Roll-up Solar Deceleration System and Method

Abstract

This invention belongs to the field of space mechanism deployment technology, specifically relating to a roll-up solar array deceleration system and method, including a first housing and a second housing extending along an axis and coaxially fixed; the first housing houses a first shaft and a transmission structure, and the second housing houses a second shaft, a rotor component, and a stator component; the second housing is equipped with a damping adjustment device and a current speed measuring device. This invention, through the coordinated operation of the transmission structure and electromagnetic components, provides stable resistance at the output end of the solar array's rotating shaft, slowing down the deployment speed, significantly reducing the impact upon deployment, and directly ensuring the safety of the solar array's battery circuitry and the stability of related structural mechanisms.

Description

Technical Field

[0001] This invention belongs to the field of space mechanism deployment technology, specifically, it relates to a roll-up solar array deceleration system and method. Background Technology

[0002] As a core component for satellite energy acquisition, the reliability of the solar array's deployment process directly determines the security of the satellite's energy supply. In existing technologies, some solar array drive mechanisms (such as those using passive hinges or deformable thin-walled space structures as driving forces) lack effective deceleration devices, resulting in excessively fast solar array deployment speeds and significant impacts upon deployment, seriously threatening the integrity of the solar array's battery circuitry and the stability of related structural mechanisms.

[0003] To address the aforementioned problems, some retardation device designs have emerged in the existing technology, but they still have significant drawbacks:

[0004] Chinese patent CN104608941A discloses a magnetorheological hinge composite device: This device relies on the flow damping of magnetorheological fluid to achieve rotational deceleration and buffering. However, its function requires continuous power supply from the satellite to adjust the damping magnitude of the magnetorheological fluid. Moreover, the damping effect of the magnetorheological fluid is extremely sensitive to temperature, requiring an additional satellite thermal control system to maintain temperature stability, which significantly increases the consumption of onboard resources (electrical energy, space, weight).

[0005] Chinese patent CN108767421A discloses a space-deployable antenna support mechanism: The slow-release module of this mechanism consists of a servo motor, a planetary gear reducer, an upper cover, a winding hub, and a base. Although it can achieve slow deployment, it requires a complex on-board closed-loop control system to precisely control the servo motor. Furthermore, the motor is prone to snagging during winding, which affects the reliability of deployment. At the same time, the overall device structure is complex and has a high risk of failure.

[0006] To address the problems of high resource consumption, poor environmental adaptability, and complex and unreliable structure in existing deceleration devices, this invention proposes a rollable solar array deceleration system and method to meet the satellite's requirements for low resource consumption, high integration, strong environmental adaptability, and high reliability. Summary of the Invention

[0007] To address the shortcomings of existing technologies, the purpose of this invention is to provide a rollable solar array deceleration system and method, which solves the problems of high resource consumption, poor environmental adaptability, complex structure and low reliability of existing deceleration devices, achieves precise control of solar array deployment speed, reduces the impact of deployment, and ensures the safety of satellite solar arrays.

[0008] A spiral-type solar panel deceleration system according to the present invention includes:

[0009] A first housing extends along axis O and includes a first end and a second end;

[0010] The first shaft is rotatably mounted on the first housing and extends along axis O. One end of the first shaft is disposed inside the first housing, and the other end passes through the first end of the first housing and is connected to the rotating shaft of the coiled solar panel.

[0011] A transmission structure is disposed within the first housing, and the input end of the transmission structure is connected to the first shaft.

[0012] The second housing is fixed to the second end of the first housing and extends along axis O;

[0013] The second shaft is rotatably mounted in the second housing, and one end of the second shaft extends along axis O into the first housing and is connected to the output end of the transmission structure;

[0014] The rotor assembly is mounted on the second shaft.

[0015] The stator component is fixed inside the second housing;

[0016] A damping adjustment device is installed on the second housing. The damping adjustment device is connected to the coil of the stator component through a wire to form a closed circuit.

[0017] The transmission structure includes:

[0018] The first gear is installed at one end of the first shaft located inside the first housing;

[0019] The fourth gear is installed at one end of the second shaft located inside the first housing;

[0020] A first drive shaft is rotatably mounted inside a first housing. The axis of the first drive shaft is parallel to axis O. A second gear and a first drive gear are provided on the first drive shaft, and the second gear meshes with the first gear.

[0021] The second drive shaft is rotatably mounted in the first housing. The axis of the second drive shaft is parallel to the axis O. The second drive shaft is provided with a third gear that meshes with the fourth gear and a second drive gear that meshes with the first drive gear.

[0022] The second transmission gear is configured to move along the axis of the second transmission shaft;

[0023] A third transmission gear is mounted on a first transmission shaft. The third transmission gear is configured to mesh with the second transmission gear, and the meshing ratios of the first and second transmission gears and the third transmission gear and the second transmission gear are different.

[0024] Furthermore, the damping adjustment device is a sliding rheostat.

[0025] Furthermore, the current measuring device is a galvanometer connected in series in the closed circuit.

[0026] Furthermore, it also includes an adapter block fixed to the first end of the first housing.

[0027] Furthermore, the rotor component is made of cobalt permanent magnet.

[0028] Based on the aforementioned spiral-wound solar wing deceleration system, this application also provides a spiral-wound solar wing deceleration method, the specific steps of which are as follows:

[0029] Step S1, Parameter Calculation: Based on the design parameters of the roll-up solar array and the characteristics of the deceleration system, calculate the damping force required for the solar array to deploy;

[0030] Step S2, System Debugging: Based on the calculated damping force, determine the target transmission ratio of the transmission structure and the target resistance value of the damping adjustment device, and debug the deceleration system to the target parameter state.

[0031] Step S3, System Installation: Connect the debugged retardation system to the solar array via the adapter block at the first end of the first housing, ensuring a reliable connection between the first shaft and the solar array shaft;

[0032] Step S4, Power Transmission and Electromagnetic Effect: The solar array unfolds and drives the first shaft to rotate. The transmission structure transmits power to the second shaft, driving the rotor component to rotate, and in conjunction with the stator component, generates an electromagnetic effect.

[0033] Step S5, Damping Force Adjustment: Adjust the resistance value through the damping adjustment device and / or adjust the transmission ratio of the transmission structure to adjust the damping force generated by the electromagnetic action;

[0034] Step S6, Deployment Speed ​​Measurement and Adjustment: Start the solar wing deployment program, measure the closed circuit current through the current speed measuring device and calculate the actual rotation speed, adjust the damping or transmission ratio according to the rotation speed until the solar wing is stably deployed at the target rotation speed, thereby achieving deceleration and reducing the impact of deployment.

[0035] Compared with the prior art, the present invention has the following beneficial effects:

[0036] 1. This invention, through the coordinated operation of the transmission structure and electromagnetic components, provides stable resistance at the output end of the solar wing shaft, slows down the deployment speed, significantly reduces the impact upon arrival, and directly ensures the safety of the solar wing battery circuit and the stability of related structural mechanisms.

[0037] 2. This invention requires satellite power only for current velocity measurement, while the rest of the core devices are passive mechanisms. It does not rely on magnetorheological fluid or require an additional thermal control system, which significantly reduces energy, space and weight consumption and is compatible with satellite resource constraints.

[0038] 3. This invention eliminates easily faulty components such as servo motors and winding hubs, eliminates the need for complex on-board closed-loop control, avoids the risk of winding hooks, and features a simple and reliable overall structure, significantly reducing the probability of failure and improving the reliability of solar array deployment. Attached Figure Description

[0039] 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:

[0040] Figure 1 This is a cross-sectional view of the deceleration system of the present invention;

[0041] Figure 2 This is a cross-sectional view of the transmission structure of the present invention;

[0042] Figure 3 This is a perspective view of the deceleration system of the present invention;

[0043] Figure 4 This is a schematic diagram of the structure of the buffer system and solar panel assembly of the present invention.

[0044] The following are the labeling elements in the figure:

[0045] 100, First housing; 100a, First end; 100b, Second end; 101, First shaft;

[0046] 200. Transmission structure; 201. First transmission shaft; 202. Second transmission shaft; 203. First gear; 204. Second gear; 205. Third gear; 206. Fourth gear; 207. First transmission gear; 208. Second transmission gear; 209. Third transmission gear;

[0047] 300. Second housing; 301. Second shaft;

[0048] 400. Stator assembly; 401. Rotor assembly;

[0049] 500. Damping adjustment device; 501. Current speed measuring device; 502. Adapter block. Detailed Implementation

[0050] 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.

[0051] This invention discloses a rollable solar fin deceleration system, including an electromagnetic component and an acceleration component, which are coaxially fixed by a housing.

[0052] The acceleration component body includes a first housing 100, a transmission structure 200, and a first shaft 101. The first housing 100 extends along the axis O and has a hollow cylindrical structure. The first housing 100 includes a first end 100a and a second end 100b in the axial direction. The first housing 100 defines an installation space for accommodating the transmission structure 200.

[0053] The first shaft 101 is rotatably installed inside the first housing 100 and extends along the axis 0. One end of the first shaft 101 is located inside the first housing 100, and the other end passes through the first end 100a of the first housing 100 and is connected to the rotating shaft of the coiled solar wing. The first shaft 101 can rotate synchronously with the rotating shaft of the coiled solar wing.

[0054] In some examples, the inner wall of the first end 100a of the first housing 100 is provided with a bearing at the insertion position of the first shaft 101 to realize the rotational connection between the first shaft 101 and the first housing 100.

[0055] The transmission structure 200 is disposed inside the first housing 100. The input end of the transmission structure 200 is connected to one end of the first shaft 101 located inside the first housing 100. The output shaft of the transmission structure 200 is connected to the second shaft 301 to realize power transmission between the first shaft and the second shaft.

[0056] In some embodiments, the transmission ratio of the transmission structure 200 is less than 1, and the transmission structure 200 is configured as an acceleration structure to increase the rotational speed of the subsequent second shaft 301, thereby improving the deceleration effect; in some examples, the transmission structure 200 is a gearbox structure, that is, the transmission ratio of the transmission structure 200 is adjustable, in order to cooperate with the subsequent damping adjustment device 500 to achieve different deceleration effects.

[0057] The transmission structure 200 includes a first transmission shaft 201 and a second transmission shaft 202; both the first transmission shaft 201 and the second transmission shaft 202 are rotatably mounted in the first housing 100, and the axes of the first transmission shaft 201 and the second transmission shaft 202 are parallel to the axis of the first shaft body 101.

[0058] A first gear 203 is mounted on one end of the first shaft 101 located inside the first housing 100, and a second gear 204 that meshes with the first gear 203 is arranged on the first drive shaft 201. Power transmission between the first shaft 101 and the first drive shaft 201 is realized through the meshing action of the first gear 203 and the second gear 204.

[0059] A fourth gear 206 is mounted on one end of the second shaft 301 located inside the first housing 100, and a third gear 205 that meshes with the fourth gear 206 is mounted on the second drive shaft 202. Power transmission between the second drive shaft 202 and the second shaft 301 is achieved through the meshing of the third gear 205 and the fourth gear 206.

[0060] A first transmission gear 207 is provided on the first transmission shaft 201, and a second transmission gear 208 is provided on the second transmission shaft 202, which meshes with the first transmission gear 207. Through the meshing action of the first transmission gear 207 and the second transmission gear 208, the power transmission between the first transmission shaft 201 and the second transmission shaft 202 is realized.

[0061] In some embodiments, the second transmission gear 208 is configured to slide along the axis of the second transmission shaft 202; the transmission structure 200 further includes a third transmission gear 209 mounted on the first transmission shaft 201, the third transmission gear 209 being able to mesh with the second transmission gear 208, and the meshing ratios of the first transmission gear 207 and the second transmission gear 208, and the meshing ratios of the third transmission gear 209 and the second transmission gear 208 being different.

[0062] It should be noted that the first transmission gear (207), the second transmission gear (208), and the third transmission gear (209) are all spur gears; a guide sliding structure is provided between the second transmission shaft (202) and the second transmission gear (208). The guide sliding structure consists of threads and mating pins between the second transmission shaft (202) and the second transmission gear (208), allowing the second transmission gear (208) to slide along the axial direction of the second transmission shaft (202) and selectively form a meshing connection with the first transmission gear (207) or the third transmission gear (209). The second transmission gear (208) rotates relative to the second transmission shaft (202) by operating an auxiliary clamp, thereby moving the second transmission shaft (202) along its axis. When it moves to the meshing position of the first transmission gear (207) or the third transmission gear (209), the second transmission shaft (202) and the second transmission gear (208) are fixed with pins, so that the movement of the second transmission shaft (202) and the second transmission gear (208) is consistent and there is no relative movement. The torque of the first transmission gear (207) or the third transmission gear (209) is transmitted to the third gear 205. The switching of the meshing relationship is achieved through the above-mentioned sliding adjustment. Since the transmission ratio of different meshing combinations is different, the transmission ratio of the transmission structure (200) is adjusted.

[0063] The main body of the electromagnetic component includes a second housing 300, a stator component 400, a rotor component 401, and a second shaft 301; the second housing 300 extends along the axis O and has a hollow cylindrical structure; the second shaft 301 is rotatably mounted inside the second housing 300 and extends along the axis O.

[0064] In some examples, a bearing is arranged at the connection position of the second housing 300 and the second shaft 301 to realize the rotational connection between the second shaft 301 and the second housing 300.

[0065] One end of the second shaft 301 extends into the first housing 100 and is connected to the output end of the transmission structure 200. Power transmission between the first shaft 101 and the second shaft 301 is achieved through the transmission structure 200, at which time the second shaft 301 can rotate with the rotation of the spiral solar array shaft.

[0066] The electromagnetic assembly also includes a rotor component 401 mounted on the second shaft 301 and a stator component 400 mounted in the second housing 300; the rotor component 401 is made of cobalt permanent magnet and has 68 teeth with N and S poles arranged alternately. The rotor component 401 is accelerated by a multi-stage gear transmission through the transmission structure 200 to increase the induced electromotive force generated by the electromagnetic rotor assembly.

[0067] The stator component 400 is fixed to the second housing 300 by adhesive bonding and uses a DT4 frame. The frame and the rotor part are engraved with 68 teeth, and a single-phase winding is wound in the frame.

[0068] The deceleration system also includes a damping adjustment device 500, which is fixed to the outer wall of the second housing 300 and connected to the coil connection of the stator component 400 via wires to form a closed circuit.

[0069] In some examples, the damping adjustment device 500 is a sliding rheostat. The sliding rheostat is connected in series with the coil of the stator component 400 to form a closed circuit. By adjusting the total resistance of the sliding rheostat, the internal resistance of the circuit loop can be changed, thereby changing the current in the closed loop and thus changing the damping torque of the system. The damping force F provided by the damping adjustment device 500 is calculated using the following formula:

[0070] F=B·w;

[0071] B=k 2 / (R+r);

[0072] Where w is the rotational speed of the solar array, B is the damping coefficient, k is the back electromotive force constant, R is the resistance of the sliding rheostat, and r is the internal resistance of the circuit loop.

[0073] The deceleration system also includes a current speed measuring device 501 fixed to the outer wall of the second housing 300. The current speed measuring device 501 is a galvanometer connected in series in the closed-loop circuit to obtain the current data of the closed circuit. Combined with the circuit resistance and the back electromotive force constant, the deployment speed of the roll-up solar array can be calculated. The calculation formula for the solar array deployment speed w obtained by measuring and calculating through the current speed measuring device 501 is as follows:

[0074] w = I·(R+r) / k;

[0075] Where I is the current in the closed loop.

[0076] The deceleration system also includes an adapter block 502, which is fixed to one end of the axis of the first housing 100 and is used to connect the deceleration system and the rollable solar array. By transferring part of the energy of the rollable solar array deployment to the electromagnetic deceleration system and converting it into heat energy release of the electromagnetic deceleration system, the rollable solar array deployment deceleration is achieved.

[0077] The present invention also provides a method for decelerating a coiled solar array, which achieves deceleration during solar array deployment through the above-mentioned coiled solar array deceleration system. The specific steps are as follows:

[0078] Step S1, Parameter Calculation: Based on the design parameters such as the deployment inertia of the roll-up solar wing and the target deployment speed, combined with the back electromotive force constant of the deceleration system and the inherent internal resistance of the circuit, calculate the damping force required during the deployment of the roll-up solar wing.

[0079] Step S2, System Debugging: Based on the damping force calculated in step S1, determine the target transmission ratio of the transmission structure 200 and the target resistance value of the damping adjustment device 500 in the deceleration system. By adjusting the axial position of the second transmission gear 208 in the transmission structure 200 to switch the meshing relationship and adjusting the resistance value of the damping adjustment device 500, the deceleration system is debugged to the target parameter state.

[0080] Step S3, System Installation: Through the adapter block 502 at the first end 100a of the first housing 100 of the retardation system, the retardation system that has been debugged in step S2 is fixedly connected to the roll-up solar panel, so that one end of the first shaft 101 that protrudes from the first housing 100 is coaxially fixed with the rotating shaft of the roll-up solar panel, ensuring that the rotating shaft of the roll-up solar panel can drive the first shaft 101 to rotate synchronously when it is unfolded.

[0081] Step S4, Power Transmission and Electromagnetic Effect Generation: When the spiral solar panel unfolds and drives the first shaft 101 to rotate, the power of the first shaft 101 is transmitted to the second shaft 301 through the transmission structure 200 in the first housing 100, driving the second shaft 301 and the rotor component 401 mounted thereon to rotate, so that the rotor component 401 cooperates with the stator component 400 fixed in the second housing 300 to generate an electromagnetic effect.

[0082] Step S5, Damping Force Adjustment: The resistance value of the damping adjustment device 500 installed on the second housing 300 is adjusted to change the total resistance of the closed circuit formed by the damping adjustment device 500 and the stator component 400 coil, thereby adjusting the circuit current and the damping force generated by electromagnetic action; and / or, the rotational speed of the second shaft 301 and the rotor component 401 is changed by adjusting the transmission ratio of the transmission structure 200, thereby adjusting the damping force generated by electromagnetic action;

[0083] Step S6, Deployment Speed ​​Measurement and Feedback Adjustment: Start the roll-up solar wing deployment program, measure the current of the closed circuit in real time through the current speed measuring device 501 installed on the second housing 300, and calculate the actual deployment speed of the solar wing by combining the total circuit resistance and the back electromotive force constant.

[0084] If the actual deployment speed is greater than the target deployment speed, reduce the resistance of the damping adjustment device 500 to increase the damping torque, or adjust the transmission structure 200 to a smaller transmission ratio; if the actual deployment speed is less than the target deployment speed, increase the resistance of the damping adjustment device 500 to decrease the damping torque, or adjust the transmission structure 200 to a larger transmission ratio, until the solar array deploys stably at the target speed, thereby reducing the deceleration during the deployment process of the roll-up solar array and reducing the impact when it is deployed in place.

[0085] 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.

[0086] 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 roll-up solar panel deceleration system, characterized in that, include: A first housing (100) extends along axis O and includes a first end (100a) and a second end (100b). The first shaft (101) is rotatably mounted on the first housing (100) and extends along the axis O. One end of the first shaft (101) is disposed inside the first housing (100), and the other end passes through the first end (100a) of the first housing (100) and is connected to the rotating shaft of the coiled solar panel. A transmission structure (200) is disposed inside the first housing (100), and the input end of the transmission structure (200) is connected to the first shaft (101), and the transmission ratio of the transmission structure (200) is less than 1; The second housing (300) is fixed to the second end (100b) of the first housing (100) and extends along axis O; The second shaft (301) is rotatably mounted in the second housing (300), and one end of the second shaft (301) extends along axis O into the first housing (100) and is connected to the output end of the transmission structure (200); The rotor component (401) is mounted on the second shaft (301); The stator component (400) is fixed inside the second housing (300); A damping adjustment device (500) is installed on the second housing (300), and the damping adjustment device (500) is connected to the coil of the stator component (400) by a wire to form a closed circuit; A current speed measuring device (501) is mounted on the second housing (300), and the current speed measuring device (501) is configured to acquire the current data of the closed circuit; The transmission structure (200) includes: The first gear (203) is installed at one end of the first shaft (101) located inside the first housing (100); The fourth gear (206) is installed at one end of the second shaft (301) located inside the first housing (100); The first drive shaft (201) is rotatably mounted in the first housing (100). The axis of the first drive shaft (201) is parallel to the axis O. The first drive shaft (201) is provided with a second gear (204) and a first drive gear (207). The second gear (204) meshes with the first gear (203). The second drive shaft (202) is rotatably mounted in the first housing (100). The axis of the second drive shaft (202) is parallel to the axis O. The second drive shaft (202) is provided with a third gear (205) that meshes with the fourth gear (206) and a second drive gear (208) that meshes with the first drive gear (207). The second transmission gear (208) is configured to move along the axis of the second transmission shaft (202); The third transmission gear (209) is mounted on the first transmission shaft (201). The third transmission gear (209) is configured to mesh with the second transmission gear (208), and the meshing ratio of the first transmission gear (207) and the second transmission gear (208) is different from that of the third transmission gear (209) and the second transmission gear (208).

2. The retractable solar array system according to claim 1, characterized in that: The damping adjustment device (500) is a sliding rheostat.

3. The retractable solar array system according to claim 1, characterized in that: The current measuring device (501) is a galvanometer connected in series in the closed circuit.

4. The retractable solar array system according to claim 1, characterized in that, It also includes a transition block (502) fixed to the first end (100a) of the first housing (100).

5. The retractable solar array system according to claim 1, characterized in that, The rotor component (401) is made of cobalt permanent magnet.

6. A method for slowing down a wound solar array, characterized in that, The specific steps of using the coiled solar panel deceleration system according to any one of claims 1 to 5 are as follows: Step S1, Parameter Calculation: Based on the design parameters of the roll-up solar array and the characteristics of the deceleration system, calculate the damping force required for the solar array to deploy; Step S2, System Debugging: Based on the calculated damping force, determine the target transmission ratio of the transmission structure (200) and the target resistance value of the damping adjustment device (500), and debug the deceleration system to the target parameter state; Step S3, System Installation: The adjusted retardation system is fixedly connected to the solar array via the adapter block (502) at the first end (100a) of the first housing (100), ensuring a reliable connection between the first shaft (101) and the solar array shaft; Step S4, Power Transmission and Electromagnetic Effect: The solar array unfolds and drives the first shaft (101) to rotate. The transmission structure (200) transmits power to the second shaft (301), driving the rotor component (401) to rotate, and cooperating with the stator component (400) to generate an electromagnetic effect. Step S5, Damping force adjustment: Adjust the resistance value by adjusting the damping adjustment device (500) and / or adjust the transmission ratio of the transmission structure (200) to adjust the damping force generated by electromagnetic action; Step S6, Deployment Speed ​​Measurement and Adjustment: Start the solar wing deployment program, measure the closed circuit current through the current speed measuring device (501) and calculate the actual rotation speed, adjust the damping or transmission ratio according to the rotation speed until the solar wing is stably deployed at the target rotation speed, thereby achieving deceleration and reducing the impact of deployment.

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