solar wing main body 2 of rotation, the both sides of satellite main body 1 are provided with the unfolding assembly 3 of driving solar wing main body 2 to unfold, the drive piece 4 of driving unfolding assembly 3 is arranged at satellite main body 1, the end surface of solar wing main body 2 is provided with the support seat 8 that can rotate with it, the side of satellite main body 1 is provided with the rotation motor 5 of driving support seat 8 to rotate, and unfolding assembly 3 includes the fixed seat 31 of being provided at satellite main body 1 and movable, the side of fixed seat 31 is rotatably provided with support rod 32, the end of support rod 32 is rotatably provided with connecting seat 33, the top of connecting seat 33 is fixedly connected with rotating seat 34, the top of rotating seat 34 is rotatably provided with rotating strip 35, and the top of rotating strip 35 is fixed with solar wing main body 2, and photosensitive sensor 15 is arranged at satellite main body 1.

[0040] In the application, when in use, the fixed seat 31 is moved to push the support rod 32, then the support rod 32 pushes the connecting seat 33, so as to unfold the solar wing main body 2, then the rotation motor 5 is started to drive the support seat 8 to rotate, so as to drive the solar wing main body 2 to rotate, wherein the support seat 8 and the solar wing main body 2 are rotatably connected, so as to facilitate the unfolding and storage of the solar wing main body 2, the photosensitive sensor 15 is arranged to sense the position of the sun when the satellite is in use, the position of the solar wing main body 2 is adjusted according to the intensity of the sun's radiation, when the rotation motor 5 drives the solar wing main body 2 to rotate, the rotating strip 35 and the rotating seat 34 are rotatably connected, so as to effectively support the solar wing main body 2 when it rotates.

[0041] In one embodiment, the satellite main body 1 is provided with a placing groove 12, the fixed seat 31 is arranged in the placing groove 12, the satellite main body 1 is provided with the drive piece 4, the drive piece 4 is used for driving the fixed seat 31 to move up and down, the satellite main body 1 is provided with a first built-in groove 13 at the inner wall of the placing groove 12, the drive piece 4 is arranged in the first built-in groove 13, the drive piece 4 includes a servo motor 41 arranged in the first built-in groove 13, a threaded rod 42 is arranged at the end of the servo motor 41, a threaded seat 43 is threadedly connected to the surface of the threaded rod 42, and the threaded seat 43 is connected with the fixed seat 31.

[0042] In the application, when the fixed seat 31 is moved, the fixed seat 31 is conveniently arranged through the placed groove 12, and then the fixed seat 31 is moved through the driving of the driving part 4, so that the support rod 32 is pushed, and then the solar wing main body 2 is pushed under the cooperation of the connecting seat 33. When the driving part 4 is used, the threaded rod 42 is rotated through the starting of the servo motor 41, so that the threaded seat 43 is effectively displaced, and then the fixed seat 31 is displaced under the cooperation of the threaded seat 43 and the fixed seat 31.

[0043] In one embodiment, the satellite main body 1 is provided with the cleaning assembly 6 at the top of the solar wing main body 2, the bottom of the cleaning assembly 6 is provided with the scraper 7, the scraper 7 is used for scraping off the dust at the top of the solar wing main body 2, the cleaning assembly 6 comprises the mounting seat 61 connected with the satellite main body 1, the inner wall of the mounting seat 61 is provided with the reset spring 63, the end of the reset spring 63 is provided with the moving block 64, the bottom of the moving block 64 is provided with the extrusion spring 65, the end of the extrusion spring 65 is connected with the scraper 7, the inner wall of the mounting seat 61 is provided with the guide rod 62, the moving block 64 is sleeved on the guide rod 62, the extrusion spring 65 is provided with the telescopic telescopic rod 66, and the ends of the telescopic telescopic rod 66 are connected with the moving block 64 and the scraper 7 respectively.

[0044] In the application, when the cleaning assembly 6 is used, when the solar wing main body 2 is rotated under the driving of the rotating motor 5, when the rotating motor 5 rotates to one side, the moving block 64 drives the scraper 7 to move to the center position of the rotating motor 5 through the extrusion of the extrusion spring 65, so that the dust on the surface of the rotating motor 5 is scraped off, when the rotating motor 5 rotates to the other direction, the other scraper 7 is used for cleaning, when the rotating motor 5 is turned to the initial position, the reset spring 63 is used for resetting through the rebound force, so that the moving block 64 drives the scraper 7 to return to the initial position, so as to facilitate the next cleaning, when the extrusion spring 65 is in the initial position of the elastic force when the rotating motor 5 is in the horizontal position, when the rotating motor 5 is turned, the elastic force of the extrusion spring 65 is increased through the extrusion, so that the scraper 7 is pushed, the telescopic rod 66 is used for limiting, so that the extrusion spring 65 moves in the vertical direction, the guide rod 62 is used for guiding, so that the moving block 64 can be at the same horizontal height when sliding, and the mounting seat 61 is used for supporting.

[0045] In one embodiment, the side of the satellite body 1 is provided with a mounting groove 11 for mounting the rotating motor 5, the surface of the solar wing body 2 is provided with a connecting piece 21, the side of the connecting piece 21 is provided with a limiting piece 22, the limiting piece 22 is connected with the scraper 7, the inner wall of the satellite body 1 at the placing groove 12 is provided with a second built-in groove 14, and the inner wall of the second built-in groove 14 is provided with a limiting piece 9.

[0046] In the application, when in use, the rotating motor 5 is conveniently mounted through the mounting groove 11, the limiting piece 22 is provided to limit the movement of the scraper 7, the connecting piece 21 is provided to conveniently mount the limiting piece 22, the second built-in groove 14 is provided to conveniently set the driving piece 4, the threaded rod 42 is driven to rotate through the starting of the servo motor 41, so that the position of the threaded seat 43 is changed, and the fixed seat 31 is driven to move, so as to push the supporting rod 32. The servo motor 41, the threaded rod 42 and the threaded seat 43 are only one embodiment of the driving piece 4, and other driving pieces such as hydraulic rods and rodless lead screws can also drive the fixed seat 31 to move. The limiting piece 9 is provided to limit the movement of the fixed seat 31, so that the fixed seat 31 moves in the vertical direction. When the limiting piece 9 is used, the sliding block 92 is provided to slide on the surface of the sliding rod 91, so as to limit the movement. The limiting piece 9 includes but is not limited to the two structures of the sliding rod 91 and the sliding block 92, and the second built-in groove 14 is provided to conveniently set the limiting piece 9.

[0047] In one embodiment, the ends of the supporting rod 32 are respectively connected with a first rotating rod 36 and a second rotating rod 37, the first rotating rod 36 is rotationally connected with the connecting seat 33, and the second rotating rod 37 is rotationally connected with the fixed seat 31.

[0048] In the application, when in use, the first rotating rod 36 and the second rotating rod 37 are provided to connect the fixed seat 31, so that the connecting seat 33 is effectively driven to move when the fixed seat 31 is pushed upward, and the solar wing body 2 is unfolded.

[0049] The above is only a preferred embodiment of the application, and the protection scope of the application is not limited to this. Any person skilled in the art can make equivalent replacements or changes according to the technical scheme and the inventive concept of the application within the technical range disclosed by the application, which should be covered by the protection scope of the application.

Claims

1. A satellite solar array deployment mechanism, comprising a satellite body (1), characterized in that, The satellite body (1) has rotating solar array bodies (2) on both sides. Deployment components (3) for deploying the solar array bodies (2) are located on both sides of the satellite body (1). A drive unit (4) for moving the deployment components (3) is located on the satellite body (1). A rotatable support base (8) is located at the end face of the solar array body (2). A rotating motor (5) for rotating the support base (8) is located on the side of the satellite body (1). The deployment components (3)... The satellite includes a movable fixed base (31) located on the main body (1). A support rod (32) is rotatably provided on the side of the fixed base (31). A connecting seat (33) is rotatably provided at the end of the support rod (32). A rotating seat (34) is fixedly connected to the top of the connecting seat (33). A rotating bar (35) is rotatably provided on the top of the rotating seat (34). The top of the rotating bar (35) is fixed to the main body (2) of the solar array. A photosensitive sensor (15) is provided on the main body (1).

2. The satellite solar array deployment mechanism according to claim 1, characterized in that, The satellite body (1) has a placement slot (12) and the fixing seat (31) is placed in the placement slot (12). The satellite body (1) is provided with a driving component (4) and the driving component (4) is used to drive the fixing seat (31) to move up and down.

3. A satellite solar array deployment mechanism according to claim 1, characterized in that, The satellite body (1) has a first built-in slot (13) on the inner wall of the placement slot (12). The driving component (4) is located in the first built-in slot (13). The driving component (4) includes a servo motor (41) installed in the first built-in slot (13). A threaded rod (42) is installed at the end of the servo motor (41). A threaded seat (43) is threadedly connected to the surface of the threaded rod (42). The threaded seat (43) is connected to the fixed seat (31).

4. A satellite solar array deployment mechanism according to claim 1, characterized in that, The satellite body (1) is provided with a cleaning component (6) on top of the solar panel body (2), and a scraper (7) is provided at the bottom of the cleaning component (6). The scraper (7) is used to scrape off the dust on the top of the solar panel body (2).

5. A satellite solar array deployment mechanism according to claim 4, characterized in that, The cleaning assembly (6) includes a mounting base (61) connected to the satellite body (1). A return spring (63) is installed on the inner wall of the mounting base (61). A moving block (64) is installed at the end of the return spring (63). A compression spring (65) is installed at the bottom of the moving block (64). The end of the compression spring (65) is connected to the scraper (7).

6. A satellite solar array deployment mechanism according to claim 5, characterized in that, A guide rod (62) is installed on the inner wall of the mounting base (61), and the moving block (64) is sleeved on the guide rod (62). A telescopic rod (66) is provided inside the compression spring (65), and the ends of the telescopic rod (66) are connected to the moving block (64) and the scraper (7) respectively.

7. A satellite solar array deployment mechanism according to claim 1, characterized in that, The satellite body (1) has a mounting groove (11) on its side, which is used to install the rotating motor (5).

8. A satellite solar array deployment mechanism according to claim 1, characterized in that, A connecting piece (21) is installed on the surface of the solar panel body (2), and a limiting piece (22) is installed on the side of the connecting piece (21). The limiting piece (22) is connected to the scraper (7) through.

9. A satellite solar array deployment mechanism according to claim 1, characterized in that, The support rod (32) is connected to a first rotating rod (36) and a second rotating rod (37) at its ends. The first rotating rod (36) is rotatably connected to the connecting seat (33), and the second rotating rod (37) is rotatably connected to the fixed seat (31).

10. A satellite solar array deployment mechanism according to claim 1, characterized in that, The satellite body (1) has a second built-in groove (14) on the inner wall of the placement groove (12). The inner wall of the second built-in groove (14) is provided with a limiting member (9). The limiting member (9) includes a slide rod (91) installed on the inner wall of the second built-in groove (14). A slider (92) is slidably connected to the surface of the slide rod (91). The slider (92) is connected to the fixed seat (31).

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