Driving mechanism of solar wing and satellite

Abstract

The invention discloses a driving mechanism of a solar wing and a satellite. The driving mechanism of the solar wing comprises a lifting mechanism and a sun orientation mechanism, the sun orientation mechanism comprises a first shaft driving mechanism installed on the lifting mechanism, a second shaft support installed on the first shaft driving mechanism, a second shaft driving mechanism installed on the second shaft support and a solar wing connecting piece installed on the second shaft driving mechanism. The lifting mechanism comprises a deformable multi-connecting-rod body, and the multi-connecting-rod body comprises a root installation driving assembly close to the satellite body, a top installation assembly away from the satellite body and a lifting beam assembly rotationally connected between the root installation driving assembly and the top installation assembly. According to the invention, interference between the solar wing and a star in the sun orientation process can be avoided; in addition, the lifting device has the advantages of compact structure, small folding size, high lifting rigidity, high use stability and the like.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and in particular to a drive mechanism for a solar array. Background Technology

[0002] In the aerospace field, solar panels are the power generation devices on spacecraft, converting solar energy into electrical energy to power various electrical components. The angle between sunlight and the solar panel's surface affects the solar cell's power generation efficiency; the efficiency is highest when sunlight is perpendicular to the solar panel's surface. Therefore, to improve the solar panel's power generation capability, it should be ensured that the solar panel is aligned with the sun as much as possible, ideally keeping the solar panel perpendicular to the surface.

[0003] Current sun-orientation mechanisms come in various forms, but they all have some drawbacks, such as: heavy overall weight, high cost, large size, insufficient lifting stiffness, poor motion stability, and easy interference with celestial bodies.

[0004] Therefore, it is necessary to propose a solar array drive mechanism and satellite to solve at least one of the above problems. Summary of the Invention

[0005] To address the shortcomings of existing technologies, this invention provides a solar array drive mechanism and satellite that can prevent interference between the solar array and celestial bodies during solar orientation. In addition, it has the advantages of compact structure, small folded volume, high lifting stiffness, and high operational stability.

[0006] The specific technical solution of the embodiments of the present invention is as follows:

[0007] A solar array drive mechanism includes a lifting mechanism and a solar orientation mechanism. The solar orientation mechanism includes a first shaft drive mechanism mounted on the lifting mechanism, a second shaft support mounted on the first shaft drive mechanism, a second shaft drive mechanism mounted on the second shaft support, and a solar array connector mounted on the second shaft drive mechanism. The lifting mechanism includes a deformable multi-link body, which includes a root-mounted drive assembly near the satellite body, a top-mounted assembly away from the satellite body, and a lifting beam assembly connecting the root-mounted drive assembly and the top-mounted assembly. The lifting mechanism has a retracted state and a lifted state. When the lifting mechanism switches from the retracted state to the lifted state, the lifting beam assembly deforms under the drive of the root-mounted drive assembly, causing the top-mounted assembly to move the solar orientation mechanism away from the satellite body to a target position.

[0008] A satellite includes a satellite body and solar arrays. A drive mechanism for the solar arrays, as described above, is installed between the satellite body and the solar arrays. The solar arrays include two sets, which are symmetrically arranged about a predetermined base plane. The predetermined base plane is a plane passing through the rotation axis of the first axis drive mechanism and perpendicular to the rotation axis of the second axis drive mechanism.

[0009] The technical solution of the present invention has the following significant beneficial effects:

[0010] The solar array drive mechanism provided in this application embodiment uses a deformable multi-link body as the main body of the lifting mechanism. This multi-link body can be folded or unfolded to deform, allowing the lifting mechanism to have a retracted state and a lifted state. After the satellite enters orbit, the lifting mechanism can switch from the retracted state to the lifted state. Through deformation, the lifting mechanism moves the solar orientation mechanism and the solar array mounted on the solar orientation mechanism to the target position away from the satellite body, ensuring that the solar array is kept at a predetermined distance from the satellite body during use. This avoids interference between the solar array and the satellite body during solar orientation and also reduces the interference of the solar array on the field of view of onboard communication payloads (laser communication payloads or microwave payloads).

[0011] Specific embodiments of the invention are disclosed in detail with reference to the following description and accompanying drawings, indicating how the principles of the invention can be employed. It should be understood that the embodiments of the invention are not therefore limited in scope. Within the spirit and scope of the appended claims, embodiments of the invention include many changes, modifications, and equivalents. Features described and / or shown for one embodiment may be used in the same or similar manner in one or more other embodiments, combined with features in other embodiments, or substituted for features in other embodiments. Attached Figure Description

[0012] The accompanying drawings described herein are for illustrative purposes only and are not intended to limit the scope of the invention in any way. Furthermore, the shapes and proportions of the components in the drawings are merely illustrative to aid in understanding the invention and do not specifically limit the shapes and proportions of the components. Those skilled in the art, guided by the teachings of this invention, can select various possible shapes and proportions to implement the invention according to specific circumstances.

[0013] Figure 1 This is a schematic diagram of a solar panel drive mechanism in a lifted state, as provided in the embodiments of this application.

[0014] Figure 2 for Figure 1 A partial cross-sectional view of a solar panel drive mechanism in a lifted state, provided in an embodiment of this application;

[0015] Figure 3 This is a schematic diagram of the drive mechanism of a solar panel provided in the embodiment of this application in a retracted state;

[0016] Figure 4 This is a schematic diagram of rotation along axis A;

[0017] Figure 5 A schematic diagram of rotation along axis B;

[0018] Figure 6 This is a schematic diagram of the root mounting driver component provided in the embodiments of this application in a first state;

[0019] Figure 7 for Figure 6 The image shows a cross-sectional view of the linkage locking component;

[0020] Figure 8 This is a schematic diagram showing the root mounting driver component provided in the embodiments of this application in a second state;

[0021] Figure 9 for Figure 8 The image shows a cross-sectional view of the linkage locking component;

[0022] Figure 10 This is a schematic diagram of the drive mechanism of another solar panel provided in the embodiment of this application in a retracted state;

[0023] Figure 11 This is a schematic diagram of the drive mechanism of another solar panel provided in the embodiment of this application in a lifted state.

[0024] Reference numerals in the figures of this application:

[0025] 1. Lifting mechanism;

[0026] 2. Second shaft support;

[0027] 3. Second axis drive mechanism;

[0028] 4. First axis drive mechanism;

[0029] 5. Solar panel connector;

[0030] 11. Root hinge;

[0031] 12. Raise the beam;

[0032] 13. Raise the beam;

[0033] 14. Place the tray on top;

[0034] 15. First lifting beam assembly;

[0035] 16. Second lifting beam assembly;

[0036] 111. Movable hinge;

[0037] 1110. Guide hole;

[0038] 1111, Long groove;

[0039] 112. Root hinge spring;

[0040] 113. Root base;

[0041] 1130. Locking hole;

[0042] 114. Spring hub;

[0043] 1140. Guide groove;

[0044] 1141. Opening;

[0045] 115. Installation components;

[0046] 116. Guide contact part;

[0047] 61. Linkage components;

[0048] 62. Locking components;

[0049] 63. Reset component;

[0050] 7. Unlocking device.

[0051] 8. Satellite body;

[0052] X, first direction;

[0053] Y, the second direction;

[0054] Z, Third-party orientation. Detailed Implementation

[0055] The technical solution of the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that these embodiments are only used to illustrate the present invention and are not intended to limit the scope of the present invention. After reading the present invention, any modifications of the present invention in various equivalent forms by those skilled in the art fall within the scope defined by the appended claims.

[0056] It should be noted that when an element is referred to as being "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.

[0057] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein in the specification of this application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0058] This invention provides a drive mechanism for a solar array and a satellite that can avoid interference with celestial bodies during the solar array's orientation to the sun. In addition, it has the advantages of compact structure, small folded volume, high lifting stiffness, and high operational stability.

[0059] Please refer to the following for comprehensive information. Figures 1 to 11 This application specification provides a drive mechanism for a solar array, which may include a lifting mechanism 1 and a solar orientation mechanism; the solar orientation mechanism includes a first shaft drive mechanism 4 mounted on the lifting mechanism 1, a second shaft support 2 mounted on the first shaft drive mechanism 4, and a second shaft drive mechanism 3 mounted on the second shaft support 2. The lifting mechanism 1 includes a solar array connector 5 mounted on the second shaft drive mechanism 3; the lifting mechanism 1 includes a deformable multi-link body, the multi-link body including: a root mounting drive assembly near the satellite body 8, a top mounting assembly away from the satellite body 8, and a lifting beam assembly rotatably connected between the root mounting drive assembly and the top mounting assembly; the lifting mechanism 1 is connected to the satellite body 8 through the root mounting drive assembly, and the top mounting assembly is used to mount the solar orientation mechanism; the lifting mechanism 1 has a retracted state and a lifted state, when the lifting mechanism 1 switches from the retracted state to the lifted state, the lifting beam assembly deforms under the drive of the root mounting drive assembly, driving the top mounting assembly to move the solar orientation mechanism away from the satellite body 8 to the target position.

[0060] The solar array drive mechanism provided in this embodiment mainly includes a lifting mechanism 1 and a solar orientation mechanism. The lifting mechanism 1 is used to be installed on the satellite body 8, and the solar orientation mechanism is installed on the lifting mechanism 1.

[0061] like Figure 2 As shown, the solar orientation mechanism may include: a first shaft drive mechanism 4 mounted on the lifting mechanism 1, a second shaft support 2 mounted on the first shaft drive mechanism 4, a second shaft drive mechanism 3 mounted on the second shaft support 2, and a solar fin connector 5 mounted on the second shaft drive mechanism 3.

[0062] Specifically, the first axis drive mechanism 4 in the dual-axis solar orientation mechanism is fixed to the lifting mechanism 1. More specifically, it can be mounted on the upper tray 14 of the lifting mechanism 1. The first axis drive mechanism 4 can drive the second axis support 2 to rotate. The second axis drive mechanism 3 is fixed to the second axis support 2 and can drive the solar array connector 5 to rotate.

[0063] Please refer to the following: Figure 4 and Figure 5 Generally, the second-axis drive mechanism 3 can adjust the angle between the normal of the solar array surface and the normal of the orbital plane to achieve solar orientation during the satellite's orbit around the Earth. The first-axis drive mechanism 4 can adjust the angle between the solar array deployment direction and the orbital plane to adapt to changes in the angle between sunlight and the orbital plane in different seasons. The combined drive of the second and first axes can improve the solar array's solar orientation capability and is suitable for solar arrays with complex orbital lighting conditions.

[0064] The solar orientation mechanism provided in this application is a dual-axis solar orientation mechanism, which has high orientation and tracking accuracy.

[0065] The solar orientation mechanism is provided with two sets of second axis drive mechanisms 3, which are symmetrically installed on the second axis bracket 2. Each set of second axis drive mechanisms 3 drives a set of solar panels.

[0066] In use, the solar orientation mechanism can drive two sets of solar arrays simultaneously. When the solar arrays are symmetrically arranged, the change in the center of mass of the solar array system during the solar orientation process is small (specifically, the center of mass of the solar array system is basically located at the intersection of the rotation axes of the first axis drive mechanism 4 and the second axis drive mechanism 3), resulting in high motion stability.

[0067] The lifting mechanism 1 may include a deformable multi-link body. This multi-link body can be folded or unfolded to deform, resulting in high overall lifting rigidity and high stability during use. For details, please refer to the relevant documentation. Figure 1 and Figure 3 or refer to the following: Figure 10 and Figure 11The lifting mechanism 1 has a retracted state and a lifted state. During satellite launch, the lifting mechanism 1 is in the retracted state, resulting in a smaller volume and more compact structure. After the satellite enters orbit, the lifting mechanism 1 can switch from the retracted state to the lifted state, thereby moving the solar array a predetermined distance away from the satellite body 8 (hereinafter referred to as the satellite). When the lifting mechanism 1 switches from the retracted state to the lifted state, it can deform, moving the solar orientation mechanism and the solar array mounted on it away from the satellite body 8 to a target position, thus lifting the solar array away from the satellite and avoiding interference with the satellite during solar orientation. In other words, by using the lifting mechanism 1, after the satellite enters orbit, the solar array can be lifted away from the satellite, avoiding interference with the satellite during solar orientation; furthermore, it can reduce the field-of-view interference of the solar array on onboard communication payloads (laser communication payloads or microwave payloads).

[0068] The multi-link body of the lifting mechanism 1 may include: a root-mounted drive assembly near the satellite body 8, a top-mounted assembly away from the satellite body 8, and a lifting beam assembly rotatably connected between the root-mounted drive assembly and the top-mounted assembly. The lifting mechanism 1 is connected to the satellite body 8 via the root-mounted drive assembly, the top-mounted assembly is used to mount the solar orientation mechanism, and the lifting beam assembly located between the root-mounted drive assembly and the top-mounted assembly is mainly used to realize the deformation of the lifting mechanism 1.

[0069] like Figure 1 and Figure 3 ,or Figure 10 and Figure 11 As shown, in some embodiments, the lifting beam assembly may include a first lifting beam assembly 15 and a second lifting beam assembly 16 arranged symmetrically; the first lifting beam assembly 15 and the second lifting beam assembly 16 respectively include a lower lifting beam 12 and an upper lifting beam 13, the lower end of the lower lifting beam 12 is fixedly connected to the root mounting drive assembly, the upper end of the lower lifting beam 12 is rotatably connected to the lower end of the upper lifting beam 13, and the upper end of the upper lifting beam 13 is rotatably connected to the top mounting assembly, the two sets of lower lifting beams 12 and upper lifting beams 13 together with the root mounting drive assembly and the top mounting assembly form a six-bar linkage mechanism.

[0070] In this embodiment, the lifting beam assembly includes a first lifting beam assembly 15 and a second lifting beam assembly 16 arranged symmetrically. The first lifting beam assembly 15 and the second lifting beam assembly 16 are symmetrically arranged between the root mounting drive assembly and the top mounting assembly at a certain distance. The symmetrical linkage mechanism can evenly distribute the load, improve the stability during the lifting process, and avoid deformation or jamming caused by unilateral force.

[0071] To ensure the stability of the lifting mechanism 1 in the lifting state, a locking structure (not shown in the figure) can be provided at the rotating connection position. Specifically, the rotating connection can be a hinge, and the locking structure can be a mechanical locking structure, a friction-damped locking structure, an electromagnetic / electric locking structure, etc. Of course, the specific form of the locking structure is not limited to the examples above. Those skilled in the art may make other modifications based on the technical essence of this application, but as long as the function and effect achieved are the same as or similar to those of this application, they should be covered within the scope of protection of this application.

[0072] Please refer to the following: Figure 6 , Figure 7 , Figure 8 and Figure 9 In one embodiment, the root mounting drive assembly includes a root hinge 11 mounted on the satellite body 8. The root hinge 11 includes a root hinge base, a movable hinge 111 rotatably connected to the root hinge base, and a drive member for providing driving force to the movable hinge 111. The movable hinge 111 is fixedly connected to the lower end of the lower lifting beam 12. When the lifting mechanism 1 switches from the retracted state to the lifting state, the movable hinge 111 rotates under the drive of the drive member. When the movable hinge 111 rotates to its position, the solar orientation mechanism moves to the target position.

[0073] In this embodiment, the root mounting drive assembly may include a root hinge 11 mounted on the satellite body 8. The root hinge 11 may include a root base 113, a movable hinge 111, and a drive component.

[0074] The root base 113 can serve as a support base for the lifting mechanism 1, and is used to fix it to the satellite body 8. The root base 113 may include opposing first and second sides, as well as opposing third and fourth sides.

[0075] The movable hinge 111 is rotatably connected to the root chassis 113. The movable hinge 111 can be divided into two groups, one group being located near the first side of the root chassis 113, and the other group being located near the second side of the root chassis 113. For each group of movable hinges 111, two hinge members may be included, spaced a predetermined distance apart and located on the third and fourth sides of the root chassis 113, respectively.

[0076] When the lifting mechanism 1 is in the retracted state, the two lower lifting beams 12 are distributed on both sides of the root hinge base, and are arranged sequentially along the first direction X with the root hinge base; the two upper lifting beams 13 are distributed on both sides of the top mounting assembly, and are arranged sequentially along the first direction X with the top mounting assembly. The top mounting assembly includes an upper tray 14. In the first direction X, the sum of the dimensions of the two lower lifting beams 12 and the root hinge base is equal to the sum of the dimensions of the two upper lifting beams 13 and the upper tray 14. That is, when the lifting mechanism 1 is in the retracted state, the lower three-link formed by the two lower lifting beams 12 and the root hinge base can fit snugly against the upper three-link formed by the two upper lifting beams 13 and the upper tray 14, thereby reducing the retracted volume of the lifting mechanism 1 and making its structure more compact.

[0077] Furthermore, such as Figure 10 and Figure 11 As shown, the rotation axis of the first shaft drive mechanism 4 extends along the second direction Y, and the rotation axis of the second shaft drive mechanism 3 extends along the third direction Z. The first direction X, the second direction Y, and the third direction Z are perpendicular to each other. Overall, the lifting mechanism 1 and the sun-aligning mechanism have a compact structural design, uniform and reasonable force distribution, and stable structure, which can avoid structural deformation or stress concentration caused by force in a single direction.

[0078] In one embodiment, the driving component may include a root hinge spring 112, and spring hubs 114 are symmetrically arranged on the periphery of the root hinge chassis. The root hinge spring 112 is mounted on the spring hubs 114. A mounting member 115 is provided on the movable hinge 111, and the mounting member 115 contacts the root hinge spring 112. When the lifting mechanism 1 is in the retracted state, the root hinge spring 112 stores elastic potential energy. When the lifting mechanism 1 switches from the retracted state to the lifting state, the elastic potential energy of the root hinge spring 112 is converted into mechanical energy.

[0079] In this embodiment, the driving component may specifically include a root hinge spring 112. Specifically, the root hinge spring 112 may be mounted on a spring hub 114, which may be fixed to the root hinge chassis. A mounting member 115 may be provided on the movable hinge 111, which is fixed to the movable hinge 111 and contacts the root hinge spring 112. Specifically, the spring hubs 114 are arranged corresponding to the movable hinge 111, and there may be four spring hubs 114 symmetrically arranged on the periphery of the root hinge chassis.

[0080] When the hinge spring 112 moves due to the release of its elastic potential energy, it can drive the movable hinge 111 to rotate by a predetermined angle via the mounting member 115. The predetermined angle rotated by the movable hinge 111 is approximately 90°. Of course, the angle rotated by the movable hinge 111 can vary depending on the fit between the various components, and its specific value is not uniquely limited in this application. In this embodiment, a 90° rotation is used as an example for illustration.

[0081] Specifically, the mounting component 115 may include a guide contact portion 116, which can be a guide shaft fixedly mounted on the movable hinge 111. This guide shaft can abut against the root hinge spring 112, thereby receiving the force applied by the root hinge spring 112. Furthermore, the mounting component 115 may also include a mounting bracket fixedly mounted on the movable hinge 111, with a slot for the root hinge spring 112 to pass through. This mounting bracket ensures reliable contact with the root hinge spring 112 and also enhances the strength of the mounting bracket, improving reliability during use.

[0082] In one embodiment, the lifting mechanism 1 further includes a linkage locking component, which is disposed between the spring hub 114, the movable hinge 111, and the root hinge chassis. The linkage locking component includes an unlocked state and a locked state. When the lifting mechanism 1 needs to switch from the retracted state to the lifting state, the elastic potential energy of the root hinge spring 112 is converted into mechanical energy, driving the movable hinge 111 to rotate. When the movable hinge 111 rotates to its position, the linkage locking component switches from the unlocked state to the locked state. The movable hinge 111 is constrained and positioned by the root hinge chassis through the linkage locking component, thereby giving the lifting mechanism 1 a high locking stiffness.

[0083] In this embodiment, the linkage locking component is disposed between the spring hub 114, the movable hinge 111 and the root hinge chassis, and is used to further constrain and position the movable hinge 111 after the root hinge spring 112 releases its elastic potential energy and the movable hinge 111 rotates into place.

[0084] The linkage locking assembly mainly includes: linkage component 61, reset component 63, and locking component 62.

[0085] Specifically, the spring hub 114 is provided with an arc-shaped guide groove 1140 on the side facing the movable hinge 111, and an opening 1141 is formed at the end of the guide groove 1140; one end of the linkage 61 extends into the guide groove 1140 and can be used for limiting the movement.

[0086] The root hinge base is provided with a locking hole 1130, which is used to cooperate with the end of the locking member 62 to form a locking mechanism.

[0087] The movable hinge 111 has a guide hole 1110 open at one end, and the reset member 63 and the locking member 62 are installed in the guide hole 1110. Specifically, the locking member 62 is installed in the guide hole 1110 with a clearance fit, allowing the locking member 62 to move axially relative to the guide hole 1110. The reset member 63 is located between the other end of the guide hole 1110 and the locking member 62, and the reset member 63 is in contact with the locking member 62. The reset member 63 can be in the form of a compression spring, although it can also be in other forms. In this embodiment, a compression spring is used as an example. Before the movable hinge 111 rotates to its final position, the compression spring is in a compressed state and abuts against the locking member 62.

[0088] Before the movable hinge 111 rotates to its final position, the spring hub 114, the linkage 61, and the movable hinge 111 cooperate to constrain the locking member 62 within the guide hole 1110. After the movable hinge 111 rotates to its final position, one end of the linkage 61 slides out of the guide groove 1140 through the opening 1141. The reset member 63 pushes the end of the locking member 62 out of the guide hole 1110 and engages it in the locking hole 1130, thus completing the locking. Figure 6 and Figure 7 The status shown has been switched to Figure 8 and Figure 9 The state shown.

[0089] In order to ensure that the locking member 62 can be accurately and reliably engaged in the locking hole 1130, the end of the locking member 62 can be provided with a guide portion, for example, it can be in the shape of a frustum with a certain cone angle. Correspondingly, the locking hole 1130 can also be a conical hole.

[0090] The locking member 62 can be a hollow cylindrical structure with a stepped hole inside. A portion of the compression spring can extend into the locking member 62, with one end abutting against the step corresponding to the stepped hole and the other end abutting against the movable hinge 111. For example, a limiting part can be provided on the movable hinge 111, and the other end of the compression spring can be fitted onto this limiting part, thereby reliably limiting the compression spring and ensuring its extension and retraction along a predetermined direction.

[0091] A through hole for the linkage 61 to pass through can be provided on the cylindrical wall of the locking member 62. The middle part of the linkage 61 can pass through the through hole, that is, the linkage 61 can pass through the locking member 62 through the through hole. In addition, a slot for the linkage 61 to pass through can also be provided on the side wall of the movable hinge 111. The slot can be a long slot 1111 extending longitudinally along the axial direction of the locking member 62, and the middle part of the linkage 61 can pass through the long slot 1111. The setting of the long slot 1111 allows the middle part of the linkage 61 and the locking member 62 to move relative to each other along the direction of the long slot 1111, ensuring that the end of the locking member 62 can be smoothly moved out of the guide hole 1110, so that there is no interference between the structures.

[0092] Before the movable hinge 111 rotates into place, the end of the locking member 62 can be located in the guide hole 1110 of the movable hinge 111.

[0093] When the root hinge spring 112 releases its elastic potential energy, it drives the spring hub 114 to rotate. The spring hub 114 then drives the movable hinge 111 and the linkage 61 to rotate. The compression spring and locking member 62 installed in the movable hinge 111 rotate synchronously. When the movable hinge 111 rotates to its position, one end of the linkage 61 slides out from the opening 1141 of the guide groove 1140 of the spring hub 114. Under the restoring force of the compression spring, the locking member 62 is pushed out of the guide hole 1110 and engaged in the locking hole 1130, thus achieving locking. Overall, this linkage locking assembly is cleverly designed between the movable hinge 111, the spring hub 114, and the root hinge chassis, making full use of the structural characteristics and matching relationships of the movable hinge 111, the spring hub 114, and the root hinge chassis themselves. It has high locking rigidity during use, and its structure is ingenious, compact, and highly reliable.

[0094] This application also provides a satellite, which includes the above-mentioned solar array drive mechanism. By setting the solar array drive mechanism, the satellite can achieve the technical effects achieved by the solar array drive mechanism implementation method. For details, please refer to the specific description of the above implementation method. This application will not repeat it here.

[0095] Specifically, the satellite may include a satellite body 8 and solar panels, with the solar panel drive mechanism installed between the satellite body 8 and the solar panels. The solar panels include two sets, which can be symmetrically arranged about a predetermined base plane, which is a plane passing through the rotation axis of the first axis drive mechanism 4 and perpendicular to the rotation axis of the second axis drive mechanism 3.

[0096] In use, the solar orientation mechanism can drive two sets of solar arrays simultaneously. When the solar arrays are symmetrically arranged, the change in the center of mass of the solar array system is small and the motion stability is high during the solar orientation process.

[0097] like Figure 10 and Figure 11 As shown, in some embodiments, the satellite may also include an unlocking device 7, which is used to keep the lifting mechanism 1 in a retracted state. When the unlocking device 7 is unlocked, the lifting mechanism 1 can deform under the drive of the root-mounted drive assembly, and move the top-mounted assembly and the sun-oriented mechanism to the target position away from the satellite body 8.

[0098] In this embodiment, to ensure that the lifting mechanism 1 can reliably remain in the retracted state before the satellite enters orbit, i.e. when it is necessary to maintain the retracted state, an unlocking device 7 can be installed between the satellite and the lifting mechanism 1. Before the satellite enters orbit, the lifting mechanism 1 is in the retracted state due to the constraint force provided by the unlocking device 7. When it is necessary to switch from the retracted state to the lifting state, the unlocking device 7 is unlocked, i.e., the constraint force applied to the lifting mechanism 1 is released. The lifting mechanism 1 can deform under the drive of the drive assembly installed at the root, and drive the top mounting assembly to move the sun orientation mechanism away from the satellite body 8 to the target position, thus completing the lifting.

[0099] Specifically, the unlocking device 7 mainly includes a pyrotechnic unlocking device 7 and a non-pyrotechnic unlocking device 7. The pyrotechnic unlocking device 7 includes a pyrotechnic cutter, a pyrotechnic release nut, etc.; the non-pyrotechnic unlocking device 7 includes a hot knife, a shape memory alloy unlocking device 7, etc. In this embodiment, a shape memory alloy unlocking device 7 can be selected. Shape memory alloys are in the martensitic phase at low temperatures and are easily deformed. When heated to a certain temperature, they undergo a phase transformation, transforming into a high-temperature austenitic phase, and simultaneously recovering their original shape, generating significant restoring force and deformation displacement. The shape memory alloy unlocking device 7 utilizes this characteristic, by applying electricity or other heating methods to the shape memory alloy element to cause deformation, driving the related mechanism to move, thereby achieving reliable unlocking.

[0100] It should be noted that in the description of this application, the terms "first," "second," etc., are used only for descriptive purposes and to distinguish similar objects; there is no order between them, nor should they be construed as indicating or implying relative importance. Furthermore, in the description of this application, unless otherwise stated, "multiple" means two or more.

[0101] The various embodiments described in this specification are presented in a progressive manner. The same or similar parts between the embodiments can be referred to each other. Each embodiment focuses on the differences from other embodiments.

[0102] The above are merely a few embodiments of the present invention. Although the embodiments disclosed in the present invention are as described above, the content is only for the purpose of facilitating understanding of the present invention and is not intended to limit the present invention. Any person skilled in the art to which this invention pertains may make any modifications and changes in the form and details of the embodiments without departing from the spirit and scope disclosed in the present invention. However, the patent protection scope of the present invention shall still be determined by the scope defined in the appended claims.

Claims

1. A drive mechanism for a solar array, characterized in that, The drive mechanism of the solar array includes: a lifting mechanism and a solar orientation mechanism; The solar orientation mechanism includes: a first shaft drive mechanism mounted on the lifting mechanism, a second shaft bracket mounted on the first shaft drive mechanism, a second shaft drive mechanism mounted on the second shaft bracket, and a solar fin connector mounted on the second shaft drive mechanism; The lifting mechanism includes a deformable multi-link body, the multi-link body comprising: a root mounting drive assembly near the satellite body, a top mounting assembly away from the satellite body, and a lifting beam assembly rotatably connected between the root mounting drive assembly and the top mounting assembly; The lifting mechanism has a retracted state and a lifted state. When the lifting mechanism switches from the retracted state to the lifted state, the lifting beam assembly deforms under the drive of the root-mounted drive assembly, which drives the top-mounted assembly to move the sun-oriented mechanism away from the satellite body to the target position.

2. The drive mechanism for the solar array as described in claim 1, characterized in that, The lifting beam assembly includes a first lifting beam assembly and a second lifting beam assembly arranged symmetrically. The first lifting beam assembly and the second lifting beam assembly each include a lower lifting beam and an upper lifting beam. The lower end of the lower lifting beam is fixedly connected to the root mounting drive assembly, the upper end of the lower lifting beam is rotatably connected to the lower end of the upper lifting beam, and the upper end of the upper lifting beam is rotatably connected to the top mounting assembly. The two sets of lower lifting beams and upper lifting beams, together with the root mounting drive assembly and the top mounting assembly, form a six-bar linkage mechanism.

3. The drive mechanism for the solar array as described in claim 2, characterized in that, The root mounting drive assembly includes a root hinge mounted on the satellite body. The root hinge includes a root hinge base, a movable hinge rotatably connected to the root hinge base, and a drive member for providing driving force to the movable hinge. The movable hinge is fixedly connected to the lower end of the lower lifting beam. When the lifting mechanism switches from the retracted state to the lifting state, the movable hinge rotates under the drive of the drive member. When the movable hinge rotates to its position, the solar orientation mechanism moves to the target position.

4. The drive mechanism for the solar array as described in claim 3, characterized in that, When the lifting mechanism is in the retracted state, the two lower lifting beams are distributed on both sides of the root hinge chassis, and are arranged sequentially along the first direction with the root hinge chassis; the two upper lifting beams are distributed on both sides of the top mounting assembly, and are arranged sequentially along the first direction with the top mounting assembly.

5. The drive mechanism for the solar array as described in claim 4, characterized in that, The top mounting assembly includes an upper tray, and in the first direction, the sum of the dimensions of the two lower lifting beams and the root hinge chassis is equal to the sum of the dimensions of the two upper lifting beams and the upper tray.

6. The drive mechanism for the solar array as described in claim 4, characterized in that, The rotation axis of the first shaft drive mechanism extends along the second direction, and the rotation axis of the second shaft drive mechanism extends along the third direction. The first direction, the second direction, and the third direction are perpendicular to each other.

7. The drive mechanism for the solar array as described in claim 3, characterized in that, The driving component includes a root hinge spring. Spring hubs are symmetrically arranged on the periphery of the root hinge chassis. The root hinge spring is mounted on the spring hubs. A mounting component is provided on the movable hinge. The mounting component is in contact with the root hinge spring. When the lifting mechanism is in the retracted state, the root hinge spring stores elastic potential energy. When the lifting mechanism switches from the retracted state to the lifting state, the elastic potential energy of the root hinge spring is converted into mechanical energy, which drives the movable hinge to rotate through the spring hubs and the mounting component.

8. The drive mechanism for the solar array as described in claim 7, characterized in that, The lifting mechanism also includes a linkage locking component, which is disposed between the spring hub, the movable hinge, and the root hinge chassis. The linkage locking component has an unlocked state and a locked state. When the lifting mechanism needs to switch from the retracted state to the lifting state, the elastic potential energy of the root hinge spring is converted into mechanical energy, driving the movable hinge to rotate. When the movable hinge rotates to the correct position, the linkage locking component switches from the unlocked state to the locked state, and the movable hinge is constrained and positioned by the root hinge chassis through the linkage locking component.

9. The drive mechanism for the solar array as described in claim 8, characterized in that, The linkage locking component includes: a linkage component, a reset component, and a locking component. The spring hub has a guide groove on the side facing the movable hinge, and an opening is formed at the end of the guide groove. One end of the linkage extends into the guide groove. The movable hinge has an open guide hole, the locking member is installed in the guide hole with clearance fit, the reset member is located between the other end of the guide hole and the locking member, and the side wall of the movable hinge has a long groove for the linkage member to pass through. The root hinge base is provided with a locking hole. Before the movable hinge rotates to the position, the spring hub, the linkage, and the movable hinge cooperate to constrain the locking member in the guide hole. After the movable hinge rotates to the position, one end of the linkage slides out of the guide groove through the opening, and the reset member pushes the end of the locking member out of the guide hole and into the locking hole to complete the locking.

10. The drive mechanism for the solar array as described in claim 1, characterized in that, The solar orientation mechanism is equipped with two sets of second axis drive mechanisms, which are symmetrically installed on the second axis bracket. Each set of second axis drive mechanisms drives a set of solar panels.

11. A satellite, characterized in that, The satellite includes a satellite body and solar panels. A drive mechanism for the solar panels according to any one of claims 1 to 10 is installed between the satellite body and the solar panels. The solar panels include two sets, which are symmetrically arranged about a predetermined base plane. The predetermined base plane is a plane that passes through the rotation axis of the first axis drive mechanism and is perpendicular to the rotation axis of the second axis drive mechanism.

12. The satellite as described in claim 11, characterized in that, The satellite also includes an unlocking device for keeping the lifting mechanism in a retracted state. When the unlocking device is released, the lifting mechanism can deform under the drive of the root-mounted drive assembly, causing the top-mounted assembly to move the sun-oriented mechanism away from the satellite body to the target position.

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