A large-load tether deployment device for a space rotating tether system

Abstract

The present invention proposes a large-load tether deployment device for a space rotating tether system, which relates to the field of on-orbit deployment, rotation, and rotation-maintaining motion stages of a space tether system; it includes a frame component, a drum component, a fixed load-bearing component and a movable load-bearing component, a bearing, and a motor bracket. The frame component is at the outermost layer of the device, supporting the size and protecting the stability of the deployment process; the drum component is at the center of the device, providing a spatial position for the tether to be coiled; the bearing is connected at the matching point of the frame and the drum component; the fixed load-bearing component is at the outermost layer of the device, ensuring stable and smooth deployment, providing an anchor point matching position and an external assembly point; the movable load-bearing component movably fixes the release end of the tether, initially in the drum groove to allow the tether to be stably coiled, and moves to the anchor point matching position at the end of deployment to form a large-load load-bearing component. The present invention solves the problems of unstable deployment process of large-diameter tethers and unstable large-load systems, and has the advantages of simple structure, strong reliability, and high secondary utilization rate.

Description

Technical Field

[0001] The present disclosure relates to the technical field of behavior detection, and in particular to a large-load tether deployment device for a space rotating tether system. Background Art

[0002] The space tether system refers to a space assembly connected by tethers. Compared with traditional spacecraft, the space tether system is reusable, flexible and low-cost. The space rotation tether system refers to a space tether system that rotates around the center of mass. Due to its unique structure and system characteristics, it has broad prospects in the fields of payload transmission, space debris cleaning, artificial gravity construction, high-altitude atmospheric detection, large-scale observation platform construction, deep space exploration, and low-cost orbit change.

[0003] At present, many studies have been conducted on the release device of the space tether system. Wu Hanling et al. of the Beijing Institute of Aerospace Systems Engineering designed a space tether release mechanism using shrapnel damping, which relies on multiple frictions between the shrapnel and the deceleration platform to brake and control the deployment of the tether (CN 109250155A). This device will produce large wear due to friction, the system cannot be reused, and the environmental adaptability is poor; Chu Zhongyi of the Beijing University of Aeronautics and Astronautics designed a large tether device that can be deployed, recovered, and tension controlled (CN 108415449A), but its disadvantages are complex structure and high space occupancy rate. In addition, the wedge brake mechanism of the space tether system designed by Northwestern Polytechnical University (CN 103241387A) and a small space tether system deployment brake mechanism using a spinning sleeve (CN 113044248A) have both conducted extensive and in-depth research on the deployment device of the space tether system.

[0004] However, there are few studies on the deployment devices involved in the space rotation tether system. During the rotation mission phase after the space rotation tether system deploys the tether, due to the large size and rotation characteristics of the space tether system, the tether is required to withstand a large tension. Therefore, the size of the tether in the actual mission is relatively large, and the characteristics of the tether itself, especially the torsion, will have a great impact on the deployment process. Secondly, due to the large tension of the tether during the rotation process, the tether deployment device is required to be able to withstand a large overload. Therefore, on the one hand, it is necessary to reduce the impact of the tether torsion on the deployment process, and on the other hand, the device strength must be higher to improve the reliability of the space tether system.

[0005] It should be noted that the information disclosed in the above background technology section is only used to enhance the understanding of the background of the present disclosure, and therefore may include information that does not constitute the prior art known to ordinary technicians in the field. Summary of the invention

[0006] The purpose of the present disclosure is to provide a large-load tether deployment device for a space rotating tether system, thereby overcoming the poor stability and low reliability caused by the limitations and defects of the relevant technology at least to a certain extent.

[0007] Other features and advantages of the present disclosure will become apparent from the following detailed description, or may be learned in part by the practice of the present disclosure.

[0008] The present disclosure provides a large-load tether deployment device for a space rotating tether system, comprising: a mother satellite, a daughter satellite, a tether, and a tether deployment device, wherein the load end of the tether is connected to the daughter satellite, and the release end is connected to the tether deployment device, and the tether deployment device is arranged in the mother satellite; the tether deployment device comprises:

[0009] a frame member fixed to the inner wall of the mother star;

[0010] A drum component is rotatably connected to the inside of the frame component, a slot is provided on the side wall of the drum component, a movable load-bearing component is clamped in the slot, and the release end of the tether is connected to the movable load-bearing component; the first section of the tether is located in the slot, the second section of the tether is wound around the side wall of the drum component, and the second section presses the first section into the slot; the load end of the tether passes through a side wall of the frame component and a side wall of the mother star in sequence, and extends to the outside of the mother star and is connected to the daughter star; the tether can move relative to the frame component and the mother star;

[0011] When the sub-satellite is completely released, the movable force-bearing component is separated from the reel component, and the movable force-bearing component is clamped on the frame component.

[0012] Optionally, the frame component includes:

[0013] A rear panel, the rear panel being in contact with a rear wall of a device cabin of the mother star;

[0014] The side plate is fixedly connected to the side wall of the rear panel; and the reel component is rotatably connected to the side plate.

[0015] Optionally, the frame component includes two side panels, one side panel is fixed to one end of the rear panel, and the other side panel is fixed to the other end of the rear panel, the two side panels are arranged opposite to each other, and the reel component is rotatably arranged between the two side panels.

[0016] Optionally, the reel component includes:

[0017] Roll body;

[0018] Roller side plates are fixed at both ends of the roll body, and there is a gap between the outer wall of the roll body and the side plates;

[0019] A reel shaft is inserted into the reel body, and its end portion extends to the outside of the reel side plate and is rotatably connected to the side plate;

[0020] A force transmission plate is coaxially sleeved on the outer side of the reel shaft, rotationally connected to the reel shaft, and fixedly connected to the reel side plate, and is used for transmitting force to the reel side plate so that the reel side plate drives the reel body to rotate with the reel shaft as the axis.

[0021] Optionally, the force transmission plate is rotatably connected to the reel shaft via a bearing.

[0022] Optionally, the reel component further includes:

[0023] The motor bracket is fixed on the outer side wall of the reel side plate, and a motor is installed on the motor bracket; the motor is connected to the force transmission plate and can drive the force transmission plate to rotate on the reel shaft.

[0024] Optionally, the frame component further includes:

[0025] A fixed load-bearing component is located at the end of the side panel and is used to lock the side panel on the rear panel.

[0026] Optionally, the fixed load-bearing component includes:

[0027] A load-bearing front panel is in contact with the side panel and is located at an end of the side panel where the rear panel is not installed; when the sub-star is fully released, the movable load-bearing component is clamped on the load-bearing front panel;

[0028] A load-bearing pull rod has one end connected to the load-bearing front panel and the other end connected to the rear panel, and the reel component is located between the load-bearing front panel and the rear panel.

[0029] Optionally, the movable load-bearing component includes:

[0030] A load-bearing block, wherein an installation groove matching the shape of the load-bearing block is provided at the edge of the clamping groove, and the load-bearing block is clamped in the installation groove;

[0031] A load-bearing pin is inserted into the load-bearing block, the load-bearing pin is clamped in the installation groove, and the length direction of the load-bearing pin is perpendicular to the length direction of the clamping groove. The load-bearing pin is used to limit the movement of the load-bearing block along the length direction of the clamping groove.

[0032] Optionally, a through hole is opened on the load-bearing front panel; the load end of the tether passes through the through hole and passes through a side wall of the mother star.

[0033] The present invention provides a large-load tether deployment device for a space rotating tether system, comprising: a mother satellite, a daughter satellite, a tether, and a tether deployment device, wherein the load end of the tether is connected to the daughter satellite, and the release end is connected to a movable load-bearing component in the tether deployment device, and the tether deployment device is arranged in the mother satellite; the tether deployment device comprises: a frame component fixed on the inner wall of the mother satellite; a drum component rotatably connected to the inside of the frame component, a slot is provided on the side wall of the drum component, a movable load-bearing component is clamped in the slot, and the release end of the tether is connected to the movable load-bearing component; a first section of the tether is located in the slot, a second section of the tether is wound around the side wall of the drum component, and the second section presses the first section into the slot; the load end of the tether passes through a side wall of the frame component and a side wall of the mother satellite in sequence, extends to the outside of the mother satellite, and is connected to the daughter satellite; the tether can move relative to the frame component and the mother satellite. When the sub-satellite is completely released, the movable force-bearing component is separated from the reel component, and the movable force-bearing component is clamped on the frame component.

[0034] By adopting the above scheme, the present invention has the following beneficial effects compared with the prior art:

[0035] 1. The adopted winch structure can make the most effective use of space, optimize the ratio of the device's rope length to the occupied space volume, and at the same time make the tether winding regular and reliable, reducing many stringent requirements on the tether. Based on the characteristics of the tether, the number of bends in the tether working condition is greatly reduced, which is beneficial to the storage and transportation of the device and ensures the stability of the state before deployment.

[0036] 2. The adopted winch structure and tangential rope output method can avoid the twisting of the tether during the deployment process to the greatest extent, weaken or even ignore the influence of the tether twisting on the deployment process, so as to ensure a smooth deployment process.

[0037] 3. The movable anchor point technology adopted moves the anchor point from the winch shaft to the rope outlet end after deployment, abandoning the design idea of ​​setting the fixed anchor point of the tether on the drum body in the classic sense, greatly reducing the strength requirements of the drum shaft and bearings, and reducing the size, weight, moment of inertia and damping torque of the drum components, so that the device can stably withstand large overloads during rotation and improve system reliability.

[0038] 4. The design of the movable load-bearing component adopts a load-bearing block and a load-bearing pin structure to avoid the tether being squeezed against the load-bearing front panel wall at the anchor point, which affects the stability and strength failure of the tether.

[0039] 5. The materials used are resistant to high and low temperatures and have high strength. The bearings are ceramic bearings, and the open structure is suitable for various environments.

[0040] It is to be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] The accompanying drawings herein are incorporated into the specification and constitute a part of the specification, illustrate embodiments consistent with the present disclosure, and together with the specification are used to explain the principles of the present disclosure. Obviously, the accompanying drawings described below are only some embodiments of the present disclosure, and for ordinary technicians in this field, other accompanying drawings can be obtained based on these accompanying drawings without creative work.

[0042] Figure 1 is a schematic diagram of the large load-bearing tether deployment device provided by the present invention installed on the space tether system;

[0043] Figure 2 It is a schematic diagram of the overall internal structure of the large load-bearing tether deployment device provided by the present invention;

[0044] Figure 3 It is an exploded view of the large load-bearing tether deployment device provided by the present invention;

[0045] Figure 4 It is a schematic diagram of the structure of the frame components of the large load-bearing tether deployment device provided by the present invention;

[0046] Figure 5 It is a schematic diagram of the structure of the drum component of the large-load tether deployment device provided by the present invention;

[0047] Figure 6 It is a schematic diagram of the structure of the load-bearing components of the large-load tether deployment device provided by the present invention;

[0048] Figure 7 Schematic diagram A of the working process of the large load-bearing tether deployment device provided by the present invention;

[0049] Figure 8 Schematic diagram B of the working process of the large load-bearing tether deployment device provided by the present invention;

[0050] Fig. 9 Schematic diagram C of the working process of the large load-bearing tether deployment device provided by the present invention;

[0051] Fig.10 Schematic diagram D of the working process of the large-load tether deployment device provided by the present invention.

[0052] In the figure: 1. mother satellite, 2. satellite, 3. tether, 4. device cabin, 5. tether deployment device, 6. rear panel, 7. side panel, 8. drum body, 9. drum side panel, 10. drum shaft, 11. force transmission plate, 12. load-bearing front panel, 13. load-bearing pull rod, 14. load-bearing block, 15. load-bearing pin, 16. bearing, 17. motor base. DETAILED DESCRIPTION

[0053] Example embodiments will now be described more fully with reference to the accompanying drawings. However, example embodiments can be implemented in a variety of forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that the disclosure will be more comprehensive and complete and to fully convey the concepts of the example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.

[0054] In addition, the accompanying drawings are only schematic illustrations of the present disclosure and are not necessarily drawn to scale. The same reference numerals in the figures represent the same or similar parts, and their repeated description will be omitted. Some of the block diagrams shown in the accompanying drawings are functional entities and do not necessarily correspond to physically or logically independent entities. These functional entities can be implemented in software form, or implemented in one or more hardware modules or integrated circuits, or implemented in different networks and / or processor devices and / or microcontroller devices.

[0055] The block diagrams shown in the accompanying drawings are merely functional entities and do not necessarily correspond to physically independent entities. That is, these functional entities may be implemented in software form, or in one or more hardware modules or integrated circuits, or in different networks and / or processor devices and / or microcontroller devices.

[0056] The flowcharts shown in the accompanying drawings are only exemplary and do not necessarily include all the contents and operations / steps, nor must they be executed in the order described. For example, some operations / steps can be decomposed, and some operations / steps can be combined or partially combined, so the actual execution order may change according to actual conditions.

[0057] With the increasing demand for space experiments, space missions have put forward cost restrictions on various devices. As the feasibility of space tether systems is continuously verified and on-orbit experiments are continuously carried out in an orderly manner, higher requirements are put forward for each component of the space tether system. In order to avoid the deficiencies of the prior art and meet the above needs, the present invention proposes a large-load tether deployment device for a space rotating tether system. The device has a simple structure, low space occupancy, strong reliability, and reliable deployment. The device is installed at the connection between the mother satellite 1 and the satellite 2 of the space tether system, which can ensure the stability of the system before the mission is executed; it can ensure the smooth execution and smooth end of the deployment process through motor control, and avoid the impact caused by the end of the deployment; the hoisting structure of the device can minimize the influence of the torsion of the tether 3 on the deployment process; the movable anchor point technology adopted by the device can ensure that the problem of the strength of the hoisting shaft is difficult to withstand large overloads is solved.

[0058] The present invention provides a large-load tether deployment device for a space rotating tether system, comprising: a mother satellite 1, a daughter satellite 2, a tether 3, and a tether deployment device 5, wherein the load end of the tether 3 is connected to the daughter satellite 2, and the release end is connected to the tether deployment device 5, and the tether deployment device 5 is arranged in the mother satellite 1; the tether deployment device 5 comprises: a frame component, which is fixed on the inner wall of the mother satellite 1; a drum component, which is rotatably connected to the inside of the frame component, a slot is provided on the side wall of the drum component, a movable load-bearing component is clamped in the slot, and the release end of the tether 3 is connected to the movable load-bearing component. The tether 3 is connected with the sub-satellite 2 by a force component; the first section of the tether 3 is located in the slot, the second section of the tether 3 is wound around the side wall of the drum component, and the second section presses the first section into the slot; the load end of the tether 3 passes through a side wall of the frame component and a side wall of the mother star 1 in sequence, and extends to the outside of the mother star 1, and is connected to the sub-satellite 2; the tether 3 can move relative to the frame component and the mother star 1; when the sub-satellite 2 is completely released, the movable force-bearing component is separated from the drum component, and the movable force-bearing component is clamped on the frame component.

[0059] In this example implementation, a large-load tether deployment device for a space rotating tether system includes a tether deployment device 5 having a frame component, a drum component, a bearing 16, a motor bracket, a fixed load-bearing component and a movable load-bearing component to ensure the stability of the deployment process and the rotation process.

[0060] The frame component includes a side plate 7 and a rear panel 6, which are located at the outermost layer of the entire device. The side plate 7 and the rear panel 6 are fixedly connected by screws, and the frame component is fixedly connected to the fixed load-bearing component by screws and bolt nut structures. The rear of the rear panel 6 contains an external assembly matching hole. The side plate 7 is matched with the reel component through a bearing 16, and the side plate 7 contains a hole for installing a motor base 17.

[0061] The reel component includes a reel body 8, a reel side plate 9, a reel shaft 10 and a force transmission plate 11, which are located at the center of the entire device. The middle part of the reel body 8 has an axial single-layer rope groove and a groove that provides an initial position for the movable load-bearing component, so the innermost tether 3 walks out of the rope groove and goes to both sides, and walks out from the slope, and completes the rope winding along the slope direction to ensure the stability of the winding state of the tether 3. The reel body 8 is fixedly connected to the reel side plate 9 by screws, and the reel shaft 10 is flattened by the shaft head and fixedly connected to the reel body 8 through the force transmission plate 11 and screws, providing a force transmission structure for motor drive control.

[0062] The bearing 16 is a ceramic bearing 16, which is located at the joint between the drum component and the frame component. Its service life is much longer than that of the metal bearing 16, and it has a low friction coefficient and does not contain lubricant, which is conducive to overcoming the harsh environment such as high and low temperatures during task execution. It has a high elastic modulus and its rigidity is 15-20% greater than that of the metal bearing 16. It has better corrosion resistance and wear resistance, which improves the reliability of the device, is more conducive to transportation and storage, and cooperates with the effective implementation of the task.

[0063] The fixed load-bearing component is composed of a load-bearing front panel 12 and a load-bearing pull rod 13, which are both located in the outermost layer of the entire device. The load-bearing front panel 12 is located at the front end of the entire device, and the rope hole contains an anchor point matching position after the unfolding is completed, ensuring the stability of the rope output direction, smooth unfolding and stable rotation. The load-bearing pull rods 13 are located on both sides of the device, with a total of four on both sides, providing an assembly point with the outside at the rear end.

[0064] The movable load-bearing component is composed of a load-bearing block 14 and a load-bearing pin 15. The load-bearing block 14 and the load-bearing pin 15 cooperate to fix the release end of the tether 3 in the movable load-bearing component. The movable load-bearing component is initially located in the groove of the drum. After the deployment is completed, it moves with the release end of the tether 3 to the anchor point matching position provided by the fixed load-bearing component to form a load-bearing component together, thereby ensuring the stable operation of the device in subsequent tasks.

[0065] In a specific embodiment, the frame component includes: a rear panel 6, which is in contact with the rear wall of the device cabin 4 of the mother satellite 1; a side panel 7, which is fixedly connected to the side wall of the rear panel 6; and the reel component is rotatably connected to the side panel 7.

[0066] In a specific embodiment, the frame component includes two side panels 7, one side panel 7 is fixed to one end of the rear panel 6, and the other side panel 7 is fixed to the other end of the rear panel 6, the two side panels 7 are arranged opposite to each other, and the reel component is rotatably arranged between the two side panels 7.

[0067] In a specific embodiment, the reel component includes: a reel body 8; a reel side plate 9, which is fixed at both ends of the reel body 8, and there is a gap between the outer wall thereof and the side plate 7; a reel shaft 10, which is inserted into the interior of the reel body 8, and its end extends to the outside of the reel side plate 9, and is rotatably connected to the side plate 7; a force transmission plate 11, which is coaxially sleeved on the outside of the reel shaft 10, is rotatably connected to the reel shaft 10, and is fixedly connected to the reel side plate 9, and is used to transmit force to the reel side plate 9, so that the reel side plate 9 drives the reel body 8 to rotate with the reel shaft 10 as the axis.

[0068] In a specific embodiment, the force transmission plate 11 is rotatably connected to the reel shaft 10 via a bearing 16 .

[0069] In a specific embodiment, the reel component also includes: a motor base 17, fixed on the outer wall of the reel side plate 9, on which a motor is installed; the motor drive is connected to the force transmission plate 11, and can drive the force transmission plate 11 to rotate on the reel shaft 10.

[0070] In a specific embodiment, the frame component further includes: a fixed load-bearing component, located at the end of the side panel 7 , for locking the side panel 7 on the rear panel 6 .

[0071] In a specific embodiment, the fixed load-bearing component includes: a load-bearing front panel 12, which is in contact with the side panel 7 and is located at the end of the side panel 7 where the rear panel 6 is not installed; when the sub-star 2 is fully released, the movable load-bearing component is clamped on the load-bearing front panel 12; a load-bearing pull rod 13, one end of which is connected to the load-bearing front panel 12 and the other end is connected to the rear panel 6, and the roller component is located between the load-bearing front panel 12 and the rear panel 6.

[0072] In a specific embodiment, the movable load-bearing component includes: a load-bearing block 14, an installation groove adapted to the shape of the load-bearing block 14 is opened on the edge of the slot, and the load-bearing block 14 is clamped in the installation groove; a load-bearing pin 15, inserted in the load-bearing block 14, the load-bearing pin 15 is clamped in the installation groove, and the length direction of the load-bearing pin 15 is perpendicular to the length direction of the slot, and the load-bearing pin 15 is used to limit the movement of the load-bearing block 14 along the length direction of the slot.

[0073] In a specific implementation, a through hole is opened on the load-bearing front panel 12 ; the load end of the tether 3 passes through the through hole and passes through a side wall of the mother star 1 .

[0074] The present invention provides a large-load tether deployment device for a space rotating tether system, comprising: a mother satellite 1, a daughter satellite 2, a tether 3, and a tether deployment device 5, wherein the load end of the tether 3 is connected to the daughter satellite 2, and the release end is connected to the tether deployment device 5, and the tether deployment device 5 is arranged in the mother satellite 1; the tether deployment device 5 comprises: a frame component, fixed on the inner wall of the mother satellite 1; a drum component, rotatably connected to the inside of the frame component, a card slot is opened on the side wall of the drum component, and a card slot is arranged in the card slot. A movable load-bearing component is clamped, and the release end of the tether 3 is connected to the movable load-bearing component; the first section of the tether 3 is located in the clamping slot, the second section of the tether 3 is wound on the side wall of the reel component, and the second section presses the first section into the clamping slot; the load end of the tether 3 passes through a side wall of the frame component and a side wall of the mother star 1 in sequence, and extends to the outside of the mother star 1, and is connected to the sub-satellite 2; the tether 3 can move relative to the frame component and the mother star 1. When the sub-satellite 2 is completely released, the movable load-bearing component is separated from the reel component, and the movable load-bearing component is clamped on the frame component.

[0075] By adopting the above scheme, the present invention has the following beneficial effects compared with the prior art:

[0076] 1. The adopted winch structure can make the most effective use of space, optimize the ratio of the device's rope length to the occupied space volume, and at the same time make the winding regularity of the tether 3 reliable, reducing many stringent requirements on the tether 3. Based on the characteristics of the tether 3, the number of bends in the working condition of the tether 3 is greatly reduced, which is beneficial to the storage and transportation of the device and ensures the stability of the state before deployment.

[0077] 2. The adopted winch structure and tangential rope discharging method can avoid the twisting of the tether 3 during the deployment process to the greatest extent, and reduce or even ignore the influence of the twisting of the tether 3 on the deployment process, so as to ensure a smooth deployment process.

[0078] 3. The movable anchor point technology adopted moves the anchor point from the winch shaft to the rope outlet end after deployment, abandoning the design idea of ​​setting the fixed anchor point of the tether 3 on the drum body 8 in the classic sense, greatly reducing the strength requirements of the drum shaft 10 and the bearing 16, and reducing the size, weight, moment of inertia and damping torque of the drum components, so that the device can stably withstand large overloads during rotation, thereby improving system reliability.

[0079] 4. The design of the movable load-bearing component adopts the structure of the load-bearing block 14 and the load-bearing pin 15, which avoids the tether 3 being squeezed by the wall of the load-bearing front panel 12 at the anchor point, affecting the stability and strength failure of the tether 3.

[0080] 5. The material used is resistant to high and low temperatures and has high strength. The bearing 16 is a ceramic bearing 16, and the open structure is suitable for various environments.

[0081] Example 2

[0082] Based on the above embodiment 1, this embodiment is combined with the attached Figure 1-10 The technical solution of this application is further described in detail:

[0083] This embodiment provides a large-load tether deployment device for a space rotating tether system, which is installed on a single-end star of the space tether system. It includes a frame component, a drum component, a bearing 16, a motor base 17, a fixed load-bearing component and a movable load-bearing component. Among them, the frame component includes a side plate 7 and a rear panel 6, the drum component includes a drum body 8, a drum side plate 9, a drum shaft 10 and a force transmission plate 11, the fixed load-bearing component includes a load-bearing front panel 12 and a load-bearing pull rod 13, and the movable load-bearing component includes a load-bearing block 14 and a load-bearing pin 15.

[0084] In a specific embodiment, the frame component includes a side panel 7 and a rear panel 6, and the side panel 7 and the rear panel 6 are fixedly connected by screws. The frame component is fixedly connected to the movable load-bearing component by a screw and bolt nut structure, and cooperates with the reel component through a bearing 16. The side panel 7 contains a hole for installing a motor bracket 17.

[0085] In a specific embodiment, the drum component includes a drum body 8, a drum side plate 9, a drum shaft 10 and a force transmission plate 11, which is located at the center of the entire device. The middle part of the drum body 8 has an axial single-layer rope-passing groove and a groove that provides an initial position for the movable load-bearing component to ensure that the winding state of the tether 3 is stable. The drum body 8 is fixedly connected to the drum side plate 9 by screws, and the drum shaft 10 is fixedly connected to the drum body 8 by the force transmission plate 11 and screws, providing a force conduction structure for motor drive control.

[0086] In a specific embodiment, the bearing 16 is a ceramic bearing, which is located at the joint of the drum component and the frame component, which is conducive to overcoming the harsh environment such as high and low temperatures during task execution, improving the reliability of the system, and cooperating with the effective implementation of the task.

[0087] In a specific embodiment, the fixed load-bearing component is composed of a load-bearing front panel 12 and a load-bearing pull rod 13, which are both in the outermost layer of the entire device. The load-bearing front panel 12 is located at the front end of the entire device, and the rope hole contains an anchor point matching position after the unfolding is completed, to ensure the stability of the rope output direction, smooth unfolding and stable rotation. The load-bearing pull rods 13 are located on both sides of the device, with a total of four on both sides, and an assembly point with the outside is provided at the rear end.

[0088] In a specific embodiment, the movable load-bearing component is composed of a load-bearing block 14 and a load-bearing pin 15. The load-bearing block 14 and the load-bearing pin 15 cooperate to fix the release end of the tether 3 in the movable load-bearing component. The movable load-bearing component is initially located in the groove of the drum. After the deployment is completed, it moves with the release end of the tether 3 to the anchor point matching position provided by the fixed load-bearing component to form a load-bearing component together, thereby ensuring the stable operation of the system in subsequent tasks.

[0089] In a specific embodiment, the frame components, reel body 8, reel side plate 9, and motor bracket are made of aluminum-6061, the reel shaft 10 is made of stainless steel 440C, the force transmission plate 11 is made of stainless steel austenite, and the load-bearing components are made of stainless steel 0Cr17Ni4Cu4Nb.

[0090] In a specific embodiment, Figure 1 As shown, the mother planet 1, the daughter planet 2, and the tether constitute a space tether system, and a tether deployment device 5 is installed in the device cabin 4 of the mother planet 1; before using the tether system to perform a space experiment, the tether 3 is coiled in the tether deployment device 5, and with the start of the deployment mission, the daughter planet 2 obtains an initial velocity, and gradually moves away from the mother planet 1 with the load end of the tether 3. During the deployment process, the tether deployment device 5 is braked, and when the tether 3 is fully deployed, the deployment speed is controlled to be braked to zero at the same time.

[0091] like Figure 2 As shown, this embodiment is composed of a frame component, a drum component, a fixed load-bearing component, a movable load-bearing component, a bearing 16, and a motor bracket 17. The frame component is fitted on the rear wall of the device cabin 4 along the corresponding hole position. The drum component is assembled in the frame component through the bearing 16, and the drum component can rotate relatively in the tether deployment device 5. The motor bracket 17 is fixedly connected to one side of the frame component by screws. The fixed load-bearing component is fixedly connected to the frame component by screws, and the assembly point at the rear end of the fixed load-bearing component is installed with nuts at the corresponding hole positions on the rear wall of the device cabin 4 of the mother satellite 1.

[0092] like Figure 3 As shown, in this embodiment, the frame component is composed of a rear panel 6 and a side panel 7. The rear panel 6 and the side panel 7 are fixedly connected by screws.

[0093] like Figure 4 As shown, the reel component in this embodiment is composed of a reel body 8, a reel side plate 9, a reel shaft 10, and a force transmission plate 11. The reel body 8 is fixedly connected to the reel side plate 9 by screws, and the reel shaft 10 is fixedly connected to the reel side plate 9 by screws through the holes of the force transmission plate 11.

[0094] like Figure 5As shown, in this embodiment, the fixed load-bearing assembly is composed of a load-bearing front panel 12 and a load-bearing rod 13, and the movable load-bearing assembly is composed of a load-bearing block 14 and a load-bearing rod 15. The load-bearing rod 13 passes through the hole of the load-bearing front panel 12 and is connected together, and the load-bearing block 14 and the load-bearing pin 15 are connected together through the card slot, and the release end of the tether 3 is fixed in the movable load-bearing assembly.

[0095] The specific working process is as follows:

[0096] like Figures 7-10 As shown, according to the three states of the movable load-bearing components, it is divided into four process stages: A, B, C, and D:

[0097] A. Before the deployment task is executed, the release end of the tether 3 is fixed in the movable load-bearing component, the movable load-bearing component is placed in the groove of the drum body 8, and the tether 3 is regularly coiled on the drum component. The drum component is in a locked state before release to ensure the stability of the state during transportation and storage. When the deployment task is executed, the drum component starts to rotate, and the satellite 2 obtains a large initial velocity. The satellite 2 drives the tether 3 to deploy, and the shaft cylinder component rotates at the same time. The movable load-bearing component is always in the groove of the drum body 8 and rotates with the drum component;

[0098] B. At the end of the deployment task, the rotation speed of the drum component is continuously braked, so that the deployment speed is controlled, and the coiled part of the tether 3 on the drum component is completely released, and finally the end of the tether 3 is driven to separate from the axial single-layer rope groove on the drum body 8, which can effectively avoid the rebound effect caused by the tether 3 after the deployment is completed;

[0099] C. The released end of the tether 3 drives the movable load-bearing component to leave the groove of the reel body 8, and slowly moves to the anchor point matching position of the load-bearing front panel 12, and finally forms a large load-bearing structure at the anchor point matching position.

[0100] D. Before the rotation task is executed, the large load-bearing components have been formed, thereby achieving the effect of separating the load-bearing parts from the reel components with lower tensile strength, forming a rigid connection device that can withstand large overloads, and achieving the large load-bearing target of subsequent rotation tasks.

[0101] In addition, the above-mentioned figures are only schematic illustrations of the processes included in the method according to an exemplary embodiment of the present invention, and are not intended to be limiting. It is easy to understand that the processes shown in the above-mentioned figures do not indicate or limit the time sequence of these processes. In addition, it is also easy to understand that these processes can be performed synchronously or asynchronously, for example, in multiple modules.

[0102] Those skilled in the art will readily appreciate other embodiments of the present disclosure after considering the specification and practicing the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the present disclosure that follow the general principles of the present disclosure and include common knowledge or customary technical means in the art that are not disclosed in the present disclosure. The specification and examples are to be considered as exemplary only, and the true scope and spirit of the present disclosure are indicated by the claims.

[0103] It should be understood that the present disclosure is not limited to the exact structures that have been described above and shown in the drawings, and that various modifications and changes may be made without departing from the scope thereof. The scope of the present disclosure is limited only by the appended claims.

Claims

1. A large-load tether deployment device for a space-oriented rotating tether system, comprising: A mother satellite (1), a daughter satellite (2), a tether (3), and a tether deployment device (5), wherein the load end of the tether (3) is connected to the daughter satellite (2), and the release end is connected to a movable load-bearing component in the tether deployment device (5), and the tether deployment device (5) is arranged in the mother satellite (1); characterized in that the tether deployment device (5) comprises: A frame component fixed on the inner wall of the mother star (1); A drum component is rotatably connected to the interior of the frame component; a slot is provided on the side wall of the drum component, a movable load-bearing component is clamped in the slot, and the release end of the tether (3) is connected to the movable load-bearing component; a first section of the tether (3) is located in the slot, a second section of the tether (3) is wound around the side wall of the drum component, and the second section presses the first section into the slot; the load end of the tether (3) passes through a side wall of the frame component and a side wall of the mother satellite (1) in sequence, and extends to the outside of the mother satellite (1), and is connected to the sub-satellite (2); the tether (3) can move relative to the frame component and the mother satellite (1); When the sub-star (2) is completely released, the movable force-bearing component is separated from the reel component, and the movable force-bearing component is clamped on the frame component.

2. The large-load tether deployment device for a space-oriented rotating tether system according to claim 1, characterized in that: The frame components include: A rear panel (6), the rear panel (6) being in contact with a rear wall of a device cabin (4) of the mother satellite (1); The side plate (7) is fixedly connected to the side wall of the rear panel (6); and the reel component is rotatably connected to the side plate (7).

3. The large load-bearing tether deployment device for a space-oriented rotating tether system according to claim 2, characterized in that: The frame component comprises two side panels (7), one side panel (7) is fixed to one end of the rear panel (6), and the other side panel (7) is fixed to the other end of the rear panel (6), the two side panels (7) are arranged opposite to each other, and the reel component is rotatably arranged between the two side panels (7).

4. The large load-bearing tether deployment device for a space-oriented rotating tether system according to claim 2, characterized in that: The reel component comprises: Roll body (8); Roller side plates (9) are fixed at both ends of the roll body (8), and a gap exists between the outer wall of the roll side plates (9) and the side plates (7); A reel shaft (10) is inserted into the interior of the reel body (8), and its end portion extends to the outside of the reel side plate (9) and is rotatably connected to the side plate (7); A force transmission plate (11) is coaxially sleeved on the outer side of the reel shaft (10), rotationally connected to the reel shaft (10), and fixedly connected to the reel side plate (9), and is used for transmitting force to the reel side plate (9), so that the reel side plate (9) drives the reel body (8) to rotate around the reel shaft (10) as the axis.

5. The large load-bearing tether deployment device for a space-oriented rotating tether system according to claim 4, characterized in that: The force transmission plate (11) is rotationally connected to the reel shaft (10) via a bearing (16).

6. The large load-bearing tether deployment device for a space-oriented rotating tether system according to claim 4, characterized in that: The reel component also includes: A motor bracket (17) is fixed on the outer side wall of the reel side plate (9) and is provided with a motor; the motor is connected to the force transmission plate (11) and can drive the force transmission plate (11) to rotate on the reel shaft (10).

7. The large load-bearing tether deployment device for a space-oriented rotating tether system according to claim 3, characterized in that: The frame component also includes: A fixed load-bearing component is located at the end of the side panel (7) and is used to lock the side panel (7) onto the rear panel (6).

8. The large load-bearing tether deployment device for a space-oriented rotating tether system according to claim 7, characterized in that: The fixed load-bearing component comprises: A load-bearing front panel (12) is in contact with the side panel (7) and is located at an end of the side panel (7) where the rear panel (6) is not installed; when the sub-satellite (2) is completely released, the movable load-bearing component is clamped on the load-bearing front panel (12); A load-bearing pull rod (13) has one end connected to the load-bearing front panel (12) and the other end connected to the rear panel (6); the reel component is located between the load-bearing front panel (12) and the rear panel (6).

9. The large load-bearing tether deployment device for a space-oriented rotating tether system according to claim 1, characterized in that: The movable load-bearing component comprises: A load-bearing block (14) is provided at the edge of the clamping slot with a mounting groove adapted to the shape of the load-bearing block (14), and the load-bearing block (14) is clamped in the mounting groove; A load-bearing pin (15) is inserted into the load-bearing block (14), the load-bearing pin (15) is clamped in the installation groove, and the length direction of the load-bearing pin (15) is perpendicular to the length direction of the clamping groove. The load-bearing pin (15) is used to limit the movement of the load-bearing block (14) along the length direction of the clamping groove.

10. The large load-bearing tether deployment device for a space-oriented rotating tether system according to claim 8, characterized in that: A through hole is provided on the load-bearing front panel (12); the load end of the tether (3) passes through the through hole and penetrates a side wall of the mother star (1).

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