Solar wing lifting mechanism

Abstract

The embodiment of the application discloses a solar wing lifting mechanism, which comprises a base fixed on a satellite, at least two first supporting arms rotatably connected with the base, a bearing table for bearing a solar wing driving mechanism, second supporting arms corresponding to the first supporting arms and rotatably connected with the bearing table, and a rotating assembly rotatably connecting the first supporting arms and the second supporting arms. The rotating assembly comprises a driving member. The lifting mechanism comprises a folding state and an unfolding state. Under the driving of the driving member, the lifting mechanism is transformed from the folding state to the unfolding state. When the lifting mechanism is in the folding state, the first supporting arms and the second supporting arms are close to each other. When the lifting mechanism is in the unfolding state, the first supporting arms and the second supporting arms are separated and located on the same straight line. The mechanism can lift the solar wing driving mechanism and the solar wing on the bearing table from a position close to the satellite to a position far away from the satellite, and the solar wing rotates under the driving of the solar wing driving mechanism, so that the solar wing is aligned with the sun.

Description

Technical Field

[0001] This application relates to the field of lifting technology, and more specifically, to a solar panel lifting mechanism. Background Technology

[0002] Solar panels are the core power supply equipment of a satellite. Common configurations of solar panels include body-mounted and deployable configurations. Currently, the mainstream configuration for solar panels on high-power satellites is the multi-panel deployable configuration that can be oriented towards the sun. In this configuration, the solar panels are symmetrically mounted on both sides of the spacecraft, folded up during launch, and deployed after entering orbit, achieving sun orientation through a solar panel drive mechanism.

[0003] Because high-power satellites are typically large in size, and due to limitations in the layout of internal equipment, each side of the solar array usually has its own solar array drive mechanism. These mechanisms rotate the solar arrays to track the sun, and in some positions, the solar arrays may obstruct the satellite's antennas.

[0004] Therefore, in order to overcome the shortcomings of existing technologies, a solar panel lifting mechanism is needed. Summary of the Invention

[0005] The purpose of this invention is to provide a solar panel lifting mechanism to solve at least one of the above-mentioned technical problems.

[0006] To achieve at least one of the above objectives, this application adopts the following technical solution:

[0007] This application provides a solar panel lifting mechanism, including:

[0008] A base fixed to the satellite;

[0009] At least two first arms are rotatably connected to the base;

[0010] It also includes: a support platform for supporting the solar array drive mechanism;

[0011] A second arm that is rotatably connected to the support platform and is provided corresponding to the first arm;

[0012] The first arm and the second arm are rotatably connected by a rotating assembly.

[0013] The rotating assembly includes a drive component;

[0014] The lifting mechanism includes a retracted state and an extended state; under the drive of the driving component, the lifting mechanism changes from the retracted state to the extended state.

[0015] When the lifting mechanism is in the retracted state, the first arm and the second arm move closer together;

[0016] When the lifting mechanism is in the deployed state, the first arm and the second arm are separated and located on the same straight line.

[0017] Optionally, the support platform includes: a platform body;

[0018] An extension formed by extending outward from the edge of the platform body and rotatably connected to the second arm.

[0019] Optionally, the end of the extension away from the platform body includes two bosses, which are located on both sides of the extension.

[0020] Optionally, the rotating assembly further includes:

[0021] A first connecting piece that is fixedly connected to the first support arm;

[0022] A second connecting member that is fixedly connected to the second arm and rotatably connected to the first connecting member;

[0023] A locking element is also included between the first connector and the second connector;

[0024] When the lifting mechanism is in the deployed state, it is used to lock the first connector and the second connector so that the first connector and the second connector do not rotate relative to each other.

[0025] Optionally, the driving element is a planar spiral spring;

[0026] One end of the planar spiral spring is fixedly connected to the first connecting member, and the other end is fixedly connected to the second connecting member;

[0027] Under the elastic force of the planar spiral spring, the first and second connecting parts change from a folded state to an open state.

[0028] Optionally, the rotating assembly has two arranged side by side.

[0029] Optionally, the lifting mechanism further includes a locking member for securing the first arm and the second arm;

[0030] Under the action of the locking element, the lifting mechanism is in a retracted state.

[0031] Optionally, the locking element includes a locking part for locking the first connecting portion;

[0032] A drive spring used to move the locking part;

[0033] When the lifting mechanism is in the deployed state, the locking part locks the first connecting part under the action of the drive spring.

[0034] Optionally, both the first arm and the second arm have three;

[0035] The angle between two adjacent first arms in the retracted state is 120 degrees, and the angle between two adjacent second arms is 120 degrees.

[0036] Optionally, the base includes a base body;

[0037] A connecting arm that is rotatably connected to the first arm, formed by extending outward from the edge of the main body.

[0038] The beneficial effects of this application are as follows:

[0039] To address the problems existing in current technologies, this application provides a solar array lifting mechanism. When the solar array is lifted to a higher position, i.e., away from the satellite, the lifting mechanism needs to change from a retracted state to an extended state. At this time, the drive component drives the first and second arms to gradually change from a close-up state to a separated state, ultimately lifting the support platform above the satellite. The support platform then drives the solar array drive mechanism and the solar array located on the solar array drive mechanism to also be lifted above the satellite, thereby aligning the solar array with the sun and better converting the sun's light and heat energy into electrical energy for the satellite. The solar array lifting mechanism provided in this application can be applied to high-power satellites, capable of lifting the solar array drive mechanism and the solar array located on the support platform from a position close to the satellite to a position away from the satellite. Driven by the solar array drive mechanism, the solar array rotates, thereby aligning with the sun to obtain more light and heat energy, while also avoiding obstruction of the satellite's antennas. Attached Figure Description

[0040] The specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0041] Figure 1 This is a schematic diagram of the overall structure of the solar panel lifting mechanism in the deployed state according to one embodiment of this application.

[0042] Figure 2 This is a schematic diagram of the overall structure of the solar panel lifting mechanism in the retracted state according to one embodiment of this application.

[0043] Figure 3 Show Figure 2 A magnified view of part A in the image.

[0044] Figure 4 Show Figure 2 A magnified view of part B in the image.

[0045] Figure 5This diagram illustrates the use of the satellite, solar wing lifting mechanism, solar wing, and solar wing drive mechanism in cooperation when the solar wing lifting mechanism is in the retracted state according to one embodiment of this application.

[0046] Figure 6 This diagram illustrates the use of the satellite, solar wing lifting mechanism, solar wing, and solar wing drive mechanism in cooperation when the solar wing lifting mechanism is in the deployed state according to one embodiment of this application. Detailed Implementation

[0047] In the following description, numerous specific details are set forth for illustrative purposes and to provide a comprehensive understanding of one or more embodiments. However, it will be apparent that these embodiments can also be implemented without these specific details.

[0048] In the description of this application, it should be noted that the terms "upper," "lower," etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application. Unless otherwise expressly specified and limited, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication between two elements. For those skilled in the art, the specific meaning of the above terms in this application can be understood according to the specific circumstances.

[0049] It should also be noted that, in the description of this application, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0050] To address the problems existing in the prior art, one embodiment of this application provides a solar panel lifting mechanism 10, such as... Figure 1-6As shown, the system includes: a base 2 fixed to satellite 1; at least two first arms 3 rotatably connected to the base 2; and a support platform 4 for supporting the solar array drive mechanism 11. The solar array 12 has two symmetrical arms, symmetrically arranged on opposite sides of the solar array drive mechanism 11. Driven by the solar array drive mechanism 11, the two solar arrays 12 rotate to align with the sun, saving costs. The lifting mechanism 10 also includes a second arm 5 rotatably connected to the support platform 4 and corresponding to the first arms 3. The first arms 3 and the second arms 5 are rotatably connected via a rotating assembly 6. The rotating assembly 6 includes a drive component. The lifting mechanism 10 has a retracted state and an extended state. Driven by the drive component, the lifting mechanism 10 changes from the retracted state to the extended state. When the lifting mechanism 10 is in the retracted state, the first arms 3 and the second arms 5 approach each other. When the lifting mechanism 10 is in the extended state, the first arms 3 and the second arms 5 separate and are located on the same straight line.

[0051] In the above embodiments of this application, when the solar array 12 is lifted to a higher position, i.e., away from satellite 1, the lifting mechanism 10 needs to change from a retracted state to an extended state. At this time, the driving component drives the first arm 3 and the second arm 5 to gradually change from a close-up state to a separated state, ultimately lifting the support platform 4 above satellite 1. The support platform 4 drives the solar array drive mechanism 11 and the solar array 12 located on the solar array drive mechanism 11 to also be lifted above satellite 1, thereby aligning the solar array 12 with the sun and better converting the sun's light and heat energy into electrical energy used by satellite 1. The solar array lifting mechanism 10 provided by this application can be applied to high-power satellite 1, and can lift the solar array drive mechanism 11 and the solar array 12 located on the support platform 4 from a position close to satellite 1 to a position away from satellite 1. Driven by the solar array drive mechanism 11, the solar array 12 rotates, thereby aligning with the sun to obtain more light and heat energy, while also avoiding obstruction of the antenna on satellite 1.

[0052] Specifically, the lifting mechanism 10 further includes a locking member 7 for fixing the first arm 3 and the second arm 5; under the action of the locking member 7, the lifting mechanism 10 is in a retracted state. When the lifting mechanism 10 needs to change from the retracted state to the extended state, under the control of the controller of satellite 1, the locking member 7 is unlocked, and the first arm 3 and the second arm 5 change from a close-up state to a separate state under the action of the drive member of the rotating assembly 6.

[0053] In one specific embodiment, the rotating assembly 6 has two arranged side by side. The two rotating assemblies 6 enable a greater driving force when the first arm 3 and the second arm 5 change from a close-up state to a separated state, and the separation process is faster and more stable.

[0054] Specifically, the rotating assembly 6 further includes: a first connecting member 62 fixedly connected to the first support arm 3; a second connecting member 63 fixedly connected to the second support arm 5 and rotatably connected to the first connecting member 62; a locking member is also included between the first connecting member 62 and the second connecting member 63; when the lifting mechanism 10 is in the deployed state, it is used to lock the first connecting member 62 and the second connecting member 63 so that the first connecting member 62 and the second connecting member 63 do not rotate relative to each other. The locking member includes: a locking part 64 for locking the first connecting part 62, and a drive spring (not shown in the figure) for driving the locking part 64 to move. When the lifting mechanism 10 is in the deployed state, that is, when the first support arm 3 and the second support arm 5 are on the same straight line, the locking part 64 locks the first connecting part 62 under the action of the drive spring, so that it cannot rotate relative to the second connecting part. At this time, the second support arm 5 also cannot rotate, thus locking the first support arm 3 and the second support arm 5.

[0055] In a specific example, the driving component is a planar spiral spring 61; one end of the planar spiral spring 61 is fixedly connected to the first connecting member 62, and the other end is fixedly connected to the second connecting member 63; under the elastic force of the planar spiral spring 61, the first connecting member 62 and the second connecting member 63 change from a folded state to an open state. Specifically, when the first arm 3 and the second arm 5 are unlocked by the locking member 7, the two ends of the planar spiral spring 61 drive the first connecting member 62 and the second connecting member 63 respectively, causing them to open, thereby unfolding the first arm 3 and the second arm 5.

[0056] In one specific embodiment, the support platform 4 includes: a platform body 41; the platform body 41 can be circular, but is not limited to a circle; and extension portions 42 formed by extending outward from the edges of the platform body 41 and rotatably connected to the second support arm 5. In this way, the support surface of the support platform 4 is larger, and when the second support arm 5 rotates relative to the support platform 4, it will not affect the solar wing drive mechanism 11 on the support platform 4.

[0057] Specifically, such as Figure 4 As shown, the end of the extension 42 away from the platform body 41 includes two protrusions 43, which are located on both sides of the extension 42. The protrusions 43 cooperate with the second support arm 5 to prevent the lifting mechanism 10 from tipping over due to the asynchronous movement of multiple second support arms at the initial moment when the lifting mechanism 10 moves from the retracted state to the extended state.

[0058] In one specific example, the base 2 includes a base body 21 and connecting arms 22 extending outward from the edges of the base body and rotatably connected to the first support arm 3. This design increases the supporting force of the base 2 while saving space and materials.

[0059] In a specific example, there are three of each of the first support arm 3 and the second support arm 5; the angle between two adjacent first support arms 3 in the retracted state is 120 degrees, and the angle between two adjacent second support arms 5 is also 120 degrees. The base 2 also has three connecting arms 22, and the angle between two adjacent connecting arms 22 is also 120 degrees; the support platform 4 also has three extensions 42, and the angle between two adjacent extensions 42 is also 120 degrees. The arrangement of three extensions 42, two second support arms 5, one first support arm 3, and three connecting arms 22 gives the entire lifting mechanism 10 good rigidity and stability, reducing the impact on the baseband frequency of satellite 1.

[0060] In practical applications, the lifting mechanism 10 provided in this application is in a retracted state when the satellite 1 is launched. After the satellite 1 enters orbit, the solar array 12 unfolds. After unfolding, the locking member 7 of the lifting mechanism 10 unlocks the first arm 3 and the second arm 5. Under the action of the planar spiral spring 61, the first arm 3 and the second arm 5 gradually change from a close-up state to a separated state. During this process, the support platform 4 slowly moves away from the satellite 1 until it is fully unfolded. At this time, the solar array 12 is lifted to the predetermined height, and the solar array drive mechanism 11 enables the solar array 12 to be accurately aligned with the sun.

[0061] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. For those skilled in the art, other variations or modifications can be made based on the above description. It is impossible to exhaustively list all the implementation methods here. All obvious variations or modifications derived from the technical solutions of the present invention are still within the protection scope of the present invention.

Claims

1. A solar panel lifting mechanism, characterized in that, include: A base fixed to the satellite; At least two first arms are rotatably connected to the base; It also includes: a support platform for supporting the solar array drive mechanism; A second arm that is rotatably connected to the support platform and is provided corresponding to the first arm; The first arm and the second arm are rotatably connected by a rotating assembly. The rotating assembly includes a driving component; The lifting mechanism includes a retracted state and an extended state; under the drive of the driving component, the lifting mechanism changes from the retracted state to the extended state. When the lifting mechanism is in the retracted state, the first arm and the second arm move closer together; When the lifting mechanism is in the deployed state, the first arm and the second arm are separated and located on the same straight line; The support platform includes: a platform body; An extension portion that is rotatably connected to the second arm is formed by extending outward from the edge of the platform body; The end of the extension away from the platform body includes two protrusions, which are located on both sides of the extension. The protrusions cooperate with the second arm to prevent the lifting mechanism from tipping over due to the asynchronous movement of multiple second arms at the initial moment when the lifting mechanism changes from the retracted state to the extended state. The rotating assembly further includes: A first connecting piece that is fixedly connected to the first support arm; A second connecting member that is fixedly connected to the second arm and rotatably connected to the first connecting member; A locking element is also included between the first connector and the second connector; When the lifting mechanism is in the deployed state, it is used to lock the first connecting member and the second connecting member so that the first connecting member and the second connecting member do not rotate relative to each other; The driving component is a planar spiral spring; One end of the planar spiral spring is fixedly connected to the first connecting member, and the other end is fixedly connected to the second connecting member; Under the elastic force of the planar spiral spring, the first and second connecting parts change from a folded state to an open state.

2. The solar panel lifting mechanism according to claim 1, characterized in that, The rotating assembly has two arranged side by side.

3. The solar panel lifting mechanism according to claim 2, characterized in that, The lifting mechanism further includes a locking element for securing the first arm and the second arm; Under the action of the locking element, the lifting mechanism is in a retracted state.

4. The solar panel lifting mechanism according to claim 3, characterized in that, The locking element includes a locking portion for locking the first connector; A drive spring used to move the locking part; When the lifting mechanism is in the deployed state, the locking part locks the first connecting member under the action of the drive spring.

5. The solar panel lifting mechanism according to claim 1, characterized in that, Both the first arm and the second arm have three; The angle between two adjacent first arms in the retracted state is 120 degrees, and the angle between two adjacent second arms is 120 degrees.

6. The solar panel lifting mechanism according to claim 1, characterized in that, The base includes a base body; A connecting arm that is rotatably connected to the first arm, formed by extending outward from the edge of the main body.

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