Angle-adjustable aerospace craft solar panel support

Abstract

The invention relates to the technical field of supports, in particular to an angle-adjustable aerospace craft solar panel support which comprises a sleeve detachably connected with an aircraft. The supporting assembly is movably arranged in the sleeve and comprises a main shaft and a plurality of solar panels which are arranged on the outer wall of the main shaft in a circumferential array mode; according to the angle-adjustable solar panel support for the aerospace craft, the problem that in the prior art, when a solar panel is not used, wind resistance is large is solved, when the solar panel is not used, the solar panel can be moved into the sleeve to be stored, and the solar panel can be conveniently moved to be stored. Therefore, air resistance during high-speed flight is effectively reduced, flight maneuverability and attitude control precision can be improved, the problem of structural fatigue of a support used for supporting the solar panel due to too large wind resistance is avoided, the service life of key components is prolonged, and the problems existing in the prior art are solved.

Description

Technical Field

[0001] The present invention relates to the technical field of brackets, and particularly to a solar panel bracket for a spacecraft with adjustable angle. Background Art

[0002] In the space field, energy supply is one of the key links to ensure the normal operation of the spacecraft. As a clean and renewable energy source, solar energy is widely used in spacecraft to provide power support for various electronic devices, propulsion systems, etc. carried by it. As the core component for converting solar energy into electrical energy, the working efficiency of the solar panel directly affects the stability of the energy supply and the endurance of the spacecraft. And as an important structure for supporting the solar panel, the solar panel bracket not only needs to ensure that the solar panel receives sunlight at an appropriate angle to maximize the energy conversion efficiency, but also needs to play a stable supporting role at different flight stages of the spacecraft.

[0003] Currently, most of the existing solar panel brackets for spacecraft have a certain angle adjustment function and can adjust the orientation of the solar panel according to the change of the sun's position to ensure better power generation effect. However, these brackets often mainly focus on the angle adjustment and stable support during the use of the solar panel, and insufficient consideration is given to the situation where the solar panel is not used during the flight of the spacecraft. When the spacecraft is in a specific flight stage, such as the initial stage of launch, high-speed flight, or performing tasks that do not require a large amount of electrical energy, the solar panel may not need to work. At this time, if the solar panel and its bracket still remain in a fully deployed state, a series of problems will arise.

[0004] On the one hand, the fully deployed solar panel will form a large windward area during the flight of the spacecraft, generating a large wind resistance. When the spacecraft flies in the atmosphere, the high-speed airflow will exert a large aerodynamic force on the solar panel and the bracket, which will not only increase the energy consumption of the spacecraft, affect its flight speed and maneuverability, but also may generate additional stress on the bracket structure. In the long term, this may lead to fatigue of the bracket structure and even pose safety hazards such as structural damage. On the other hand, due to the lack of effective storage or fixing mechanisms in the existing brackets, the solar panel may shake or vibrate in high-speed flight or complex airflow environments, which will not only affect the stability of the bracket itself, but also may cause damage to the solar panel, reducing its service life and reliability. Summary of the Invention

[0005] In view of the problems existing in the prior art, the present invention is proposed.

[0006] To solve the above technical problems, the present invention provides the following technical solution: An adjustable-angle solar panel bracket for a spacecraft, comprising a sleeve detachably connected to the spacecraft; and a support assembly movably disposed within the sleeve, including a main shaft and a plurality of solar panels circumferentially arrayed on the outer wall of the main shaft; and a traveling assembly disposed outside the main shaft for supporting the displacement of the support assembly.

[0007] As a preferred embodiment of the adjustable-angle solar panel bracket for a spacecraft of the present invention, wherein: A fixing plate is further installed on the outer wall of the main shaft by bolts, a first fixing block is provided on the fixing plate, and an adjusting member is hinged to the outer wall of the first fixing block.

[0008] As a preferred embodiment of the adjustable-angle solar panel bracket for a spacecraft of the present invention, wherein: The adjusting member includes a first rotating cylinder hinged to the first fixing block, a first pull rod is slidably disposed inside the first rotating cylinder, and a first elastic member is sleeved on the outer wall of the first pull rod.

[0009] As a preferred embodiment of the adjustable-angle solar panel bracket for a spacecraft of the present invention, wherein: A second fixing block is welded to the end of the first pull rod away from the first pull rod, and the inner ratio of the second fixing block is slidably connected to the fixing plate.

[0010] As a preferred embodiment of the adjustable-angle solar panel bracket for a spacecraft of the present invention, wherein: A transmission member is hinged to the outer wall of the second fixing block, and the transmission member includes a second rotating cylinder.

[0011] As a preferred embodiment of the adjustable-angle solar panel bracket for a spacecraft of the present invention, wherein: A second pull rod is movably disposed inside the second rotating cylinder, a second elastic member is sleeved on the outer wall of the second pull rod, and one end of the second pull rod is connected to a support rod.

[0012] As a preferred embodiment of the adjustable-angle solar panel bracket for a spacecraft of the present invention, wherein: The traveling assembly includes a housing, and the end of the support rod away from the second pull rod is hinged to the housing.

[0013] As a preferred embodiment of the adjustable-angle solar panel bracket for a spacecraft of the present invention, wherein: A connecting rotating rod is rotatably connected to the outer wall of the fixing plate, and one end of the connecting rotating rod is connected to the outer wall of the housing.

[0014] As a preferred embodiment of the adjustable-angle solar panel bracket for a spacecraft of the present invention, wherein: The traveling assembly further includes an output motor, and the output shaft of the output motor extends into the housing and is sleeved with an output gear.

[0015] As a preferred embodiment of the adjustable-angle solar panel support for a spacecraft in the present invention, the following is provided: A crawler is sleeved on the outer wall of the housing, and drive teeth meshing with the output gear are integrally formed on the inner wall of the crawler. A support wheel body for supporting the crawler is further provided inside the housing.

[0016] Advantages of the present invention: The adjustable-angle solar panel support for a spacecraft provided by the present invention addresses the problem of high wind resistance when the solar panel is not in use in the prior art. When the solar panel is not in use, it can be moved into the sleeve for storage, thereby effectively reducing the air resistance during high-speed flight. At the same time, it can also improve flight maneuverability and attitude control accuracy, avoid structural fatigue problems of the support for the solar panel caused by excessive wind resistance, extend the service life of key components, and solve the problems existing in the prior art. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings. Among them:

[0018] Figure 1 It is a schematic diagram of the overall structure in the present invention.

[0019] Figure 2 It is a schematic diagram of the support assembly structure in the present invention.

[0020] Figure 3 It is a schematic diagram of the transmission member structure in the present invention.

[0021] Figure 4 It is a schematic diagram of the traveling assembly structure in the present invention. DETAILED DESCRIPTION OF THE INVENTION

[0022] To make the above objects, features, and advantages of the present invention more obvious and understandable, the following will provide a detailed description of the specific embodiments of the present invention with reference to the accompanying drawings of the specification.

[0023] Many specific details are set forth in the following description to facilitate a thorough understanding of the present invention. However, the present invention may be implemented in other ways different from those described herein. Those skilled in the art can make similar extensions without departing from the spirit of the present invention. Therefore, the present invention is not limited by the specific embodiments disclosed below.

[0024] Second, the "one embodiment" or "embodiment" referred to herein means a specific feature, structure, or characteristic that may be included in at least one implementation manner of the present invention. The "in one embodiment" that appears in different places in this specification does not all refer to the same embodiment, nor is it a separate or alternative embodiment that is mutually exclusive with other embodiments.

[0025] Embodiment 1, referring to Figures 1 to 4 , is the first embodiment of the present invention.

[0026] Specifically, an adjustable-angle solar panel bracket for a spacecraft includes a sleeve 10 detachably connected to the aircraft; and a support assembly 20 movably disposed within the sleeve 10, including a main shaft 21 and a plurality of solar panels 22 circumferentially arrayed on the outer wall of the main shaft 21; and a traveling assembly 30 disposed outside the main shaft 21 for supporting the displacement of the support assembly 20.

[0027] In summary, the sleeve 10 can be connected to the aircraft by bolts, welding, or by means of a fastening hoop. When the solar panel 22 needs to be used, the solar panel is transported to the outside of the sleeve 10 for energy storage operations. When the solar panel 22 is not needed, considering the wind resistance problem of the aircraft, the support assembly 20 can be moved into the sleeve 10 by controlling the traveling assembly 30, that is, the solar panel 22 is stored, thereby reducing the wind resistance coefficient.

[0028] It should be noted that the external shape of the sleeve 10 can be teardrop-shaped, and its internal cross-section can be equilateral triangle, rectangle, or circle.

[0029] Embodiment 2, referring to Figures 1 to 4 , is the second embodiment of the present invention.

[0030] Specifically, a fixing plate 23 is also installed on the outer wall of the main shaft 21 by bolts. A first fixing block 231 is provided on the fixing plate 23, and an adjusting member 24 is hinged on the outer wall of the first fixing block 231. The adjusting member 24 includes a first rotating cylinder 241 hinged to the first fixing block 231, and a first pull rod 242 is slidably disposed inside the first rotating cylinder 241, and a first elastic member 243 is sleeved on the outer wall of the first pull rod 242.

[0031] A second fixing block 232 is welded to the end of the first pull rod 242 away from the first pull rod 242, and the inner wall of the second fixing block 232 is slidably connected to the fixing plate 23. A transmission member 25 is hinged on the outer wall of the second fixing block 232, and the transmission member 25 includes a second rotating cylinder 251. A second pull rod 253 is movably disposed inside the second rotating cylinder 251, and a second elastic member 252 is sleeved on the outer wall of the second pull rod 253. One end of the second pull rod 253 is connected to a support rod 254.

[0032] In summary, since the shape of the sleeve 10 may need to be rotated according to the actual application scenario or the scale of the aircraft, in order to adapt to different specifications of the sleeve, each walking component 30 can perform synchronous movement.

[0033] Specifically, when controlling the movement of the first pull rod 242, it will push the transmission member 25 to displace. During this process, the walking component 30 will extend or contract outward under the support of the connecting rotating rod 233. The movement of the first pull rod 242 can be achieved by setting a cylinder. It should be noted that the first elastic member 243 is a compression spring, which can provide a certain buffering effect when the first pull rod 242 moves.

[0034] Embodiment 3, refer to Figures 1 to 4 , which is the third embodiment of the present invention.

[0035] Specifically, the walking component 30 includes a housing 31. One end of the support rod 254 away from the second pull rod 253 is hinged to the housing 31. The outer wall of the fixed plate 23 is rotatably connected with a connecting rotating rod 233, and one end of the connecting rotating rod 233 is connected to the outer wall of the housing 31. The walking component 30 further includes an output motor 32, and the output shaft of the output motor 32 extends into the housing 31 and is sleeved with an output gear 321. A crawler 33 is sleeved on the outer wall of the housing 31, and a transmission tooth meshing with the output gear 321 is integrally formed on the inner wall of the crawler 33. A support wheel body 311 for supporting the crawler 33 is also provided inside the housing 31.

[0036] In summary, the walking component 30 is used to support the overall displacement of the support component 20 with the solar panel 22. Specifically, to achieve the displacement of the support component 20, the output motor 32 can be controlled to start, driving the output gear 321 to rotate. The rotating output gear 321 will mesh with the transmission teeth on the inner wall of the crawler 33, causing the crawler 33 to rotate outside the housing 31, and then realizing the "walking" function.

[0037] Importantly, it should be noted that the construction and arrangement of the present application shown in multiple different exemplary embodiments are merely illustrative. Although only a few embodiments are described in detail in this disclosure, those who refer to this disclosure should easily understand that many modifications are possible without materially departing from the novel teachings and advantages of the subject matter described in this application (e.g., changes in the dimensions, scales, structures, shapes and proportions of various elements, as well as parameter values (such as temperature, pressure, etc.), installation arrangements, use of materials, colors, orientations, etc.). For example, an element shown as integrally formed may be composed of multiple parts or elements, the position of the element may be inverted or otherwise changed, and the nature, number or position of discrete elements may be altered or changed. Accordingly, all such modifications are intended to be included within the scope of the present invention. The order or sequence of any process or method steps may be altered or re-ordered according to alternative embodiments. In the claims, any "means plus function" clauses are intended to cover the structures that perform the recited function herein, and not only structural equivalents but also equivalent structures. Other substitutions, modifications, changes and omissions may be made in the design, operating conditions and arrangement of the exemplary embodiments without departing from the scope of the present invention. Accordingly, the present invention is not limited to the specific embodiments, but extends to various modifications that still fall within the scope of the appended claims.

[0038] In addition, in order to provide a concise description of the exemplary embodiments, not all features of the actual embodiments may be described (i.e., those features that are not relevant to the currently contemplated best mode of carrying out the present invention, or those features that are not relevant to the implementation of the present invention).

[0039] It should be understood that in the development of any actual implementation, as in any engineering or design project, numerous specific implementation decisions may be made. Such development efforts may be complex and time-consuming, but for those of ordinary skill in the art who benefit from this disclosure, without undue experimentation, such development efforts will be a routine task of design, manufacturing and production.

[0040] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them. Although the present invention has been described in detail with reference to the preferred embodiments, those of ordinary skill in the art should understand that the technical solutions of the present invention may be modified or equivalently replaced without departing from the spirit and scope of the technical solutions of the present invention, and they should all be covered within the scope of the claims of the present invention.

Claims

1. An adjustable-angle solar panel bracket for a spacecraft, characterized in that: Comprising, a sleeve (10) detachably connected to the aircraft; and, a support assembly (20) movably arranged inside the sleeve (10), including a main shaft (21) and a plurality of solar panels (22) circumferentially arrayed on the outer wall of the main shaft (21); and, a traveling assembly (30) arranged outside the main shaft (21) for supporting the displacement of the support assembly (20).

2. The adjustable-angle solar panel support for a spacecraft as claimed in claim 1, wherein: A fixing plate (23) is further installed on the outer wall of the main shaft (21) by bolts. A first fixing block (231) is arranged on the fixing plate (23), and an adjusting member (24) is hinged to the outer wall of the first fixing block (231).

3. The adjustable-angle solar panel bracket for a spacecraft as claimed in claim 2, wherein: The adjusting member (24) includes a first rotating cylinder (241) hinged to the first fixing block (231). A first pull rod (242) is slidably arranged inside the first rotating cylinder (241), and a first elastic member (243) is sleeved on the outer wall of the first pull rod (242).

4. The adjustable-angle solar panel bracket for a spacecraft according to claim 3, wherein: The first pull rod (242) is welded with a second fixing block (232) at the end far from the first pull rod (242), and the inner wall of the second fixing block (232) is slidably connected to the fixing plate (23).

5. The adjustable-angle solar panel bracket for a spacecraft as claimed in claim 4, wherein: A transmission member (25) is hinged to the outer wall of the second fixing block (232), and the transmission member (25) includes a second rotating cylinder (251).

6. The adjustable-angle solar panel bracket for a spacecraft according to claim 5, characterized in that: A second pull rod (253) is movably arranged inside the second rotating cylinder (251). A second elastic member (252) is sleeved on the outer wall of the second pull rod (253), and one end of the second pull rod (253) is connected with a support rod (254).

7. The adjustable-angle solar panel bracket for a spacecraft according to claim 6, wherein: The traveling assembly (30) includes a housing (31), and the support rod (254) is hinged to the housing (31) at the end far from the second pull rod (253).

8. The adjustable-angle solar panel bracket for a spacecraft as claimed in claim 7, wherein: A connecting rotating rod (233) is rotatably connected to the outer wall of the fixing plate (23), and one end of the connecting rotating rod (233) is connected to the outer wall of the housing (31).

9. The adjustable-angle solar panel bracket for a spacecraft according to claim 8, characterized in that: The traveling assembly (30) further includes an output motor (32), and an output shaft of the output motor (32) extends into the housing (31) and is sleeved with an output gear (321).

10. The adjustable-angle solar panel bracket for a spacecraft according to claim 9, wherein: A crawler belt (33) is sleeved on the outer wall of the housing (31), and transmission teeth meshing with the output gear (321) are integrally formed on the inner wall of the crawler belt (33). A support wheel body (311) for supporting the crawler belt (33) is further arranged inside the housing (31).

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