Ground unfolding test device for large-scale single-plate unfolding type satellite solar wing
By designing a ground deployment test device for large-scale single-board expansion satellite solar wings, the problem of difficult to meet the requirements of high-precision and multi-angle dynamic performance in the prior art is solved, and the automatic expansion and closing of the solar wings is realized and Multi-angle performance testing improves the accuracy and efficiency of the test.
Patent Information
- Application Number
- CN202411611884.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-13
- Publication Date
- 2025-02-18
AI Technical Summary
The existing technology is difficult to meet the high-precision, multi-angle dynamic performance testing requirements of large-scale single-board expansion satellite solar wings in ground tests, and the degree of automation and mechanization is insufficient, resulting in cumbersome operation, low testing efficiency, stability and safety problems. .
A ground deployment test device for large-scale single-board expansion satellite sun wings was designed, including truss structure, mounting plate, mobile device and satellite. Through components such as suspension devices, clamping robotic arms and upper guide rail robotic arms, they are realized. Automatic expansion and closing of the sun wings and multi-angle performance testing.
The device can efficiently assist in the alignment, installation and disassembly of the solar wings, realize automatic expansion and closing and multi-angle dynamic performance testing, improve the accuracy and efficiency of the test, and ensure the reliability and stability of the solar wings during the deployment process.
Smart Images
Figure CN119469712A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the field of spacecraft ground test technology, and specifically to a ground deployment test device for large-scale single-board deployable satellite solar wings. The device can efficiently assist in the alignment, installation and disassembly of the solar wing, and realize its automatic deployment and folding and multi-angle dynamic performance testing on the ground. In addition, the clamping mechanical arm system provides precise support and limit for the solar wing, ensuring the reliability and stability of the solar wing during the deployment and folding process, and the upper rail mechanical arm can assist in the performance testing of the solar wing at multiple angles. Background Art
[0002] At present, the number of satellites in orbit in my country is increasing. Among them, solar panels are the energy supply system of satellites and the core component of space equipment. They directly determine whether the satellite can operate normally in orbit. However, the extreme environment in space can easily cause damage to the solar panels, making the actual service life of the satellite much lower than expected. Therefore, ground deployment tests and performance tests of solar panels are very important.
[0003] However, the solar wing is large in size and complex in structure, and traditional ground test equipment often cannot meet the needs of high-precision, multi-angle dynamic performance testing. Existing aerospace ground test technology still relies on manual operation, and the degree of automation and mechanization is still insufficient. There are problems such as cumbersome operation, low test efficiency, low stability, and lack of safety.
[0004] To address this problem, this paper develops a large-scale single-board deployable satellite solar wing deployment test device that can assist the solar wing in precise alignment with the satellite connection interface for installation and disassembly, and realize automatic deployment and folding and multi-angle dynamic performance testing. The device solves the deficiencies in the existing technology through innovative structural design, provides precise support and positioning for the solar wing, improves the accuracy and efficiency of the test, ensures the reliability and stability of the solar wing during the deployment process, and provides strong technical support for the development of spacecraft ground test technology. Summary of the invention
[0005] The purpose of the present invention is to provide a ground deployment test device for a large-scale single-board deployable satellite solar wing, comprising a truss structure 1, a mounting plate 2, a mobile device 3, and a satellite 4.
[0006] The truss structure 1 includes a truss body 1-1, an upper guide rail mechanical arm 1-2, a rack guide rail 1-3, a guide rail 1-4, a first suspension device 1-5, a second suspension device 1-6, a motor 1-2-1, a slider 1-2-2, a first connecting rod 1-2-3, a second connecting rod 1-2-4, a third connecting rod 1-2-5, a fourth connecting rod 1-2-6, a fifth connecting rod 1-2-7, a first clamping plate 1-2-8, a second clamping plate 1-2-9, a first slider 1-5-1, a second slider 1-5-2, a motor 1-5-3, a third slider 1-5-4, a guide rail 1-5-5, a suspension rope 1-5-6, a first slider 1-6-1, The second slider 1-6-2, the motor 1-6-3, the third slider 1-6-4, the guide rail 1-6-5, and the suspension rope 1-6-6; the connection relationship between the various components and equipment is as follows: the rack guide rail 1-3 and the guide rail 1-4 are fixedly connected to the truss 1-1; the upper guide rail mechanical arm 1-2 is connected to the rack guide rail 1-3 through a moving pair driven by a motor; one side of the first suspension device 1-5 is connected to the rack guide rail 1-3 through a moving pair driven by a motor; the other side of the first suspension device 1-5 is connected to the guide rail 1-4 through a moving pair; one side of the second suspension device 1-6 is connected to the rack guide rail 1-3 through a moving pair driven by a motor; the second suspension device 1-6 The other side is connected to the guide rail 1-4 through a moving pair; the motor 1-2-1 is connected to the slider 1-2-2 through a bolt connection; the slider 1-2-2 is connected to the first connecting rod 1-2-3 through a rotating pair driven by the motor; the first connecting rod 1-2-3 is connected to the second connecting rod 1-2-4 through a rotating pair driven by the motor; the second connecting rod 1-2-4 is connected to the third connecting rod 1-2-5 through a rotating pair driven by the motor; the third connecting rod 1-2-5 is connected to the fourth connecting rod 1-2-6 through a rotating pair driven by the motor; the fourth connecting rod 1-2-6 is connected to the fifth connecting rod 1-2-7 through a rotating pair driven by the motor; the fifth connecting rod 1-2-7 is connected to the The rotating pair driven by the motor is connected to the first clamping plate 1-2-8; the first clamping plate 1-2-8 is connected to the second clamping plate 1-2-9 through the rotating pair driven by the motor; the first slider 1-5-1 and the third slider 1-5-4 are fixedly connected at both ends of the connecting rod 1-5-5; the second slider 1-5-2 is connected to the connecting rod 1-5-5 through the moving pair; the suspension rope 1-5-6 is fixedly connected to the second slider 1-5-6; the first slider 1-6-1 and the third slider 1-6-4 are fixedly connected at both ends of the connecting rod 1-6-5; the second slider 1-6-2 is connected to the connecting rod 1-6-5 through the moving pair; the suspension rope 1-6-6 is fixedly connected to the second slider 1-6-6.
[0007] The mounting plate 2 includes a mounting plate body 2-1, a telescopic frame 2-2, a first motor 2-3, a rack guide rail 2-4, a slider 2-5, a hydraulic rod 2-6, a second motor 2-7, and a telescopic plate 2-8; the connection relationship between the various components is as follows: the hydraulic rod 2-6 is fixedly connected to the mounting plate body 2-1 by bolts; the telescopic frame 2-2 is connected to the hydraulic rod 2-6 by a hydraulically driven moving pair; the rack guide rail 2-4 is fixedly connected to the telescopic frame 2-2; the slider 2-5 is connected to the rack guide rail 2-4 by a motor-driven moving pair; the first motor 2-3 and the second motor 2-7 are fixedly connected to the slider 2-5 by bolts; the telescopic plate 2-8 is connected to the slider 2-7 by a motor-driven moving pair.
[0008] The mobile device 3 includes a satellite fixing seat 3-1, a clamping robot 3-2, a robot arm moving base 3-3, a mounting plate moving base 3-4, a large motor 3-5, a rack guide rail 3-6, a clamping actuator 3-2-1, a clamping wrist 3-2-2, a first connecting rod 3-2-3, a second connecting rod 3-2-4, a third connecting rod 3-2-5, a fourth connecting rod 3-2-6, and a robot arm base 3-2-7; the connection relationship between the various components is as follows: the satellite fixing seat 3-1 is fixedly connected to the rack guide rail 3-6; the clamping robot 3-2 is fixed to the robot arm moving base 3-3 by bolts; the robot arm moving base 3-3 and the mounting plate moving base 3-4 are connected to the rack guide rail 3-6 through a moving pair driven by a motor. Connection; the large motor 3-5 is fixed to the robot arm moving base 3-3 and the mounting plate moving base 3-4 by bolts; the clamping actuator 3-2-1 is connected to the clamping wrist 3-2-2 through a motor-driven moving pair; the clamping wrist 3-2-2 is connected to the first connecting rod 3-2-3 through a motor-driven rotating pair; the first connecting rod 3-2-3 is connected to the second connecting rod 3-2-4 through a motor-driven rotating pair; the second connecting rod 3-2-4 is connected to the third connecting rod 3-2-5 through a motor-driven rotating pair; the third connecting rod 3-2-5 is connected to the fourth connecting rod 3-2-6 through a motor-driven rotating pair; the fourth connecting rod 3-2-6 is connected to the robot arm base 3-2-7 through a motor-driven rotating pair.
[0009] Satellite 4 includes a satellite body 4-1, a support frame 4-2, a connecting plate 4-3, a substrate 4-4, a solar panel 4-5, a satellite connection interface 4-6, and a positioning column 4-7; the connection relationship between the various components is as follows: the support plate 4-2 can be fixed on the connection interface 4-6 by installation; the connecting plate 4-3 is connected to the support frame 4-2 by a hinge connection; the various substrates 4-4 are connected by hinges; the solar panel 4-5 is fixed on the substrate 4-4; the positioning column 4-7 is fixed to the lower end of the satellite body 4-1.
[0010] The connection method between each device is: the suspension rope 1-6-6 in the truss structure 1 is fixed on the base plate 4-4 in the satellite 4; the positioning column 4-7 in the satellite 4 is fixed on the satellite fixing seat 3-1 in the mobile device 3; the mounting plate body 2-1 in the mounting plate 2 is fixed on the mounting plate moving base 3-4 in the mobile device 3.
[0011] The working principle of the present invention is as follows: Reference Figure 3 , Figure 7 , Fig.11 , Fig.12 , Fig.13 , Fig.15 A ground deployment test device for a large-scale single-board deployable satellite solar wing consists of a truss structure 1, a mounting plate 2, a mobile device 3 and a satellite 4.
[0012] Reference Figure 1 , Fig.11 , Fig.12 , Fig.13 , Fig.15 A telescopic frame 2-2 on a mounting plate 2 of a large-scale single-board deployable satellite solar wing ground deployment test device is retracted and extended by hydraulic drive, and the height of the telescopic plate 2-8 can be adjusted. The first motor 2-3 drives the gear to rotate and engage with the rack on the rack guide 2-4 to move, and the distance between the two telescopic plates can be adjusted to better clamp the support plate 4-2 in the satellite 3. At the same time, the second motor 2-7 drives the gear to rotate and engage with the rack on the telescopic plate 2-8 to complete the telescopic function of the telescopic plate 2-8, so that the solar wing can be more stably fixed on the mounting plate 2 to align with the interface. Finally, the two telescopic plates 2-8 clamp the support plate 4-2 so that the support plate 4-2 is in a vertical posture and aligned with the interface to complete the installation.
[0013] Reference Figure 3 , Figure 6 , Figure 7 , Fig. 9 , Fig.10 , Fig.15 A suspension device 1-5 on a truss 1 of a large-scale single-board deployable satellite solar wing ground deployment test device is driven by a motor 1-5-3 to rotate the gear and mesh with the rack on the rack guide 1-3 to form a moving pair. At the same time, the suspension device 1-6 below is driven by a motor 1-6-3 to rotate the gear and mesh with the rack on the rack guide 1-3 to form a moving pair. The two suspension devices are driven at the same time to realize the deployment of the solar wing, so as to stably deploy the solar wing. At the same time, the upper and lower separation of the two suspension devices can realize that each substrate is more compact in the folded form.
[0014] Reference Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 , Fig.13 , Fig.14 , Fig.15 A clamping mechanical arm 3-2 in a mobile device 3 for a large-scale single-board deployable satellite solar wing ground deployment test device can clamp the outermost substrate 4-4 by adjusting the position through motor drive between each rod, and then adjust the clamping actuator 3-2 to close inward through motor drive, so as to clamp the outer substrate 4-4 more tightly, and can also play the role of limiting and supporting during the deployment process. Similarly, during the folding process, the suspension device alone may cause each substrate 4-4 to be subjected to force toward the outside of the hinge and cause damage. Therefore, when the folding starts, the rotation of the clamping mechanical arm plays a key role.
[0015] Reference Figure 4 , Figure 5 , Figure 7 , Figure 8 , Fig.15 When the angle between each substrate 4-4 in satellite 3 of a large-scale single-board deployable satellite solar wing ground deployment test device needs to be adjusted, the upper guide rail mechanical arm 1-2 drives the gear to rotate through the motor 1-2-1 to engage with the rack on the rack guide rail 1-3 to form a moving pair, and then the motor drive between each connecting rod in the upper guide rail mechanical arm 1-2 adjusts the posture, applies pressure to the hinge connection of the substrate 4-4, and adjusts the angle of each substrate 4-4 by the angle between the first clamping plate 1-2-8 and the second clamping plate 1-2-9, which can assist in the performance test of the solar wing under multi-angle deployment.
[0016] The advantages of the present invention are: 1. The present invention is a ground deployment test device for large-scale single-board deployable satellite solar wings, which consists of a truss structure, a mounting plate, a mobile device and a satellite. It can be used for installation and disassembly of solar wings of different scales aligned with the satellite interface. The installation height of the base plate can be adjusted according to the position of the interface, and the distance between the telescopic plates can be adjusted according to the thickness of the base plate. It has a wide range of applications and strong practicality.
[0017] 2. The present invention is a ground deployment test device for large-scale single-board deployable satellite solar wings. When deploying, a suspension device drives the solar wing to deploy and fold through a moving pair driven by a motor. It has good stability and high efficiency. At the same time, the rack and pinion transmission has the characteristics of high precision and high speed.
[0018] 3. The present invention is a ground deployment test device for large-scale single-board deployable satellite solar wings. In the face of the problem of heavy load on large-scale single boards, during the deployment of the solar wings, the clamping mechanical arm clamps the outermost substrate and then drives the deployment through various suspension devices, which has the functions of limiting and supporting, thereby improving stability.
[0019] 4. The present invention is a ground deployment test device for large-scale single-board deployable satellite solar wings. At the beginning of the folding process, the solar wing is driven by the suspension device alone, which may cause the base plate to be forced toward the outside of the hinge connection and cause damage. The clamping mechanical arm can flip the angle and work together with the suspension device to fold the solar wing, thereby better protecting the solar wing and preventing damage.
[0020] 5. The present invention is a ground deployment test device for large-scale single-board deployable satellite solar wings. The robot arm can adjust the position and apply pressure on the hinge connection between the substrates to adjust the angle between the substrates when the solar wing is deployed. It is highly professional and efficient, and can assist in completing the performance test of the solar wing at different angles. At the same time, the number of robot arms can be increased or decreased according to the number of solar wing substrates. BRIEF DESCRIPTION OF THE DRAWINGS
[0021] Figure 1 Schematic diagram of solar wing installation in the present invention; Figure 2 Schematic diagram of the robot arm clamping the solar wing substrate in the present invention; Figure 3 Schematic diagram of the deployment of the solar wing in the present invention; Figure 4 Schematic diagram of multi-angle fixing of solar wings in the present invention Figure 1 ; Figure 5 Schematic diagram of multi-angle fixing of solar wings in the present invention Figure 2 ; Figure 6 Schematic diagram of folding the solar wing in the present invention; Figure 7 Schematic diagram of the truss structure in the present invention; Figure 8 Schematic diagram of the upper guide rail mechanical arm of the truss in the present invention; Fig. 9 A schematic diagram of a first suspension device of a truss in the present invention; Fig.10 A schematic diagram of a second suspension device of a truss in the present invention; Fig.11 The mounting plate of the present invention is shown in FIG. Figure 1 ; Fig.12 The mounting plate of the present invention is shown in FIG. Figure 2 ; Fig.13 A schematic diagram of a mobile device in the present invention; Fig.14 A schematic diagram of a clamping mechanical arm of a mobile device in the present invention; Fig.15 Schematic diagram of satellite in the present invention; In the figure: 1: Truss structure 2: Mounting plate 3: Mobile device 4: Satellite 1-1: Truss body 1-2: Upper guide rail mechanical arm 1-3: Rack guide rail 1-4: Guide rail 1-5: First suspension device 1-6: Second suspension device 1-2-1: Motor 1-2-2: Slider 1-2-3: First connecting rod 1-2-4: Second connecting rod 1-2-5: Third connecting rod 1-2-6: Fourth connecting rod 1-2-7: Fifth connecting rod 1-2-8: First clamping plate 1-2-9: Second clamping plate 1-5-1: First slider 1-5-2: Second slider 1-5-3: Motor 1-5-4: Third slider 1-5-5: Connecting rod 1-5-6: Lifting rope 1-6-1: First slider 1-6-2: Second slider 1-6-3: Motor 1-6-4: Third slider 1-6-5: Connecting rod 1-6-6: Lifting rope 2-1: Mounting plate body 2-2: Telescopic frame 2-3: First motor 2-4: Rack guide 2-5: Slider 2-6: Hydraulic rod 2-7: Second motor 2-8: Telescopic plate 3-1: Satellite mount 3-2: Clamping arm 3-3: Mobile base of the arm 3-4: Mobile base of the mounting plate 3-5: Large motor 3-6: Rack guide 3-2-1: Clamping actuator 3-2-2: Clamping wrist 3-2-3: First link 3-2-4: Second link 3-2-5: Third link 3-2-6: Fourth link 3-2-7: Base of the arm 4-1: Satellite body 4-2: Support plate 4-3: Connecting plate 4-4: Base plate 4-5: Solar panel 4-6: Satellite connection interface 4-7: Positioning column DETAILED DESCRIPTION
[0022] The present invention is described below in conjunction with the accompanying drawings and embodiments, but the present invention is not limited to the following embodiments. Example
[0023] Reference Figure 1 , Figure 2 , Figure 3 , Fig.14 A ground deployment test device for large-scale single-board deployable satellite solar wings consists of a truss structure 1, a mounting frame 2, a mobile device 3 and a satellite 4, and can complete the tasks of solar wing alignment, installation, disassembly, automatic deployment and folding, and multi-angle fixation.
[0024] Reference Figure 1 , Fig.11 , Fig.12 , Fig.13 , Fig.15A mounting plate 2 for a large-scale single-board deployable satellite solar wing ground deployment test device is first adjusted by the thickness of the solar wing support plate 4-2 and the total thickness of each base plate 4-4 after folding, wherein driving the first motor 2-3 can adjust the distance between the telescopic plates 2-8, and driving the second motor 2-7 can adjust the distance between the mounting plate body 2-1 and the telescopic plate 2-8. After the solar wing is fixed on the mounting plate 2, the height of the telescopic frame 2-2 is controlled by hydraulic drive to align with the satellite connection interface 4-6 for fixing. It is suitable for the installation of solar wings of different sizes. After installation, it can be The telescopic plate 2-8 is retracted by adjusting the height and spacing, and at the same time, the large motor 3-5 in the moving device 3 drives the gear to rotate and engage with the rack guide 3-6 to drive the mounting plate moving base 3-4 to retract. The disassembly process is similar to the installation process. After the solar wing is folded, the mounting plate 2 is driven by the mounting plate moving base 3-4 in the moving device 3 to the front of the folded solar wing, so that the outermost substrate 4-4 coincides with the surface of the mounting plate main body 2-1, and the hydraulic drive controls the height of the telescopic frame 2-2 to wrap the solar wing, and then the mounting plate is driven back by the mounting plate moving base 3-4 to complete the folding.
[0025] Reference Figure 2 , Figure 3 , Figure 7 , Fig. 9 , Fig.10 , Fig.13 , Fig.14 The outermost second suspension device 1-6 of a truss structure 1 of a large-scale single-board deployable satellite solar wing ground deployment test device first drives the outermost substrate 4-4 in the satellite 4 to open by driving the gear to rotate through the motor 1-6-3, and the clamping mechanical arm 3-2 in the moving device 3 adjusts the posture by rotating through the motor drive between the rods, so that the clamping actuator 3-2-1 of the clamping mechanical arm 3-2 clamps the outermost substrate 4-4, and then the first suspension device 1-5 and the second suspension device 1-6 are driven by the motor to drive the remaining substrates to unfold together, and the clamping mechanical arm 3-2 continuously adjusts the posture through the motor drive between the rods to ensure the stability of the outermost substrate 4-4, which plays a role of support and limit.
[0026] Reference Figure 4 , Figure 5 , Figure 7 , Figure 8 , Fig.13 , Fig.14 , Fig.15The upper rail mechanical arm 1-2 in the truss structure 1 of a large-scale single-board deployable satellite solar wing ground deployment test device can drive the slider 1-2-2 to move to the position between each substrate 4-4 through the motor 1-2-1 driving gear rotation, and the upper rail mechanical arm 1-2 is driven by the motor between each rod to adjust the posture, and adjust the angle between the first clamping plate 1-2-8 and the second clamping plate 1-2-9, and apply pressure to a pair of substrates 4-4. Then, the mechanical arm in the moving device 3 adjusts the position of the mobile base 3-3 and the motor drive between the rods of the clamping mechanical arm 3-2 to adjust the posture, which can assist in the performance test of the multi-angle folding lower solar wing.
[0027] Reference Figure 6 , Figure 7 , Fig. 9 , Fig.10 , Fig.13 , Fig.14 , Fig.15 After the clamping mechanical arm 3-2 in the mobile device 3 of a large-scale single-board deployable satellite solar wing ground deployment test device flips the outermost substrate 4-4 toward the inner side of the hinge connection, the motor drive of each suspension device in the truss structure 1 drives each substrate 4-4 to retract, and the clamping mechanical arm 3-2 supports and prevents the substrate 4-4 from being damaged by force.
Claims
1. A ground deployment test device for large-scale single-board deployable satellite solar wings, characterized by: It includes a truss structure (1), a mounting plate (2), a mobile device (3) and a satellite (4); The truss structure (1) comprises a truss body (1-1), an upper guide rail mechanical arm (1-2), a rack guide rail (1-3), a guide rail (1-4), a first suspension device (1-5), a second suspension device (1-6), a motor (1-2-1), a slider (1-2-2), a first connecting rod (1-2-3), a second connecting rod (1-2-4), a third connecting rod (1-2-5), a fourth connecting rod (1-2-6), a fifth connecting rod (1-2-7), a first clamping plate (1-2-8), a second clamping plate (1-2-9), a first slider (1-5-1), a second slider (1-5-2), a motor (1-5-3), a third slider (1-5-4), a guide rail (1-5-5), a suspension rope (1-56), a first A slider (1-6-1), a second slider (1-6-2), a motor (1-6-3), a third slider (1-6-4), a guide rail (1-6-5), and a suspension rope (1-6-6); the connection relationship between the various components and equipment is as follows: the rack guide rail (1-3) and the guide rail (1-4) are fixedly connected to the truss (1-1); the upper guide rail mechanical arm (1-2) is connected to the rack guide rail (1-3) through a moving pair driven by a motor; one side of the first suspension device (1-5) is connected to the rack guide rail (1-3) through a moving pair driven by a motor; the other side of the first suspension device (1-5) is connected to the guide rail (1-4) through a moving pair; one side of the second suspension device (1-6) is connected to the rack guide rail (1-3) through a moving pair driven by a motor; The other side of the suspension device (1-6) is connected to the guide rail (1-4) through a moving pair; the motor (1-2-1) is connected to the slider (1-2-2) through a bolt connection; the slider (1-2-2) is connected to the first connecting rod (1-2-3) through a rotating pair driven by the motor; the first connecting rod (1-2-3) is connected to the second connecting rod (1-2-4) through a rotating pair driven by the motor; the second connecting rod (1-2-4) is connected to the third connecting rod (1-2-5) through a rotating pair driven by the motor; the third connecting rod (1-2-5) is connected to the fourth connecting rod (1-2-6) through a rotating pair driven by the motor; the fourth connecting rod (1-2-6) is connected to the fifth connecting rod (1-2-7) through a rotating pair driven by the motor; the fifth connecting rod (1-2-7) The first clamping plate (1-2-8) is connected to the first clamping plate (1-2-8) through a rotating pair driven by a motor; the first clamping plate (1-2-8) is connected to the second clamping plate (1-2-9) through a rotating pair driven by a motor; the first slider (1-5-1) and the third slider (1-5-4) are fixedly connected to the two ends of the connecting rod (1-5-5); the second slider (1-5-2) is connected to the connecting rod (1-5-5) through a moving pair; the suspension rope (1-5-6) is fixedly connected to the second slider (1-5-6); the first slider (1-6-1) and the third slider (1-6-4) are fixedly connected to the two ends of the connecting rod (1-6-5); the second slider (1-6-2) is connected to the connecting rod (1-6-5) through a moving pair; the suspension rope (1-6-6) is fixedly connected to the second slider (1-6-6); The mounting plate (2) comprises a mounting plate body (2-1), a telescopic frame (2-2), a first motor (2-3), a rack guide rail (2-4), a slider (2-5), a hydraulic rod (2-6), a second motor (2-7), and a telescopic plate (2-8); the connection relationship between the various components is as follows: the hydraulic rod (2-6) is fixedly connected to the mounting plate body (2-1) by bolt connection; the telescopic frame (2-2) is connected to the hydraulic rod (2-6) by a hydraulically driven moving pair; the rack guide rail (2-4) is fixedly connected to the telescopic frame (2-2); the slider (2-5) is connected to the rack guide rail (2-4) by a motor-driven moving pair; the first motor (2-3) and the second motor (2-7) are fixedly connected to the slider (2-5) by bolt connection; and the telescopic plate (2-8) is connected to the slider (2-7) by a motor-driven moving pair; The moving device (3) comprises a satellite fixing seat (3-1), a clamping robot arm (3-2), a robot arm moving base (3-3), a mounting plate moving base (3-4), a large motor (3-5), a rack guide rail (3-6), a clamping actuator (3-2-1), a clamping wrist (3-2-2), a first connecting rod (3-2-3), a second connecting rod (3-2-4), a third connecting rod (3-2-5), a fourth connecting rod (3-2-6), and a robot arm base (3-2-7); the connection relationship between the various components is as follows: the satellite fixing seat (3-1) is fixedly connected to the rack guide rail (3-6); the clamping robot arm (3-2) is fixed to the robot arm moving base (3-3) by bolt connection; the robot arm moving base (3-3) and the mounting plate moving base (3-4) are connected to the rack guide rail through a moving pair driven by a motor. The large motor (3-5) is fixed to the movable base (3-3) of the robot arm and the movable base (3-4) of the mounting plate by bolt connection; the clamping actuator (3-2-1) is connected to the clamping wrist (3-2-2) by a movable pair driven by the motor; the clamping wrist (3-2-2) is connected to the first connecting rod (3-2-3) by a rotating pair driven by the motor; the first connecting rod (3-2-3) is connected to the second connecting rod (3-2-4) by a rotating pair driven by the motor; the second connecting rod (3-2-4) is connected to the third connecting rod (3-2-5) by a rotating pair driven by the motor; the third connecting rod (3-2-5) is connected to the fourth connecting rod (3-2-6) by a rotating pair driven by the motor; the fourth connecting rod (3-2-6) is connected to the robot arm base (3-2-7) by a rotating pair driven by the motor; The satellite (4) comprises a satellite body (4-1), a support frame (4-2), a connecting plate (4-3), a substrate (4-4), a solar panel (4-5), a satellite connection interface (4-6), and a positioning column (4-7); the connection relationship between the various components is as follows: the support plate (4-2) is fixed on the satellite connection interface (4-6) by installation; the connecting plate (4-3) is connected to the support frame (4-2) by a hinge connection; the various substrates (4-4) are connected by hinges; the solar panel (4-5) is fixed on the substrate (4-4); and the positioning column (4-7) is fixed to the lower end of the satellite body (4-1); The suspension rope (1-6-6) in the truss structure (1) is fixed on a base plate (4-4) in the satellite (4); the positioning column (4-7) in the satellite (4) is fixed on a satellite fixing seat (3-1) in the mobile device (3); and the mounting plate body (2-1) in the mounting plate (2) is fixed on a mounting plate moving base (3-4) in the mobile device (3).
2. The ground deployment test device for large-scale single-board deployable satellite solar wing according to claim 1 is characterized in that: During the solar wing installation process, the mounting plate adjusts the telescopic plate spacing, height and distance from the mounting plate body according to the different large-scale solar wings to fix the solar wing support plate to align with the satellite connection interface for installation.
3. The ground deployment test device for large-scale single-board deployable satellite solar wing according to claim 1 is characterized in that: After the installation is completed, the deployment process begins. The outermost suspension device drives the outermost substrate to unfold through the motor drive. Then the clamping robot arm is driven by the mobile base and the motor drive between each rod member adjusts the posture, so that the clamping actuator clamps the outermost substrate. Then each suspension device drives the solar wing to unfold at the same time, and the motor drive between each rod member of the clamping robot arm adjusts the posture to ensure the stability of the solar wing deployment process.
4. The large-scale satellite solar wing auxiliary folding and disassembly device in a space environment according to claim 1, characterized in that: The upper guide rail robotic arm is driven by a motor to move along the rack guide rail and adjust its position, then exerts pressure on the hinge connections between the substrates to adjust the angles between the substrates when the solar wing is unfolded, thereby assisting in completing the performance test of the solar wing at different angles and increasing or decreasing the number of robotic arms according to the number of solar wing substrates.
5. The large-scale satellite solar wing auxiliary folding and disassembly device in a space environment according to claim 1, characterized in that: At the beginning of the folding process, the solar wing is driven by the suspension device alone, which may cause the substrate to be subjected to force toward the outside of the hinge connection and cause damage. After the clamping robotic arm flips the angle, the suspension device drives the substrate through the motor to move toward the satellite to fold the solar wing and protect the solar wing from damage.
6. The large-scale satellite solar wing auxiliary folding and disassembly device in a space environment according to claim 1, characterized in that: After folding, the mounting plate moves the base to drive the mounting plate forward to the folding surface of the solar wing. The mounting plate changes the height of the telescopic plate through hydraulic drive, and the motor drive controls the spacing between the telescopic plates. The motor drive adjusts the spacing between the telescopic plate and the mounting plate body to wrap the folded solar wing. After fixing the solar wing, the solar wing mounting plate will be removed and returned.