Solar wing sailboard system and unfolding method and manufacturing method thereof

Abstract

The invention relates to the technical field of solar wing sailboards, in particular to a solar wing sailboard system and an unfolding method and a manufacturing method thereof. Comprising a plurality of standard single-module substrates, and the single-module substrates achieve assembly of sailboards of different structural forms through substrate connecting blocks; output of the driving hinge and the driving motor is transmitted to the main female hinge through the gear transmission assembly, and the encoder assembly serves as a motion parameter detection device and can transmit the hinge unfolding angle to an upper computer system. According to the solar wing sailboard system, the standard modular design is adopted in the solar wing sailboard system, and a complete solar wing sailboard is formed by assembling a plurality of single module substrates. The modular design not only simplifies the production process, but also realizes batch production and cost control, and reduces the manufacturing cost. Due to the modular design, the size and the power configuration of the sailboard can be flexibly adjusted according to actual requirements, and the adaptability and the expandability of the system are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of solar wing sailboards, and in particular to a solar wing sailboard system and a deployment method and a manufacturing method thereof. Background Art

[0002] With the gradual development of the country's aerospace field, the demand for spacecraft continues to expand. At the same time, the power consumption of spacecraft has not increased much. Almost all spacecraft use solar panels to obtain energy in the sky, and the demand for high-power solar panels continues to expand.

[0003] At present, there are various structural forms of solar wing sailboard systems at home and abroad. The commonly used sailboard structure is a rigid sailboard, and its unfolding is a one-time unfolding and locking mechanism, and it does not have the function of repeated folding and unfolding. With the increasing demand for high-power solar wing sailboards in spacecraft, the size and fold number of rigid solar wing sailboards are constantly increasing. Traditional rigid solar wings that are unfolded and locked once are difficult to meet the current needs of high-power sailboards. When the spacecraft needs to change its orbit over a large range, the large-area, multi-fold unfolded solar wings will bear a large load; the retractable solar wing hinge can fold the solar wing sailboard in orbit, reducing the load on the solar wing when the spacecraft changes its orbit.

[0004] At present, retractable solar wing hinges mostly use in-position switches as extension and retraction indications, and the motor is open-loop controlled, which can only control the solar wing sailboard to be fully extended and folded. At the same time, retractable solar wing hinges mostly use single-motor direct-drive control. This type of drive method has the risk of motor shaft overload and damage during the spacecraft's ascent phase. The in-position switch controls the extension and retraction state and the single-motor driven hinge extension and retraction are both single-point control states. If the in-position switch / motor is damaged, the solar wing sailboard system extension and retraction system will fail.

[0005] In view of this, this patent application is specially filed to solve the problems existing in the prior art and to meet the needs of spacecraft for high-performance, low-cost, and high-reliability solar wing sailboard systems. Summary of the invention

[0006] The present invention provides a solar wing sailboard system and a deployment method and a manufacturing method thereof, aiming at improving the performance of the solar wing sailboard system.

[0007] To achieve the above object, the technical solution of the present invention is:

[0008] A solar wing sailboard system, comprising:

[0009] A plurality of standard single-module base plates, wherein the single-module base plates are used to assemble sailboards of different structural forms through base plate connecting blocks;

[0010] The active hinge includes a drive assembly, a mounting flange, a gear transmission assembly, an encoder assembly, a main male hinge and a main female hinge. The output of the drive motor is transmitted to the main female hinge through the gear transmission assembly. The encoder assembly is used as a motion parameter detection device to transmit the hinge expansion angle to the host computer system.

[0011] The driven hinge is used to assist in supporting the rotating shaft and to work with the active hinge to realize the deployment and folding of the solar wing sail panel;

[0012] The clamping and releasing device is arranged on the single module substrate and is used for fixing the single module substrate after folding. The clamping and releasing device comprises a clamping block, a base bracket, a wire binding shaft, a hot knife assembly, a lifting screw assembly and a bottom plate. The clamping and releasing device realizes the locking function of the solar wing sail panel by cooperating with the conical socket stop between the clamping block and the base bracket and fixing it by the wire binding. The wire binding tensioning process is realized by the lifting screw, and the hot knife assembly can heat and melt the wire binding to complete the unlocking and releasing work.

[0013] Furthermore, the compression release device adopts a hot knife assembly for unlocking, and the layout of the hot knife assembly is divided into opposite layout and stacked layout to meet the unlocking requirements of different wire binding pre-tensioning methods.

[0014] Furthermore, the active hinge and the driven hinge work together to enable the solar wing sailboard system to realize the on-orbit extension and retraction function, thereby solving the spacecraft's on-orbit requirements for the solar wing sailboard in various postures.

[0015] Furthermore, the unfolding mechanism of the solar wing sailboard system is controlled by a driving component, which is a motor. The motor controls the driving of the active hinge, which in turn drives the driven hinge. The unfolding and folding process is controllable, the unfolding angle and speed are adjustable, and there is no impact during the unfolding process.

[0016] A method for deploying a solar wing sailboard system comprises the following steps:

[0017] The hinge is driven by a motor to realize the unfolding and folding process of the solar wing sailboard, wherein the motor is used as a driving source and the gear set is used as a transmission mechanism to perform the unfolding and folding work of the hinge;

[0018] During the unfolding or folding process, the unfolding angle of the hinge is detected by the encoder component, and the information is fed back to the control system to ensure that the unfolding angle is accurately controllable;

[0019] The hot knife assembly is used to melt the binding wires, release the binding wire pre-tightening, and complete the unlocking of the compression release device, so that the solar wing sail panel can be smoothly unfolded or folded.

[0020] Furthermore, the layout of the hot knife assembly includes opposite layout and stacked layout to adapt to different wire pre-tightening methods and ensure the success rate of unlocking.

[0021] A method for compressing and releasing a solar wing sailboard system comprises the following steps:

[0022] The binding wire is pulled by lifting the screw assembly to tighten the binding wire, thereby ensuring that the solar wing sail panel and the satellite body are reliably locked;

[0023] The hot knife assembly generates heat to melt the binding wires, thereby releasing the binding wire pre-tension and unlocking the compression release device, allowing the solar wing sail panel to be unfolded or folded.

[0024] Furthermore, the layout of the hot knife assembly includes opposite layout and stacked layout to adapt to different wire pre-tightening methods and ensure the success rate of unlocking.

[0025] A method for manufacturing a solar wing sailboard system comprises the following steps:

[0026] Adopting standard modular design, multiple single-module substrates are assembled to form solar wing sail panels, thus realizing mass production and low-cost manufacturing of solar wing sail panels;

[0027] A multi-module combination design is carried out according to the actual size of the sailboard to form a standardized solar wing sailboard structure.

[0028] Furthermore, the solar wing sail panel system is suitable for a spacecraft power subsystem, and its main function is to supply power to the spacecraft and increase the power of the spacecraft battery array through a multi-layer folding structure.

[0029] The beneficial effects achieved by the present invention are:

[0030] The present invention provides a solar wing sailboard system, which adopts a standard modular design and forms a complete solar wing sailboard by assembling multiple single-module substrates. This modular design not only simplifies the production process, but also realizes mass production and cost control, thereby reducing manufacturing costs. The modular design allows the size and power configuration of the sailboard to be flexibly adjusted according to actual needs, thereby improving the adaptability and scalability of the system.

[0031] The solar wing sailboard system of the present invention adopts a motor-driven hinge method to unfold and fold the sailboard, making the whole process fully controllable. Compared with the traditional spring drive mechanism, the motor drive can accurately control the unfolding angle and speed, avoiding the impact and uncontrollable factors that may occur during the unfolding process. The motor drive method can also enable the solar wing sailboard to maintain any angle, meet the requirements of the spacecraft for different postures in orbit, and enhance the flexibility and adaptability of the system.

[0032] The solar wing sailboard system of the present invention adopts a motor drive and a hot knife fuse type compression release mechanism, so the entire unfolding and folding process is smooth and impact-free. This not only protects the solar wing sailboard itself, but also reduces the impact on other components of the spacecraft, and improves the reliability and safety of the system.

[0033] The present invention provides a solar wing sailboard system, which can be driven by a motor to realize multiple deployment and retraction operations, solving the problem that the traditional one-time deployment mechanism cannot be reused. This feature greatly prolongs the service life of the system and reduces maintenance costs, and is particularly suitable for tasks that require frequent adjustment of the solar wing posture.

[0034] The present invention provides a solar wing sailboard system, wherein the compression and release device adopts a binding wire and a conical socket compression block, and is unlocked in combination with a hot knife assembly. The hot knife assembly is divided into two types: opposite arrangement and stacked arrangement, forming a primary-backup design, which improves the success rate of unlocking and the reliability of the system. The binding wire compression and release device has a low cost, and the unlocking process is impact-free, which further improves the economy and safety of the system.

[0035] The present invention provides a solar wing sailboard system, which can adapt to the reliable compression and unlocking of multiple layers of sailboards, ensure the connection and fixation between the layers of sailboards and the star body through the cone socket stop structure and the pre-tightening of the binding wire, limit the horizontal displacement, and ensure the stability and reliability of the system.

[0036] The present invention provides a solar wing sailboard system, in which an in-position switch is arranged on the driven hinge as a backup for position detection of an active hinge encoder. When the encoder fails, an additional detection means can be provided to ensure accurate detection of the unfolding state of the sailboard, thereby improving the redundancy and safety of the system.

[0037] The present invention provides a solar wing sailboard system, which is not only applicable to rigid stacked sailboards, but also to flexible sailboards, and has a wide range of applicability. Through different module combinations and configurations, it can meet the needs of different types of spacecraft, especially in complex tasks such as high power and multi-attitude adjustment. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0039] Figure 1 It is a schematic diagram of the overall structure of a solar wing sailboard system;

[0040] Figure 2 An enlarged view of an active hinge of a solar wing sail system;

[0041] Figure 3 This is an enlarged view of the internal structure of an active hinge of a solar wing sail system;

[0042] Figure 4 It is an enlarged view of the gear transmission component structure of a solar wing sailboard system;

[0043] Figure 5 It is an enlarged view of the structure of a driving component of a solar wing sailboard system;

[0044] Figure 6 It is an enlarged view of a driven hinge structure of a solar wing sailboard system;

[0045] Figure 7 It is an enlarged view of another angle of a driven hinge structure of a solar wing sailboard system;

[0046] Figure 8 It is an enlarged view of a compression and release device of a solar wing sail panel system;

[0047] Fig. 9 A diagram of a single-axis hot knife structure of a solar wing sailboard system arranged in opposing directions;

[0048] Fig.10 A diagram of a double-axis hot knife structure for a solar wing sail system arranged in a stacked manner;

[0049] In the figure, 1, single module base plate; 2, driven hinge; 21, slave female hinge; 22, slave male hinge; 23, in-position switch; 24, ball joint shaft;

[0050] 3. Active hinge; 31. Driving assembly; 32. Mounting flange; 33. Gear transmission assembly; 331. Motor gear; 332. Driving gear; 34. Encoder assembly; 35. Main male hinge; 36. Main female hinge;

[0051] 4. Baseboard connection block;

[0052] 5. Compression release device; 51. Compression block; 52. Wire binding shaft; 53. Hot knife assembly; 54. Lifting screw assembly; 55. Wire binding.

[0053] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0054] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0055] It should be noted that if the embodiments of the present invention involve directional indications (such as up, down, left, right, front, back...), the directional indications are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0056] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present invention, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, if the meaning of "and / or" appearing in the full text is to include three parallel schemes, taking "A and / or B" as an example, it includes scheme A, or scheme B, or a scheme that satisfies both A and B. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in this field to implement. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0057] like Figure 1-10 As shown, a solar wing sailboard system includes: a plurality of standard single-module substrates 1, wherein the single-module substrates 1 realize sailboard assembly of different structural forms through substrate connection blocks 4; as the basic building unit of the solar wing sailboard, the single-module substrate 1 provides structural support for the entire system. They are interconnected through substrate connection blocks 4 to form sailboard assembly of different structural forms. With the standard modular design, the size and power configuration of the sailboard can be flexibly adjusted according to actual needs, thereby improving the adaptability and scalability of the system. It is usually manufactured using lightweight, high-strength materials (such as carbon fiber composite materials) to ensure good radiation resistance and thermal stability in space.

[0058] The active hinge 3 includes a drive assembly 31, a mounting flange 32, a gear transmission assembly 33, an encoder assembly 34, a main male hinge 35 and a main female hinge 36, wherein the output of the drive motor is transmitted to the main female hinge 36 through the gear transmission assembly 33, and the encoder assembly 34 is used as a motion parameter detection device to transmit the hinge deployment angle to the host computer system; the encoder assembly 34 is used as a motion parameter detection device to monitor the hinge deployment angle in real time and feed back the data to the control system to ensure the precise controllability of the deployment process. The motor drive mode allows the solar wing sail to maintain any angle, meet the spacecraft's requirements for different postures in orbit, and enhance the flexibility and adaptability of the system. Compared with the traditional spring drive mechanism, the motor drive can avoid the impact that may occur during the deployment process and protect the safety of the solar wing sail and other components of the spacecraft.

[0059] The driven hinge 2 is used to assist in supporting the rotating shaft and works with the active hinge 3 to realize the unfolding and folding of the solar wing sailboard; an in-position switch 23 is arranged on the driven hinge 2 as a backup for the encoder position detection of the active hinge 3, which can provide an additional detection method when the encoder fails, thereby ensuring the accurate detection of the unfolding state of the sailboard and improving the redundancy and safety of the system.

[0060] The clamping and releasing device 5 includes a clamping block 51, a base bracket, a wire binding shaft 52, a hot knife assembly 53, a lifting screw assembly 54 and a bottom plate. The clamping and releasing device 5 realizes the locking function of the solar wing sailboard by cooperating with the conical socket stop between the clamping block 51 and the base bracket and fixing it by the wire binding, wherein the wire binding tensioning process is realized by the lifting screw, and the hot knife assembly 53 can heat and melt the wire binding 55 to complete the unlocking and releasing work. The clamping and releasing device 5 adopts the hot knife assembly 53 for unlocking. The hot knife assembly 53 is arranged in opposite directions and in layers to meet the unlocking requirements of different wire binding pre-tightening methods. The hot knife assembly 53 can heat and melt the wire binding 55 to complete the unlocking work of the clamping and releasing device 5, so that the solar wing sailboard can be smoothly unfolded or folded. The hot knife assembly 53 is arranged in opposite directions and in layers to adapt to different wire binding pre-tightening methods and ensure the success rate of unlocking. The compression and release device 5 of the wire binding method has a low cost and an impact-free unlocking process, which further improves the economy and safety of the system.

[0061] The design of the hot knife assembly 53 takes redundancy into consideration. Even if one deployment method fails, the other deployment method can still work normally, thereby improving the safety of the system. The hot knife assembly 53 can generate heat and fuse the binding wire in a short time, ensuring that the unlocking process is completed quickly without affecting the deployment progress of the solar wing sail panel.

[0062] The active hinge 3 and the driven hinge 2 work together to enable the solar wing sailboard system to realize the on-orbit extension and retraction function, thereby meeting the spacecraft's on-orbit requirements for the solar wing sailboard in various postures.

[0063] The unfolding mechanism of the solar wing sailboard system is controlled by a driving component 31, which is a motor. The motor controls the driving active hinge 3, which in turn drives the driven hinge 2. The unfolding and folding process is controllable, the unfolding angle and speed are adjustable, and there is no impact during the unfolding process.

[0064] A method for deploying a solar wing sailboard system comprises the following steps:

[0065] The hinge is driven by a motor to realize the unfolding and folding process of the solar wing sailboard, in which the motor serves as a driving source and the gear set serves as a transmission mechanism to execute the unfolding and folding work of the hinge.

[0066] During the unfolding or folding process, the unfolding angle of the hinge is detected by the encoder assembly 34, and the information is fed back to the control system to ensure that the unfolding angle is accurately controllable.

[0067] The hot knife assembly 53 is used to melt the binding wire, release the pre-tightening of the binding wire, and complete the unlocking of the compression release device 5, so that the solar wing sailboard can be smoothly unfolded or folded.

[0068] The arrangement of the hot knife assembly 53 includes opposite arrangement and stacked arrangement to adapt to different wire pre-tightening methods and ensure the success rate of unlocking.

[0069] A method for compressing and releasing a solar wing sailboard system comprises the following steps:

[0070] The binding wire is pulled by lifting the screw assembly 54 to tighten the binding wire, thereby ensuring that the solar wing sail panel and the satellite body are reliably locked.

[0071] The hot knife assembly 53 generates heat to melt the binding wire, thereby releasing the pre-tightening of the binding wire and unlocking the compression release device 5, allowing the solar wing sail panel to be unfolded or folded.

[0072] like Fig. 9 and Fig.10 As shown, the layout of the hot knife assembly 53 includes opposite layout and stacked layout to adapt to different wire pre-tightening methods to ensure the success rate of unlocking. The opposite layout and stacked layout are selected according to the actual unlocking space, and the difference between the two is that the main and standby hot knives are placed in different positions.

[0073] A method for manufacturing a solar wing sailboard system comprises the following steps:

[0074] By adopting a standard modular design, a plurality of single-module substrates 1 are assembled to form a solar wing sail panel, thereby realizing mass production and low-cost manufacturing of the solar wing sail panel.

[0075] A multi-module combination design is carried out according to the actual size of the sailboard to form a standardized solar wing sailboard structure.

[0076] The solar wing sail panel system is suitable for a spacecraft power subsystem, and its main function is to supply power to the spacecraft and increase the power of the spacecraft battery array through a multi-layer foldable structure.

[0077] like Figure 2 and Figure 3 As shown, the active hinge 3 of the retractable solar wing hinge mainly includes a main male hinge 35, a main female hinge, a gear transmission assembly 33 (inside the protective cover), an encoder assembly 34, and a drive motor. The output of the drive motor is transmitted to the female hinge through a gear reducer assembly. The maximum torque of the brushed DC motor used in the present invention is 1.5Nm. After passing through the gear set reducer, the motor can output a maximum torque of 2.4Nm, which can provide a sufficiently large deployment torque for the deployment system to ensure that the deployment process of the retractable solar wing hinge does not get stuck. The outside of the gear assembly uses a motor protection cover to prevent dust and excess objects, etc., to prevent the gear from being contaminated by excess objects and getting stuck. The active hinge 3 adopts a dual-motor main backup design. If the main motor works abnormally, the backup motor can work to improve the system robustness of the retractable hinge. The active hinge 3 uses a magnetic encoder 6 as a motion parameter detection device for the active hinge 3, which can transmit the hinge deployment angle to the host computer system. The magnetic encoder is small in size and low in cost, which can realize the low-cost design of the active hinge 3.

[0078] The gear set of the active hinge 3 mainly includes an encoder magnet 14, a drive gear 332 blocking shaft 15, a drive gear 332 bearing 16, and a motor gear 331 bearing 17. The magnetic encoder magnet is installed through the mounting plate and the drive gear 332, and can feedback the rotation angle position of the drive gear 332. The drive gear 332 and the motor gear 331 are both matched with bearings and mounting surfaces, which can ensure smooth rotation of the gears and reduce the axial force of the motor.

[0079] like Figure 4 As shown, the gear set of the active hinge 3 mainly includes a motor gear 3318 and a driving gear 3329, wherein the motor gear 3318 adopts a broken tooth design, which has two functions: one is to ensure that the two gears are in a non-meshing state during the mechanical uplink phase of the spacecraft, thereby avoiding collision and wear between the two gears during this phase; the other is to ensure that the main and backup operations of the retractable hinge of the dual motors do not affect each other, the working motor gear 331 is in a meshing state, and the backup motor housing is in a non-meshing state.

[0080] like Figure 6 and Figure 7As shown, the driven hinge 2 mainly comprises four parts, namely, a slave female hinge 2110, a slave male hinge 2211, an in-position switch 2312, and a ball hinge shaft 2413. The ball hinge as a shaft can eliminate the influence of different coaxiality of the two shafts on the hinge unfolding, and the in-position switch 23 can be used as a backup for the encoder assembly 34 of the active hinge 3 to detect the hinge unfolding state, and can detect whether the solar wing hinge is in place after the encoder fails.

[0081] Example 1: Solar wing sailboard system with standard modular design

[0082] This embodiment is suitable for medium to large spacecraft, especially those missions that require high-power electrical energy supply. The system can be customized according to the specific needs of the spacecraft to meet the needs of different missions.

[0083] The single module substrate 1 is made of high-strength, lightweight materials (such as carbon fiber composite materials) to ensure good radiation resistance and thermal stability in space. Each single module substrate 1 is integrated with a solar cell array and is stacked in multiple layers through a substrate connection block 4.

[0084] The active hinge 3 includes a small DC motor as a driving component 31, which transmits power to the main hinge 36 through a gear transmission component 33. The encoder component 34 is installed on the motor output shaft to detect the angular position of the hinge and feed the data back to the control system in real time.

[0085] The driven hinge 2 assists in supporting the rotating shaft and works in conjunction with the active hinge 3 to ensure the stability of the solar wing sail panel during the process of unfolding and folding.

[0086] The clamping release device 5 includes a clamping block 51, a base bracket, a wire binding shaft 52, a hot knife assembly 53, a lifting screw assembly 54 and a bottom plate. The clamping block 51 and the base bracket are matched through a conical socket stop, and the binding wire is tightened by the lifting screw to ensure that the solar wing sailboard and the satellite body are reliably locked. The hot knife assembly 53 is divided into two types of opposite layout and stacked layout to adapt to different wire binding pre-tightening methods to ensure the success rate of unlocking.

[0087] On the ground, according to the design requirements of the spacecraft, multiple single-module substrates 1 are used to assemble into the required size and shape of the solar wing sailboard through the substrate connecting block 4. After the assembly is completed, the solar wing sailboard is installed on the spacecraft and locked by the clamping release device 5.

[0088] When the spacecraft is launched, the clamping release device 5 remains locked to ensure that the solar wing sail panels will not become loose or damaged due to launch vibrations.

[0089] When the spacecraft enters the predetermined orbit, the ground control center sends a command to start the deployment procedure. First, the hot knife assembly 53 heats up and melts the binding wire to release the binding wire pre-tightening; then, the motor drives the active hinge 3, driving the driven hinge 2, so that the solar wing sail panel is gradually deployed. During the entire deployment process, the encoder assembly 34 continuously monitors the hinge angle and feeds the data back to the control system to ensure that the deployment process is smooth and impact-free. After the deployment is completed, the control system confirms that all hinges have reached the predetermined angle and the deployment action is completed.

[0090] Example 2: Solar wing sailboard system with repeated deployment and retraction functions

[0091] This embodiment is suitable for missions that require frequent adjustment of the solar wing attitude, such as earth observation satellites, communication satellites, etc. These missions may require regular changes in the angle of the solar wing to optimize energy collection efficiency.

[0092] A redundant design is added on the original basis, including an additional in-position switch 23, which is installed on the driven hinge 2 as a backup for the encoder position detection of the active hinge 3 to improve the reliability of the system.

[0093] The motor drive system has been optimized to enable more precise control of the speed and angle of deployment and folding, thereby better adapting to different posture adjustment requirements.

[0094] According to mission requirements, the ground control center can send instructions at any time to adjust the angle of the solar wing sail. The motor drive system responds to the instructions and performs the corresponding deployment or folding actions to ensure that the solar wing sail is always at the best energy collection angle.

[0095] Thanks to the motor drive mechanism, the solar wing sails can be deployed and retracted multiple times throughout the mission cycle, unlike traditional one-time deployment mechanisms that can only be deployed once. This feature greatly extends the service life of the system and reduces maintenance costs.

[0096] Example 3: Solar wing sailboard system suitable for flexible sailboard

[0097] This embodiment targets missions that require flexibility to accommodate spacecraft of different shapes and sizes, particularly small satellites, which often have strict size and weight constraints.

[0098] Flexible sailboards, made of lightweight, flexible solar cell materials, can be compactly stored in a folded state to save space. When unfolded, the sailboard can provide a large surface area to obtain sufficient electricity.

[0099] The compression release device 5, in order to adapt to the characteristics of the flexible sailboard, ensures that the flexible material will not be damaged when the binding line is untied. At the same time, the layout of the hot knife assembly 53 is adjusted to ensure that the unlocking process is fast and reliable.

[0100] Taking into account the special properties of the flexible sailboard, the motor-driven hinge unfolding mechanism is designed to be more gentle to avoid applying excessive force to the sailboard and prevent damage to the sailboard.

[0101] During the ground testing and assembly phase, the flexible sails were folded and secured with lashing lines to ensure they would not accidentally unfold during launch.

[0102] After entering the track, the hot knife assembly 53 fuses the binding wire, the motor drives the hinge to start working, and the flexible sailboard is gradually unfolded. Due to the material characteristics of the flexible sailboard, the unfolding process is relatively slow, but very stable, ensuring that the sailboard can work normally after being fully unfolded.

[0103] During the operation of the flexible sailboard in orbit, the angle of the sailboard can be fine-tuned through the motor drive mechanism to maximize the energy collection efficiency. Even after long-term operation, the flexible sailboard can still maintain good performance and will not age or be damaged due to repeated deployment and retraction.

[0104] The above descriptions are only optional embodiments of the present invention, and are not intended to limit the patent scope of the present invention. All equivalent structural changes made using the contents of the present invention's specification and drawings, or directly / indirectly applied in other related technical fields, are included in the patent protection scope of the present invention.

Claims

1. A solar wing sailboard system, characterized in that: include: A plurality of standard single-module base plates (1), wherein the single-module base plates (1) are used to assemble sailboards of different structural forms through base plate connecting blocks (4); The active hinge (3) comprises a driving assembly (31), a mounting flange (32), a gear transmission assembly (33), an encoder assembly (34), a main male hinge (35) and a main female hinge (36), wherein the output of the driving motor is transmitted to the main female hinge (36) through the gear transmission assembly (33), and the encoder assembly (34) serves as a motion parameter detection device and can transmit the hinge deployment angle to the upper computer system; A driven hinge (2) is used to assist in supporting the rotating shaft and to work together with the active hinge (3) to achieve the unfolding and folding of the solar wing sailboard; The pressing and releasing device (5) is arranged on the single module base plate and is used for fixing the single module base plate after folding.

2. A solar wing sailboard system according to claim 1, characterized in that: The clamping and releasing device (5) comprises a clamping block (51), a base bracket, a wire binding shaft (52), a hot knife assembly (53), a lifting screw assembly (54) and a bottom plate. The clamping and releasing device (5) achieves a locking function for the solar wing sailboard by cooperating between the clamping block (51) and the base bracket through a conical socket stop and fixing through a wire binding. The wire binding tensioning process is achieved through the lifting screw. The hot knife assembly (53) can generate heat to melt the wire binding to complete the unlocking and releasing work.

3. A solar wing sailboard system according to claim 1, characterized in that: The deployment mechanism of the solar wing sailboard system is controlled by a drive component (31), the drive component (31) is a motor, and the motor controls and drives the active hinge (3), thereby driving the driven hinge (2), and has controllable deployment and folding processes, adjustable deployment angles and speeds, and no impact during the deployment process.

4. A method for deploying a solar wing sailboard system, characterized in that: The steps include: The hinge is driven by a motor to realize the unfolding and folding process of the solar wing sailboard, wherein the motor is used as a driving source and the gear set is used as a transmission mechanism to perform the unfolding and folding work of the hinge; During the unfolding or folding process, the unfolding angle of the hinge is detected by the encoder assembly (34), and the information is fed back to the control system to ensure that the unfolding angle is accurately controllable; The hot knife assembly (53) is used to melt the binding wire, release the pre-tightening of the binding wire, and complete the unlocking of the pressing release device (5), so that the solar wing sailboard can be smoothly unfolded or folded.

5. The unfolding method according to claim 4, characterized in that: The arrangement of the hot knife assembly (53) includes opposite arrangement and stacked arrangement to adapt to different wire binding pre-tightening methods and ensure the success rate of unlocking.

6. A method for manufacturing a solar wing sailboard system, characterized in that: The steps include: A standard modular design is adopted to assemble a plurality of single-module substrates (1) to form a solar wing sail panel, thereby realizing mass production and low-cost manufacturing of the solar wing sail panel; A multi-module combination design is carried out according to the actual size of the sailboard to form a standardized solar wing sailboard structure.

7. The manufacturing method according to claim 6, characterized in that: The solar wing sail panel system is suitable for a spacecraft power subsystem and increases the power of a spacecraft battery array through a multi-layer foldable structure.

Images