Solar panel assembly and method of deploying the same

Abstract

This invention provides a solar panel assembly and its deployment method, belonging to the field of meteorological satellite technology. The solar panel assembly of this invention includes a solar panel composed of a left panel, a middle panel, and a right panel, a timing mechanism, a clamping and releasing mechanism, and a deployment locking mechanism. The timing mechanism is installed on the deployment shaft of the first deployed solar panel. Through the cooperation of a rotating pin and a semi-circular pin, the left and right panels are deployed step by step in a set sequence. The deployment locking mechanism drives a locking pin to slide along a guide slide and lock into a locking groove via a locking spring, triggering a microswitch to provide a feedback signal. After the clamping and releasing mechanism unlocks, the solar panel is deployed under the drive of the deployment locking mechanism. This invention achieves orderly deployment of the two panels through purely mechanical timing control, avoiding collisions and interference during the deployment process, and improving system reliability and safety.

Description

Technical Field

[0001] This invention belongs to the field of meteorological satellite technology, specifically relating to a solar panel assembly and its deployment method, and more particularly to a solar panel assembly controlled by a timing mechanism and its step-by-step deployment method. Background Technology

[0002] The deployment method of solar panels is also affected by factors such as the overall satellite attitude and configuration. When multiple solar panels are deployed in different directions using the same clamping and releasing mechanism, the deployment sequence of the solar panels needs to be controlled, otherwise it may lead to the risk of collision and snagging.

[0003] Currently, most solar panel deployment methods employ motor-driven sequence control, where a motor assembly is installed on the solar panel to drive its deployment. Since the solar panel is the satellite's sole energy source, installing motors on the external portion increases the risk to power supply safety. A few solar panels use a clamping and releasing mechanism to control the deployment sequence, but this method wastes the satellite's pyrotechnic resources. Both of these approaches increase the complexity of the on-orbit deployment process and reduce deployment safety. This invention utilizes a time-sequence mechanism-controlled step-by-step deployment method. This eliminates the need for individual power-consuming components like motors and pyrotechnics, increasing safety while still achieving step-by-step deployment; furthermore, it saves on development costs.

[0004] Currently, the relevant existing technologies include: Chinese patent document CN107954005A discloses a telescopic solar panel deployment mechanism and method. Specifically, the telescopic solar panel deployment mechanism includes a telescopic component, a solar panel, and a drive component. The telescopic component includes a base and multiple telescopic parts, which can extend and retract sequentially relative to the base. The drive component is located at the base and can drive the multiple telescopic parts to extend and retract relative to the base. The solar panel includes multiple support rods, one of which is connected to the base, and the remaining support rods are connected to the multiple telescopic parts one by one. When the multiple telescopic parts extend sequentially relative to the base, the multiple support rods separate sequentially to deploy the solar panel. This telescopic solar panel deployment mechanism can reduce the overall volume of the solar panel during satellite launch. After the satellite is launched into orbit, the drive component drives the multiple telescopic parts to extend sequentially relative to the base, thereby deploying the solar panel. The on-orbit deployment of the solar panel is mainly achieved through the telescopic component.

[0005] A Chinese patent document with publication number CN107933960A discloses a small solar panel deployment and locking mechanism. Specifically, the mechanism includes a deployment mechanism based on a torsion spring and nylon cable ties, and a spring stiffness locking mechanism. The deployment mechanism comprises a custom torsion spring, a torsion spring retainer, a torsion spring retainer cover, nylon cable ties, and a cable tie seat. The torsion spring retainer and retainer cover are mounted on the same side of the solar panel. Four sets of nylon cable ties, with eight pairs of holes, pass through the cable tie seat and the solar panel. The direction of the ties depends on the rotation axis position of the solar panel when it is retracted. The cable ties are only used to connect two solar panels. The spring stiffness locking mechanism includes a special spring and a spring clamping seat. The special spring is a sheet metal bent piece with a certain angled bend at one end. After the solar panel is deployed, the special spring blocks and limits its position along the thickness direction of the solar panel. The deployment and locking of the solar panel are mainly achieved through nylon cable ties.

[0006] Chinese patent document CN207809816U discloses a sliding solar panel deployment mechanism. Specifically, the mechanism includes: primary and secondary solar panel support frames, a drive assembly, and an elastic element. The drive assembly applies a driving force to the secondary solar panel support frame. When the drive assembly does not apply a driving force to the secondary solar panel support frame, the secondary solar panel support frame moves to a position relative to the primary solar panel support frame under the elastic action of the elastic element. With this sliding solar panel deployment mechanism, the solar panels deploy via a sliding structure after the satellite is launched into orbit.

[0007] Chinese patent document CN207819839U discloses a roll-up solar panel deployment mechanism. Specifically, the mechanism includes a drive chain, a winding assembly, and a driving assembly. One end of the drive chain is connected to the winding assembly, and the drive chain can be wound onto the winding assembly or extended outward from the winding assembly under the drive of the driving assembly. The drive chain includes mounting links, connecting links, and self-locking links, with the mounting links and connecting links alternately hinged. One end of the self-locking link is rotatably mounted on the mounting link, and the other end can connect to an adjacent mounting link under external force. This roll-up solar panel deployment mechanism allows the solar panels to be wound into a cylindrical shape before satellite launch, resulting in a small overall volume of the solar panel. After the satellite is launched and placed into orbit, the solar panels can be deployed to ensure power supply to the satellite, achieved through the drive chain.

[0008] A Chinese patent document with publication number CN204334449U discloses a space solar panel deployment mechanism, mainly composed of a driving component, a self-locking and damping component, an angle sensor, and auxiliary and connecting components. The driving component mainly includes a permanent magnet rotor, a stator ring, an electromagnet, a C-shaped magnetic core, and a coil; the self-locking and damping component is composed of a magnetically conductive spring; the angle sensor is a conductive plastic potentiometer; the auxiliary and connecting components mainly include a rotating shaft, a housing, connectors for connecting the solar panels, and end caps. This invention is based on the principle of electromagnetic-permanent magnet interaction, utilizing neodymium iron boron (NdFeB), a third-generation rare-earth permanent magnet material, as the main driving element; it primarily achieves solar panel deployment through the driving component and angle sensor.

[0009] A Chinese patent document with publication number CN106275515A discloses a satellite solar panel deployment mechanism that utilizes a solar panel deployment and locking method implemented by providing a torsion spring, a slide rail, and male and female hinges. Summary of the Invention

[0010] In view of the deficiencies in the prior art, the purpose of this invention is to provide a solar panel assembly and its deployment method.

[0011] The solar panel assembly provided by the present invention includes: a solar panel, the solar panel including a middle plate, a left plate located on one side of the middle plate and a right plate located on the other side of the middle plate; A clamping release mechanism is used to lock the solar panel in the retracted state or release it from the lock. An unfolding locking mechanism is used to drive and lock the left and right plates to unfold after the clamping release mechanism is released; A timing mechanism is mounted on the unfolding shaft of the left plate or the right plate; The middle plate remains fixed during the unfolding process, and the left plate unfolds in the opposite direction to the right plate. The timing mechanism is used to restrict the delayed deployment of another plate adjacent to its mounting plate, so as to achieve the step-by-step deployment of the left plate and the right plate.

[0012] Preferably, the timing mechanism includes a rotating pin and a semi-circular pin; The rotating pin is mounted on the unfolding shaft of the first unfolded plate and can rotate synchronously with the first unfolded plate. The semi-circular pin is set on the plate that unfolds later; During the initial unfolding phase, the end of the rotating pin presses against the semicircular pin to restrict the movement of the delayed unfolding plate; When the rotating pin rotates with the first unfolded plate to a set angle α, the rotating pin separates from the semicircular pin, releasing the restriction on the delayed unfolded plate.

[0013] Preferably, the rotating pin is fixedly connected to the female hinge to which the first unfolded plate is connected; The semi-circular pin is fixed to the free end edge of the delayed-deployment plate; The contact surfaces of the rotary pin and the semicircular pin are in line contact.

[0014] Preferably, the timing mechanism further includes positioning pins. The positioning pin is disposed on the middle plate and is used to limit the vibration displacement of the semi-circular pin when the sail is in the retracted state.

[0015] Preferably, the unfolding locking mechanism includes: a male hinge, a female hinge, a locking spring, a locking pin assembly, and a locking groove disposed on the female hinge; The locking spring drives the locking pin assembly to slide along the male hinge until the locking pin assembly is engaged in the locking groove to achieve unfolding and locking. The solar panel assembly also includes: a micro switch. When the locking pin assembly engages with the locking slot, it triggers the micro switch to generate an unfolded signal.

[0016] Preferably, the male hinge is provided with a guide slide. The locking pin of the locking pin assembly slides along the guide slide. The micro switch is a normally open switch. The locking pin presses against the micro switch contact to trigger the switch. The locking spring is a spiral spring.

[0017] Preferably, the clamping and releasing mechanism is provided with a clamping rod. One end of the clamping rod is fixed to the star, and the other end is fixed to the outermost solar panel in the retracted state; after unlocking, the clamping rod is cut off on the side closest to the star, becoming part of the outermost solar panel.

[0018] Preferably, the set angle α is a collision prevention safety angle, and the calculation includes the distance g between the left plate rotation axis A point and the right plate (6) rotation axis B point, the length n from the far end of the right plate to the rotation axis, the distance m from the pressure release mechanism to the left plate rotation axis, and the length h of the pressure rod, so as to avoid the plate body from hooking and colliding with the pressure rod during the unfolding process.

[0019] A method for deploying a solar panel assembly according to the present invention, characterized in that it includes: Step S1: Control the clamping release mechanism to unlock and release the locking constraint on the solar panels; Step S2: The locking spring drives the first unfolding plate to rotate first, and the rotating pin of the timing mechanism rotates synchronously with the first unfolding plate. The end pressing semi-circular pin restricts the movement of the lagging unfolding plate. Step S3: First, rotate the unfolding plate to the set angle α, and the rotating pin separates from the semi-circular pin, releasing the restriction on the lagging unfolding plate; Step S4: The left and right panels unfold synchronously until the locking pin assembly engages with the locking slot to complete the locking, triggering the micro switch to send an unfolding signal.

[0020] Preferably, when the solar panel is retracted, the positioning pin on the middle plate limits the semi-circular pin, suppressing the vibration of the semi-circular pin in the active launch section and preventing the semi-circular pin from repeatedly striking the rotating pin, which could damage the component.

[0021] Compared with the prior art, the present invention has the following beneficial effects: 1. The present invention, by setting a timing mechanism including a rotating pin, a semi-circular pin and a positioning pin, enables the left plate and the right plate to unfold in sequence step by step, thereby avoiding collision and snagging between the two plates during the unfolding process. 2. This invention effectively prevents repeated impacts and fatigue damage caused by plate vibration in the active launch phase by setting a positioning pin on the middle plate to limit the vibration of the semi-circular pin. 3. The present invention achieves automatic locking and status feedback when the locking pin is fully deployed by the locking spring in the deployment locking mechanism and the locking groove is engaged with the locking groove, combined with the trigger signal of the micro switch.

[0022] 4. This invention utilizes a timing mechanism for purely mechanical control and angle adjustment. The optimized design eliminates the need for motors or pyrotechnics, improving system reliability and safety while ensuring deployment timing. Attached Figure Description

[0023] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram of the solar panel in its retracted state according to the present invention; Figure 2 for Figure 1 The enlarged view at point A in the middle is a partial view of the unfolding axis of the left solar panel of the present invention, which is in the shape of a folded-up solar panel. Figure 3 This is a schematic diagram illustrating the working principle of the timing mechanism during solar panel deployment in this invention. Figure 4 This is a simplified diagram illustrating the deployment process and angle of the solar panel of the present invention. Figure 5 This is a simulation diagram of the solar panel deployment process of the present invention.

[0024] The diagram shows: Detailed Implementation

[0025] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0026] like Figure 1 As shown, this embodiment of the invention provides a solar panel assembly, including: a solar panel, a timing mechanism, a male hinge 10, a female hinge 12, a locking spring 9, a micro switch 13, a pressure release mechanism 14, and an deployment locking mechanism. The aforementioned solar panel comprises three solar panels: a left panel 4, a middle panel 5, and a right panel 6. The middle panel 5 remains stationary during the deployment of the solar panel assembly. The left panel 4 and the right panel 6 deploy in opposite directions under the drive of the deployment locking mechanism. To ensure that the left panel 4 and the right panel 6 do not collide during deployment, they must deploy sequentially. The aforementioned timing mechanism is installed on the deployment axis of the first deployed solar panel to restrict the other solar panel from deploying later. In a more specific embodiment, when the solar panel is in its retracted state, the left panel 4 is folded to the outermost side. Therefore, the left panel 4 is deployed first, followed by the right panel 6. Thus, the deployment locking mechanism is installed on the deployment axis of the left panel 4 to restrict the right panel 6 from deploying later. When the clamping and releasing mechanism 14 is locked, the solar panel is in a clamped and retracted state. When the clamping and releasing mechanism 14 is unlocked, the solar panel is in a released state. At this time, the solar panel deploys under the drive of the locking spring 9 within the deployment locking mechanism.

[0027] Furthermore, after the clamping release mechanism 14 is unlocked, the left plate 4 unfolds under the action of the unfolding locking mechanism, while the right plate 6 remains in its original position under the constraint of the timing mechanism. Specifically, the timing mechanism includes a rotating pin 1, a semi-circular pin 2, and a positioning pin 3. When the left plate 4 unfolds, the rotating pin 1 rotates synchronously with the left plate 4. The semi-circular pin 2 is fixed on the right plate 6 and serves as a limit. According to the design requirements, when different lengths of rotating pin 1 are selected, the rotating pin 1 unfolds to a set angle α and then separates from the semi-circular pin 2. At this time, the semi-circular pin 2 on the right plate 6 is only unfolded to a relatively small angle Δ due to the restriction of the rotating pin 1, and will not interfere with the left plate 4. After that, the restriction on the right plate 6 is released, and under the action of the unfolding locking mechanism, the left plate 4 and the right plate 6 unfold and lock in place one after another. The aforementioned rotating pin 1 is fixed to the female hinge 12, and the semi-circular pin 2 is fixed to the right plate 6. When the left plate 4 is unfolded under the action of the unfolding locking mechanism, the rotating pin 1 will rotate synchronously with the unfolding movement of the left plate 4; the end of the rotating pin 1 presses against the semi-circular pin 2, restricting the unfolding of the right plate 6; when the rotating pin 1 unfolds to the set angle... After separating from the semicircular pin 2, the semicircular pin 2 on the right plate 6 is restricted by the rotating pin 1 and can only unfold to a relatively small angle. Afterwards, the restriction on the right plate 6 is released, allowing it to unfold. Driven by the unfolding locking mechanism, the left plate 4 and right plate 6 unfold and lock in place sequentially. It is important to note that after the restriction on the right plate 6 is released, the left plate 4 and right plate 6 unfold at the same angular velocity. To ensure that the left plate 4 and right plate 6 do not collide or hook during the unfolding process, it is essential to ensure that the right plate 6 does not collide with the body of the left plate 4, nor with the clamping rod 15 of the clamping release mechanism 14. In a more specific embodiment, to prevent the clamping rod 15 of the clamping release mechanism 14 from hooking, the length of the clamping rod 15 is also considered as a factor in calculating the safety angle; that is, the length h is also one of the conditions for calculating the safety angle. Among these, based on the characteristics of the timing mechanism, the small angle of unfolding of the restricted plate... Generally less than The angle calculation method is as follows: Measure the distance g between point A on the left plate 4 and point B on the right plate 6; obtain the length n from the far end of the right plate 6 to its rotation axis; obtain the distance m from the clamping release mechanism 14 to the rotation axis of the left plate 4 and the length h of the clamping rod 15; calculate the distance s from the rotation axis to the free end of the clamping rod 15; calculate... Angle and Angle ; Need to be greater than and The largest of the; the specific steps are: Step S1: Simplify the solar panel model diagram as shown in the figure. Measure the distance between point A, the rotation axis of the left panel 4, and point B, the rotation axis of the right panel 6, as g meters. Step S2: Based on the design of the solar panel, the length from the far end of the right panel 6 to the rotation axis is n meters, and the unfolded curve of the right panel 6 is drawn, and an arc is drawn with the rotation axis of the right panel 6 as the center and the length n meters as the radius. Step S3: Based on the design, obtain the distance m (meters) from the clamping release mechanism 14 to the rotation axis of the left plate 4, and the length h (meters) of the clamping rod 15 remaining on the left plate 4 after the clamping release mechanism 14 is unlocked, and draw them respectively: a. The point where the left plate 4 collides with the unfolding trajectory of the right plate 6 during the unfolding process is the point of collision C, which is the point of tangency between the left plate 4 rotation axis and the unfolding arc of the right plate 6. b. Draw the position where the clamping rod 15 collides with the right plate 6 during its unfolding process. Using the rotation axis of the left plate 4 as the center and the distance from the rotation axis to the free end of the clamping rod 15 as the radius, draw an arc. The intersection of this arc and the unfolding curve of the right plate 6 is the collision point D. Since the clamping rod remaining on the left plate 4 is basically perpendicular to the left plate 4, s can be calculated using the Pythagorean theorem. ; Step S4: Connect the rotation axis A of the left plate 4 to the collision points C and D respectively, and calculate... Angle , The angle is ; Greater than , The largest one in the middle can ensure that the unfolding process of the left plate 4 and the right plate 6 will not interfere with each other.

[0028] Furthermore, the aforementioned positioning pin 3 is located on the middle plate 5. Since the semicircular pin 2 is located at the free end of the right plate 6, it is used to limit the vibration of the semicircular pin 2 during the active launch phase. That is, it is used to avoid the semicircular pin 2 repeatedly striking the rotating pin 1 due to asynchronous vibration between the right plate 6 and the left plate 4 during the active launch phase, which could lead to fatigue damage. More specifically, the semicircular pin 2 itself is fixed to the right plate 6 with a certain small gap. Even if it is struck during the active phase, it will not damage the battery panel. The impact only occurs between the rotating pin 1, the semicircular pin 2, and the positioning pin 3. Moreover, the product strength has been tested and guaranteed, and it will not be damaged by small vibrations. It can still work normally after entering the orbit.

[0029] Furthermore, the aforementioned clamping and releasing mechanism 14 clamps the solar panels by fixing one end of its clamping rod 15 to the star body and the other end to the outermost solar panel. When the clamping rod 15 is locked, it becomes an integral part of the outermost solar panel away from the star body. When released, it is cut off on the side closer to the star body, and the clamping rod 15 becomes part of the outer solar panel. In order to ensure the smooth deployment of the solar array, it is necessary to ensure that the clamping rod 15 on the outermost solar panel does not collide or hook with other panels. The outermost solar panel is the outermost solar panel in the retracted state of the solar panel, that is, the first solar panel to be deployed. In the more specific embodiment described above, it is the left panel 4.

[0030] Furthermore, the aforementioned unfolding and locking mechanism includes: a locking pin assembly 7, a locking groove 8, and a locking spring 9. During unfolding, the locking pin of the locking pin assembly 7 slides along the guide slide 11 on the male hinge 10 under the action of the locking spring 9 and eventually enters the locking groove 8 located on the female hinge 12. The locking pin is locked in the locking groove 8 under the action of the locking spring 9, thereby triggering the micro switch 13 to give an unfolding-in signal. Specifically, the aforementioned micro switch 13 is a normally closed switch installed at the unfolding and locking mechanism. When the locking pin of the locking pin assembly 7 is locked, it presses against the contact of the micro switch 13 installed at the unfolding and locking mechanism. After the micro switch 13 is closed, it can trigger and provide feedback a unfolding-in signal. Specifically, the aforementioned locking spring 9 is an unfolding spring, or a spiral spring, which has the following properties: it can achieve an unfolding force in a compressed state; when one end is fixed and compressed, the other end can rotate around the axis under the drive of the spring force, thereby achieving a drive that is different from motor drive.

[0031] Next, the invention will be further described with reference to a more specific embodiment. In this embodiment, to prevent collisions during the unfolding of the left and right panels 6, a timing mechanism is installed at the unfolding locking mechanism. This timing mechanism consists of a rotating pin 1, a semi-circular pin 2, and a positioning pin 3. Specifically, the contact surfaces of the rotating pin 1 and the semi-circular pin 2 are in line contact, such as... Figure 2The shape shown is an axial view of the aforementioned timing mechanism assembly. The middle plate remains stationary during unfolding, while the left plate 4 and right plate 6 unfold in opposite directions under the drive of their respective unfolding locking mechanisms. To ensure that the left plate 4 and right plate 6 do not collide during unfolding, they must unfold sequentially. According to this invention, the left plate 4 is folded to the outermost edge, therefore it can be configured to unfold first, followed by the right plate 6. For similar configurations, the outermost folded battery panel can be unfolded first. Therefore, a timing mechanism is set at the unfolding axis of the left plate 4 to restrict the right plate 6 from unfolding later. The unfolding locking mechanism consists of a locking pin assembly 7, a locking groove 8, and a locking spring 9. During unfolding, the locking pin slides along the guide slide 11 on the male hinge 10 under the action of the locking spring 9 and eventually enters the locking groove 8 located on the female hinge 12. The locking pin is locked in the locking groove 8 under the action of the locking spring 9, thereby triggering the microswitch 13 installed at the unfolding locking mechanism, thus providing an unfolding completion signal. A normally closed switch installed at the unfolding locking mechanism presses against the contacts of microswitch 13 when the locking pin is locked. When microswitch 13 closes, it triggers and provides feedback on the unfolded position. When the pressing release mechanism 14 unlocks, the left plate 4 unfolds under the action of the unfolding locking mechanism, while the right plate 6 remains essentially in its original position under the constraint of the timing control mechanism. Rotary pin 1 is fixed to the female hinge 12, and semicircular pin 2 is fixed to the right plate 6. When the left plate 4 unfolds, rotary pin 1 rotates synchronously; the end of rotary pin 1 presses against semicircular pin 2, restricting the unfolding of the right plate 6. When rotary pin 1 unfolds to a set angle α, it separates from semicircular pin 2. At this point, semicircular pin 2 on the right plate 6, restricted by rotary pin 1, only unfolds to a small angle and does not interfere with the left plate 4. Afterward, the restriction on the right plate 6 is released, and under the action of the unfolding locking mechanism, the left plate 4 and right plate 6 unfold and lock into place sequentially. Positioning pin 3 is installed on the middle plate. Since semicircular pin 2 is installed on the free end of right plate 6, to prevent fatigue damage caused by repeated striking of rotating pin 1 by semicircular pin 2 due to asynchronous vibration between right plate 6 and left plate 4 during the active launch phase, a positioning pin 3 is installed on the middle plate to limit the vibration of semicircular pin 2. When the clamping release mechanism 14 is locked, the solar panel is in a clamped and retracted state; when the clamping release mechanism 14 is unlocked, the solar panel is in a released state. At this time, the solar panel unfolds under the drive of locking spring 9 in the unfolding locking mechanism. The clamping release mechanism 14 achieves the clamping of the solar panel by fixing one end of clamping rod 15 to the satellite and the other end to the outermost solar panel. When the clamping rod 15 is locked, it becomes integrated with the outermost solar panel; when released, it is cut off near the satellite, and the clamping rod 15 becomes part of the outer plate. To ensure smooth deployment of the solar array, it is necessary to ensure that the clamping rod 15 on the outer plate does not collide or hook with other plates. Figure 3As shown, clamping rod 15 is used to fix several solar panels to the surface of the celestial body before the solar panels are deployed. After entering orbit, the clamping rod 15 is unlocked to release the restriction. The solar panels are then deployed under the drive of locking springs 9 (worm springs) inside each hinge. The restriction release process is as follows: after the rotating pin 1 is deployed by an angle α, it separates from the semicircular pin 2; the rotating pin 1 rotates... After the angle is adjusted, the left plate 4 separates from the semicircular pin 2. That is, after the left plate 4 unfolds by an angle α, the restriction on the right plate 6 is released. Subsequently, driven by their respective unfolding locking mechanisms, the left plate 4 and right plate 6 unfold at the same angular velocity. To ensure that the left plate 4 and right plate 6 do not collide or hook during the unfolding process, it is necessary to ensure that the right plate 6 does not collide with the body of the left plate 4, nor with the clamping rod 15 of the clamping release mechanism 14. The value of angle α is calculated using the following steps: The first step is to simplify the solar panel model diagram and measure the distance between point A on the left panel 4 and point B on the right panel 6 as g meters. After simplification, the distance g between points A and B is measured to be 2 meters. The second step is to determine the length n from the far end of the right panel 6 to the rotation axis as 1.8 meters based on the design of the solar panel. Then, draw the unfolded curve of the right panel 6, that is, draw an arc with the rotation axis of the right panel 6 as the center and the length n, i.e., 1.8 meters, as the radius. The third step involves obtaining, based on the design, the distance m from the clamping release mechanism 14 to the rotation axis of the left plate 4 as 0.5 meters, and the length h of the clamping rod 15 remaining on the left plate 4 after the clamping release mechanism 14 is unlocked as 0.1 meters, and drawing them respectively: a. The point where the left plate 4 collides with the unfolding trajectory of the right plate 6 during the unfolding process is the point of collision C, which is the point of tangency between the left plate 4 rotation axis and the unfolding arc of the right plate 6. b. Draw the position where the clamping rod 15 collides with the right plate 6 during its unfolding process. Using the rotation axis of the left plate 4 as the center and the distance s from the rotation axis to the free end of the clamping rod 15 as the radius, draw an arc. The intersection of this arc and the unfolding curve of the right plate 6 is the collision point D. Since the clamping rod 15 remaining on the left plate 4 is basically perpendicular to the left plate 4, s can be calculated using the Pythagorean theorem. That is, s is approximately 0.5 meters; Fourth step, connect the rotation axis A of the left plate 4 to the collision points C and D respectively, and calculate as follows: Angle , The angle is ; A value greater than 64.2° will ensure that the left plate 4 and the right plate 6 do not interfere with each other during the unfolding process.

[0032] In summary, this invention addresses the shortcomings of existing step-by-step solar panel deployment designs by proposing a solar panel assembly and its deployment method. After the solar array's clamping release mechanism 14 is unlocked, the solar panels deploy under the drive of the deployment locking mechanism. The middle panel remains stationary during deployment, while the left panel 4 and right panel 6 deploy in opposite directions under the drive of their respective deployment locking mechanisms. Based on the folding method of the solar panels, the outermost panel deploys first. To avoid collisions during deployment, a timing control mechanism controls the deployment order of the left panel 4 and right panel 6. In this case, the left panel 4 is located at the outermost position when folded, meaning it deploys first. The timing mechanism is installed on the deployment axis of the left panel 4, restricting the right panel 6 from deploying later. The timing control mechanism consists of three parts: a rotating pin 1, a semi-circular pin 2, and a locking pin. Rotating pin 1 is fixed to the female hinge 12, and semi-circular pin 2 is fixed to the end of the right plate 6. When the left plate 4 is unfolded, rotating pin 1 rotates synchronously. The end of rotating pin 1 presses against semi-circular pin 2, restricting the unfolding of the right plate 6. When the left plate 4 unfolds to a set angle... After the restriction on the right plate 6 is lifted, the semicircular pin 2 on the right plate 6 is restricted by the rotating pin 1 and can only unfold to a relatively small angle. Subsequently, the left plate 4 and right plate 6 unfold together under the drive of their respective deployment and locking mechanisms until they are locked in place. Simultaneously, since the semicircular pin 2 is installed at the free end of the right plate 6, to prevent fatigue damage caused by the semicircular pin 2 repeatedly striking the rotating pin 1 due to asynchronous vibration between the right plate 6 and the left plate 4 during the active launch phase, a positioning pin 3 is installed on the middle plate to limit the vibration of the semicircular pin 2. This invention, using a single clamping and releasing mechanism 14, employs a timing mechanism to control the distributed deployment of the solar panels, reducing the number of unlocking operations of the clamping and releasing mechanism 14, lowering the complexity of the solar panel deployment-related commands in the flight procedure, and increasing the reliability of solar panel deployment. This invention does not use external motors or other deployment controls, but uses a timing mechanism to achieve step-by-step solar panel deployment; it eliminates the need for an internal unit to power the external deployment control unit, reducing the complexity of energy interaction between the satellite and the external environment, and increasing the reliability and safety of universal solar panel deployment.

[0033] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They 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. Therefore, they should not be construed as limitations on this application.

[0034] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A solar panel assembly, characterized in that, include: A solar panel, the solar panel comprising a center plate (5), a left plate (4) located on one side of the center plate (5) and a right plate (6) located on the other side of the center plate (5); The compression release mechanism (14) is used to lock the solar panel in the retracted state or release it from the lock; An unfolding locking mechanism is used to drive and lock the left plate (4) and the right plate (6) to unfold after the clamping release mechanism (14) is released from locking; The timing mechanism is installed on the unfolding shaft of the left plate (4) or the right plate (6); The middle plate (5) remains fixed during the unfolding process, and the left plate (4) unfolds in the opposite direction to the right plate (6). The timing mechanism is used to restrict the delayed deployment of another plate adjacent to its mounting plate, so as to achieve the step-by-step deployment of the left plate (4) and the right plate (6).

2. The solar panel assembly according to claim 1, characterized in that, The timing mechanism includes a rotating pin (1) and a semi-circular pin (2); The rotating pin (1) is set on the unfolding shaft of the first unfolded plate and can rotate synchronously with the first unfolded plate; The semicircular pin (2) is set on the plate that unfolds later; During the initial unfolding phase, the end of the rotating pin (1) is pressed against the semicircular pin (2) to restrict the movement of the plate during the delayed unfolding; When the rotating pin (1) rotates with the first unfolded plate to a set angle α, the rotating pin (1) separates from the semicircular pin (2), releasing the restriction on the delayed unfolded plate.

3. The solar panel assembly according to claim 2, characterized in that, The rotating pin (1) is fixedly connected to the female hinge (12) connected to the first unfolded plate; The semicircular pin (2) is fixed to the free end edge of the delayed-deployment plate; The contact surfaces of the rotating pin (1) and the semicircular pin (2) are in line contact.

4. The solar panel assembly according to claim 2 or 3, characterized in that, The timing mechanism also includes a positioning pin (3). The positioning pin (3) is disposed on the middle plate (5) and is used to limit the vibration displacement of the semicircular pin (2) when the sail is in the retracted state.

5. The solar panel assembly according to claim 1, characterized in that, The unfolding locking mechanism includes: a male hinge (10), a female hinge (12), a locking spring (9), a locking pin assembly (7), and a locking groove (8) disposed on the female hinge (12); The locking spring (9) drives the locking pin assembly (7) to slide along the male hinge (10) until the locking pin assembly (7) is engaged in the locking groove (8) to achieve unfolding and locking; The solar panel assembly also includes a micro switch (13). When the locking pin assembly (7) is engaged in the locking slot (8), the micro switch (13) is triggered to generate an unfolded signal.

6. The solar panel assembly according to claim 5, characterized in that, The male hinge (10) is provided with a guide slide (11). The locking pin of the locking pin assembly (7) slides along the guide slide (11); The micro switch (13) is a normally closed switch. The locking pin presses against the contact of the micro switch (13) to trigger the switch. The locking spring (9) is a spiral spring.

7. The solar panel assembly according to claim 1, characterized in that, The clamping release mechanism (14) is provided with a clamping rod (15). One end of the clamping rod (15) is fixed to the star, and the other end is fixed to the outermost solar panel in the retracted state; after unlocking, the clamping rod (15) is cut off on the side near the star and becomes part of the outermost solar panel.

8. The solar panel assembly according to claim 7, characterized in that, The set angle α is the anti-collision safety angle. When calculating, the distance g between the left plate (4) rotation axis point A and the right plate (6) rotation axis point B, the length n from the far end of the right plate (6) to the rotation axis, the distance m from the pressure release mechanism (14) to the left plate (4) rotation axis, and the length h of the pressure rod (15) are included to avoid the plate body from hooking and colliding with the pressure rod (15) during the unfolding process.

9. A method for deploying a solar panel assembly according to any one of claims 1 to 8, characterized in that, include: Step S1: Control the clamping release mechanism (14) to unlock and release the clamping constraint on the solar panel; Step S2: The locking spring (9) drives the first unfolding plate to rotate first, and the rotating pin (1) of the timing mechanism rotates synchronously with the first unfolding plate. The end pressing semi-circular pin (2) restricts the movement of the lagging unfolding plate. Step S3: First, rotate the unfolding plate to the set angle α, and the rotating pin (1) separates from the semi-circular pin (2) to release the restriction on the lagging unfolding plate; Step S4: The left plate (4) and the right plate (6) unfold synchronously until the locking pin assembly (7) is engaged in the locking slot (8) to complete the locking and trigger the micro switch (13) to send an unfolding signal.

10. The unfolding method according to claim 9, characterized in that, When the solar panel is retracted, the positioning pin (3) on the middle plate (5) limits the semicircular pin (2), suppresses the vibration of the semicircular pin (2) of the active launch section, and avoids the semicircular pin (2) from repeatedly hitting the rotating pin (1) and causing damage to the component.

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