A multifunctional space debris capture device

Abstract

The present invention relates to the field of space debris capture technology, and more specifically, to a multifunctional space debris capture device, comprising a satellite housing, a drive assembly disposed outside the satellite housing, and a capture assembly connected to the drive assembly; the satellite housing is also provided with a storage bin and a clamping robotic arm, the storage bin being provided with a storage cavity, and the clamping robotic arm being used to grab space debris captured by the capture assembly into the storage cavity. The present invention overcomes the shortcomings of the prior art, which require the use of an additional recovery device to recover space debris captured by the capture mechanism, resulting in higher equipment costs and lower space debris recovery efficiency. By combining the capture assembly, the storage bin, and the robotic arm, the present invention utilizes the robotic arm to grab space debris captured by the capture assembly into the storage bin for storage and recovery, thereby not only reducing equipment costs but also improving space debris recovery efficiency.

Description

Technical Field

[0001] The present invention relates to the technical field of space debris capture, and more particularly, to a multifunctional space debris capture device. Background Art

[0002] Currently, space debris in low-Earth orbit is growing exponentially. High-speed debris can collide with spacecraft's solar panels, optical components, and other components, potentially causing structural material to detach or even render the entire spacecraft useless. Therefore, the capture and removal of space debris is a critical technology urgently needed in the field of space technology.

[0003] The prior art discloses a cage-type device for capturing non-cooperative space debris and its working method. The device includes a ball cage, a leveling frame assembly, a connector, and a robotic arm. The ball cage includes a cage cover and a cage body. When the cage cover is opened, the cage body opening allows debris to enter, and the cage cover is closed in time to prevent the debris from escaping. The debris is captured without having to identify the specific posture of the non-cooperative debris.

[0004] After capturing space debris, the aforementioned technical solution requires additional recovery equipment to remove the debris from the cage and transfer it to another location for storage, allowing the cage to continue capturing the debris and facilitate its recovery. However, using separate equipment for capturing and recovering space debris not only increases equipment costs but also reduces the efficiency of space debris recovery. Summary of the Invention

[0005] In response to the problem that the above-mentioned prior art requires the additional use of a recovery device to recover the space debris captured by the capture mechanism, resulting in higher equipment costs and lower space debris recovery efficiency, the present invention provides a multifunctional space debris capture device, which has the functions of capturing and recovering space debris and can recover space debris after capturing it.

[0006] In order to solve the above technical problems, the technical solution provided by the present invention is:

[0007] A multifunctional space debris capture device comprises a satellite shell, a drive assembly arranged outside the satellite shell and a capture assembly connected to the drive assembly, the capture assembly comprising an intermediate panel, a plurality of shell petal assemblies being rotatably connected to the intermediate panel, the drive assembly being used to drive the shell petal assemblies to rotate relative to the intermediate panel so that the ends of the shell petal assemblies move closer to or away from each other; when the ends of the shell petal assemblies move closer to each other, a accommodating cavity for accommodating space debris is formed between the shell petal assembly and the intermediate panel; the satellite shell is also provided with a storage bin for placing space debris and a clamping robotic arm, the storage bin is provided with a storage cavity, and the clamping robotic arm is used to grab the space debris in the accommodating cavity into the storage cavity.

[0008] In the above technical solution, in the initial state, the ends of the multiple shell petal assemblies are separated from each other, and the shell petal assemblies are in an expanded state; when the space debris approaches the inner side of the shell petal assembly and is located within the envelope of the accommodating cavity, the driving assembly drives the ends of the shell petal assemblies to move closer together, so that the shell petal assemblies close and form an accommodating cavity, thereby enclosing the space debris in the accommodating cavity, thus completing the capture of the space debris. After the space debris is stabilized in the accommodating cavity, the driving assembly then drives the ends of the shell petal assemblies to gradually move away from each other to open the accommodating cavity and expose the space debris; the clamping robot arm then extends to the space debris and grabs the space debris into the storage cavity for storage, thus completing the recovery of the space debris.

[0009] It can be understood that the inner side of the middle panel and the shell petal assembly refers to the side where the accommodating cavity is located, and the outer side refers to the side opposite to the accommodating cavity.

[0010] Preferably, the satellite housing has an inner cavity and a through-hole communicating with the inner cavity. A linear drive mechanism is disposed within the inner cavity, and the storage bin is connected to the power output of the linear drive mechanism. The linear drive mechanism is configured to drive the storage bin to translate in and out of the inner cavity through the through-hole. After the gripping robotic arm grasps the space debris, the linear drive mechanism drives the storage bin through the through-hole from inside the inner cavity to outside the inner cavity. The gripping robotic arm then places the space debris into the storage cavity. The linear drive mechanism then drives the storage bin from outside the inner cavity to inside the inner cavity. This protects the space debris from external interference and damage by the satellite housing, while also reducing the overall size of the entire device.

[0011] Preferably, the storage bin is slidably connected to the satellite shell, and the linear drive mechanism is used for sliding the storage bin, so that the storage bin can enter and exit the inner cavity in a more stable state, avoiding vibration transmission and causing space debris to escape from the storage bin.

[0012] The linear drive mechanism can be a pneumatic cylinder, an electric push rod, a rack and pinion drive mechanism, a linear motor drive mechanism, a synchronous belt drive mechanism, or the like. Preferably, the linear drive mechanism includes a linear motor, which is mounted on the inner wall of the inner cavity, and whose output shaft is connected to the storage bin. Using a linear motor to drive the movement of the storage bin offers advantages such as high precision, high response speed, low vibration, ease of control, and long life, thereby improving the efficiency of space debris recovery.

[0013] Preferably, the clamping robotic arm includes a fixed arm connected to the satellite shell, a first rotation drive assembly arranged on the fixed arm, a first spiral arm rotatably connected to the fixed arm, a second rotation drive assembly arranged on the first spiral arm, a second spiral arm rotatably connected to the first spiral arm, a third rotation drive assembly arranged on the second spiral arm, a third spiral arm rotatably connected to the second spiral arm, a fourth rotation drive assembly arranged on the third spiral arm, and a clamping assembly rotatably connected to the third spiral arm and used to clamp space debris; the axis of the first spiral arm is parallel to the axes of the fixed arm and the second spiral arm, and the first rotation drive assembly is used to drive the first spiral arm to rotate around its own axis; the second rotation drive assembly is used to drive the second spiral arm to rotate around an axis perpendicular to its own axis; the third rotation drive assembly is used to drive the third spiral arm to rotate around an axis perpendicular to its own axis; the fourth rotation drive assembly is used to drive the clamping assembly to rotate around the axis of the third spiral arm. It can be understood that such a clamping robot arm is a five-degree-of-freedom robot arm, and the range of motion of the clamping component is relatively wide. The position and clamping angle of the clamping component can be flexibly adjusted by rotating the first rotary arm, the second rotary arm, the third rotary arm and the clamping component, thereby clamping space debris in multiple positions, which is conducive to improving the success rate and efficiency of space debris recovery.

[0014] Preferably, the shell petal assemblies are distributed circumferentially on the middle panel; the drive assembly includes a driver and a telescopic assembly arranged on the satellite shell, the driver is provided with a fixed portion, one end of the telescopic assembly is connected to the fixed portion, and the other end is connected to the shell petal assembly; the driver is used to drive the telescopic assembly to extend and retract, and when the telescopic assembly is extended, the ends of the shell petal assemblies move closer to each other, and when the telescopic assembly is shortened, the ends of the shell petal assemblies move away from each other. It can be understood that when the telescopic assembly is extended, one end of the telescopic assembly applies a thrust to the shell petal assembly, and the thrust can push the shell petal assembly to rotate toward the inner side of the middle panel, so that the ends of the shell petal assembly move closer to each other, and finally form a accommodating cavity with the middle panel. The shell petal assembly is driven to expand or close by the extension and retraction of the telescopic assembly. This driving method is more flexible and safe, and is also conducive to simplifying the structure of the entire capture mechanism.

[0015] Preferably, the telescopic assembly includes a first joint, a second joint, and a first pusher, wherein the first joint and the second joint are rotationally connected and both are rotationally connected to the fixed portion and the first pusher, respectively, and the first pusher is rotationally connected to the outer side of the shell petal assembly; the rotation axis of the first joint relative to the fixed portion and the rotation axis of the second joint relative to the first pusher are both perpendicular to the rotation axis of the second joint relative to the first joint, and the rotation axis of the first pusher relative to the shell petal assembly is perpendicular to the rotation axis of the second joint relative to the first pusher; the driver is used to drive the intermediate panel to rotate, the rotation axis of the intermediate panel being perpendicular to the rotation axis of the first joint relative to the fixed portion, and when the intermediate panel rotates, the second joint rotates relative to the first joint to extend or shorten the telescopic assembly. When the driver drives the intermediate panel to rotate, the second joint rotates relative to the first joint, and at the same time, the first joint rotates relative to the fixed portion, the second joint rotates relative to the first pusher, and the first pusher rotates relative to the shell petal assembly, thereby causing the telescopic assembly to reach an extended state; during the extension of the telescopic assembly, the second joint applies a driving force to the shell petal assembly through the first pusher, thereby driving the shell petal assembly to rotate toward the inner side of the intermediate panel. By driving the middle panel to rotate, the ends of the shell petal assembly can be brought closer to each other. Such a drive assembly structure and its drive method are more flexible and simple, which not only helps to reduce the weight of the entire mechanism and reduce the manufacturing cost and maintenance cost of the mechanism, but also makes it easier to control the mechanism movement, making the task more smoothly.

[0016] Preferably, the shell valve assembly includes a first panel and a second panel rotatably connected to the middle panel, the middle panel, the first panel and the second panel are all regular pentagonal panels, one side of the first panel is rotatably connected to one side of the middle panel, the second panel is located on the side of the first panel opposite to the middle panel, and is rotatably connected to the first panel; one side of the second panel is connected to a third panel in the shape of an isosceles triangle, and the third panel is located on the side of the second panel opposite to the first panel; the first pushing member is rotatably connected to the middle part of the outer side of the first panel.

[0017] Furthermore, the telescopic assembly also includes a third joint, a fourth joint and a second pushing member, the third joint is rotatably connected to the fourth joint and both are rotatably connected to the first pushing member and the second pushing member respectively; the second pushing member is rotatably connected to the middle part of the outer side of the second panel; the rotation axis of the third joint relative to the first pushing member and the rotation axis of the fourth joint relative to the second pushing member are both perpendicular to the rotation axis of the fourth joint relative to the third joint; when the middle panel rotates, the first panel, the second panel, the third panel and the middle panel can form a closed accommodating cavity.

[0018] During the rotation of the middle panel, the first joint rotates relative to the fixed portion, the first joint rotates relative to the second joint, the second joint rotates relative to the first pusher, and the first pusher rotates relative to the first panel, so that the telescopic assembly is extended, and the first panel is pushed to rotate toward the inner side of the middle panel by the first pusher; at the same time, the third joint rotates relative to the first pusher, the third joint rotates relative to the fourth joint, the fourth joint rotates relative to the second pusher, and the second pusher rotates relative to the second panel, so that the telescopic assembly is further extended, and the second panel is pushed to rotate toward the inner side of the first panel by the second pusher, and finally the third panels are brought closer to each other. The first panel, the second panel, and the middle panel are unified into regular pentagonal panels, which are easier to produce and process, and the accommodating cavity surrounded by such first panel, second panel, third panel, and middle panel is better sealed, which can greatly reduce the probability of debris escaping the accommodating cavity.

[0019] Preferably, the satellite housing is provided with a battery, and a first solar panel is provided on the inner sides of the intermediate panel, the first panel, and the second panel, and the first solar panel is electrically connected to the battery. When the ends of the shell petal assembly are spaced apart, the first solar panel is exposed, absorbing solar energy and converting it into electricity, which is stored in the battery. This provides power for the entire capture device, reducing its reliance on external power sources and thus lowering the operating costs of the entire device.

[0020] Preferably, a second solar panel is provided on the exterior of the satellite housing, and the second solar panel is electrically connected to the battery. Similarly, the second solar panel can absorb solar energy and convert it into electrical energy, which is stored in the battery, thereby providing a continuous and stable power supply for the entire device, thereby improving the stability and safety of the entire device.

[0021] Beneficial effects of the present invention:

[0022] (1) The device has the function of capturing and recovering space debris. By combining the capture component, storage chamber and robotic arm, the robotic arm can be used to grab the captured space debris and store it in the storage chamber for recovery so that the space debris can be reused later. This can not only reduce equipment costs but also improve the recovery efficiency of space debris.

[0023] (2) The robotic arm is flexible and has a high success rate in grabbing space debris. The robotic arm has five degrees of freedom, and the gripping components have a wide range of motion and are flexible, allowing it to successfully grab space debris at multiple locations.

[0024] (3) Strong adaptability. The capture component can be used to capture and recycle space debris of different shapes, such as rod-shaped, bar-shaped, and sheet-shaped debris.

[0025] (4) The device has a solar power generation function. Solar panels are set up to absorb solar energy and convert it into electrical energy and store it in batteries, which can provide a continuous and stable power supply for the entire device, reducing the device's dependence on external power and the device's operating costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a schematic diagram of the structure of the inner cavity of a multifunctional space debris capture device;

[0027] Figure 2 It is a structural diagram of the storage warehouse;

[0028] Figure 3 It is a schematic diagram of the structure of a multifunctional space debris capture device;

[0029] Figure 4 This is a schematic diagram capturing one of the perspectives outside the component.

[0030] Figure 5 is a schematic diagram of the shell petal assembly with its ends moving away from each other;

[0031] Figure 6 It is a schematic diagram of the ends of the shell petal assembly when they are brought close to each other;

[0032] Figure 7 It is a structural diagram of the telescopic component;

[0033] Figure 8 It is a structural diagram that captures another perspective of the outside of the component;

[0034] Figure 9 is a side view of the capture assembly.

[0035] In the accompanying drawings: 1-satellite shell; 101-inner cavity; 102-through port; 2-middle panel; 3-shell petal assembly; 301-first panel; 302-second panel; 303-third panel; 304-weight reduction groove; 305-reinforcement rib; 306-accommodation cavity; 4-storage compartment; 401-storage cavity; 5-clamping robotic arm; 501-fixed arm; 502-first rotary arm; 503-second rotary arm; 504-third rotary arm; 505-clamping assembly; 6-drive; 601-fixed part; 7-telescopic assembly; 701-first joint; 702-second joint; 703-first pusher; 704-third joint; 705-fourth joint; 706-second pusher; 8-first solar panel; 9-second solar panel; 10-space debris. DETAILED DESCRIPTION

[0036] The drawings are for illustrative purposes only and should not be construed as limiting this patent. To better illustrate the embodiments, some components in the drawings may be omitted, enlarged, or reduced in size, and do not represent actual product dimensions. Those skilled in the art will understand that some well-known structures and their descriptions may be omitted from the drawings. The positional relationships depicted in the drawings are for illustrative purposes only and should not be construed as limiting this patent.

[0037] The same or similar numbers in the drawings of the embodiments of the present invention correspond to the same or similar parts; in the description of the present invention, it should be understood that if there are terms such as "upper", "lower", "left", "right", "long", "short", etc. indicating the orientation or position relationship, they are based on the orientation or position relationship shown in the drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation. Therefore, the terms describing the position relationship in the drawings are only used for illustrative purposes and cannot be understood as limiting this patent. For ordinary technicians in this field, the specific meanings of the above terms can be understood according to specific circumstances.

[0038] The technical solution of the present invention is further described in detail below through specific embodiments and in conjunction with the accompanying drawings:

[0039] Example 1

[0040] Combine Figures 1 to 6A multifunctional space debris capture device is shown, which includes a satellite shell 1, a drive assembly arranged outside the satellite shell 1, and a capture assembly connected to the drive assembly, the capture assembly includes an intermediate panel 2, and a plurality of shell petal assemblies 3 are rotatably connected to the intermediate panel 2, and the drive assembly is used to drive the shell petal assemblies 3 to rotate relative to the intermediate panel 2 so that the ends of the shell petal assemblies 3 move closer to or away from each other; when the ends of the shell petal assemblies 3 move closer to each other, a accommodating cavity 306 for accommodating space debris 10 is formed between the shell petal assembly 3 and the intermediate panel 2; the satellite shell 1 is also provided with a storage bin 4 for placing space debris 10 and a clamping robot arm 5, a storage cavity 401 is provided in the storage bin 4, and the clamping robot arm 5 is used to grab the space debris 10 in the accommodating cavity 306 into the storage cavity 401.

[0041] Furthermore, the satellite housing 1 is provided with an inner cavity 101 and a through-hole 102 communicating with the inner cavity 101. A linear drive mechanism (not shown) is provided within the inner cavity 101. The storage bin 4 is connected to the power output of the linear drive mechanism. Initially, one side of the storage bin 4 is flush with a side of the satellite housing 1. The linear drive mechanism is used to drive the storage bin 4 to translate in and out of the inner cavity 101 through the through-hole 102. After the gripping robot 5 grasps the space debris 10, the linear drive mechanism drives the storage bin 4 to move from the inside of the inner cavity 101 to the outside through the through-hole 102. The gripping robot 5 then places the space debris 10 into the storage cavity 401. The linear drive mechanism then drives the storage bin 4 from the outside of the inner cavity 101 to the inside of the inner cavity 101. This protects the space debris 10 from external interference and damage within the satellite housing 1, while also reducing the overall size of the entire device.

[0042] Furthermore, the storage bin 4 is slidably connected to the satellite shell 1, and a linear drive mechanism is used for the sliding of the storage bin 4, so that the storage bin 4 can enter and exit the inner cavity 101 in a more stable state, avoiding vibration transmission and causing the space debris 10 to escape from the storage bin 4.

[0043] Furthermore, the linear drive mechanism includes a linear motor, which is mounted on the inner wall of the inner cavity 101. The output shaft of the linear motor is connected to the storage bin 4. The linear motor drives the movement of the storage bin 4. The linear motor has the characteristics of high precision, high response speed, low vibration, easy control, and long life, which helps improve the recovery efficiency of space debris 10.

[0044] Furthermore, the gripping robot arm 5 includes a fixed arm 501 connected to the satellite housing 1, a first rotation drive assembly (not shown in the figure) provided on the fixed arm 501, a first rotary arm 502 rotatably connected to the fixed arm 501, a second rotation drive assembly (not shown in the figure) provided on the first rotary arm 502, a second rotary arm 503 rotatably connected to the first rotary arm 502, a third rotation drive assembly (not shown in the figure) provided on the second rotary arm 503, a third rotary arm 504 rotatably connected to the second rotary arm 503, and a fourth rotation drive assembly (not shown in the figure) provided on the third rotary arm 504. The first rotary arm 502 has an axis parallel to the axes of the fixed arm 501 and the second rotary arm 503. The first rotary arm 502 has an axis parallel to the axes of the fixed arm 501 and the second rotary arm 503. The first rotary drive assembly is used to drive the first rotary arm 502 to rotate about its own axis. The second rotary drive assembly is used to drive the second rotary arm 503 to rotate about an axis perpendicular to its own axis. The third rotary drive assembly is used to drive the third rotary arm 504 to rotate about an axis perpendicular to its own axis. The fourth rotary drive assembly is used to drive the clamping assembly 505 to rotate about the axis of the third rotary arm 504. It will be appreciated that such a clamping robot arm 5 has five degrees of freedom. The clamping assembly 505 has a wide range of motion. The rotation of the first rotary arm 502, the second rotary arm 503, the third rotary arm 504, and the clamping assembly 505 allows for flexible adjustment of the position and clamping angle of the clamping assembly 505, thereby clamping space debris 10 at different locations, thereby improving the success rate and efficiency of recovering space debris 10.

[0045] The working principle or workflow of this embodiment is as follows: in the initial state, the ends of the multiple shell petal assemblies 3 are away from each other, and the shell petal assemblies 3 are in an expanded state; when the space debris 10 approaches the inner side of the shell petal assembly 3 and is located within the envelope of the accommodating cavity 306, the driving assembly drives the ends of the shell petal assembly 3 to move closer together, so that the shell petal assembly 3 is closed and forms the accommodating cavity 306, thereby enclosing the space debris 10 in the accommodating cavity 306, thus completing the capture of the space debris 10. After the space debris 10 is stabilized in the accommodating cavity 306, the driving assembly then drives the ends of the shell petal assembly 3 to gradually move away from each other to open the accommodating cavity 306 and expose the space debris 10; the clamping robot 5 then adjusts the position of the clamping assembly 505, extends the clamping assembly 505 to the space debris 10, and grabs the space debris 10 into the storage cavity 401 for storage, thus completing the recovery of the space debris 10.

[0046] It can be understood that the inner side of the middle panel 2 and the shell petal assembly 3 refers to the side where the accommodating cavity 306 is located, and the outer side refers to the side opposite to the accommodating cavity 306 .

[0047] Beneficial effects of this embodiment:

[0048] (1) The device has the function of capturing and recovering space debris. By combining the capture component, storage chamber and robotic arm, the robotic arm can be used to grab the captured space debris and store it in the storage chamber for recovery so that the space debris can be reused later. This can not only reduce equipment costs but also improve the recovery efficiency of space debris.

[0049] (2) The robotic arm is flexible and has a high success rate in grabbing space debris. The robotic arm has five degrees of freedom, and the gripping components have a wide range of motion and are flexible, allowing it to successfully grab space debris at multiple locations.

[0050] Example 2

[0051] This embodiment is based on embodiment 1. Figures 3 to 9 As shown, the shell petal assembly 3 is distributed in a circular shape on the middle panel 2; the drive assembly includes a driver 6 and a telescopic assembly 7 arranged on the satellite shell 1, and the driver 6 is provided with a fixed portion 601, one end of the telescopic assembly 7 is connected to the fixed portion 601, and the other end is connected to the shell petal assembly 3; the driver 6 is used to drive the telescopic assembly 7 to extend and retract, and when the telescopic assembly 7 is extended, the ends of the shell petal assembly 3 are brought closer to each other, and when the telescopic assembly 7 is shortened, the ends of the shell petal assembly 3 are moved away from each other. It can be understood that when the telescopic assembly 7 is extended, one end of the telescopic assembly 7 applies a thrust to the shell petal assembly 3, and this thrust can push the shell petal assembly 3 to rotate in the direction close to the inner side of the middle panel 2, so that the ends of the shell petal assembly 3 are brought closer to each other, and finally form a accommodating cavity 306 with the middle panel 2. The shell petal assembly 3 is driven to expand or close by the extension and retraction of the telescopic assembly 7. This driving method is more flexible and safe, and is also conducive to simplifying the structure of the entire capture mechanism.

[0052] Furthermore, the telescopic assembly 7 includes a first joint 701, a second joint 702 and a first pushing member 703. The first joint 701 is rotatably connected to the second joint 702 and both are rotatably connected to the fixed part 601 and the first pushing member 703 respectively. The first pushing member 703 is rotatably connected to the outer side of the shell valve assembly 3; the rotation axis of the first joint 701 relative to the fixed part 601 and the rotation axis of the second joint 702 relative to the first pushing member 703 are both perpendicular to the rotation axis of the second joint 702 relative to the first joint 701, and the rotation axis of the first pushing member 703 relative to the shell valve assembly 3 is perpendicular to the rotation axis of the second joint 702 relative to the first pushing member 703; the driver 6 is a motor of the prior art, and its output shaft is connected to the middle part of the outer side of the middle panel 2, for driving the middle panel 2 to rotate. The rotation axis of the middle panel 2 is perpendicular to the rotation axis of the first joint 701 relative to the fixed part 601. When the middle panel 2 rotates, the second joint 702 and the first joint 701 rotate relative to each other to cause the telescopic assembly 7 to extend or shorten. When the driver 6 drives the middle panel 2 to rotate, the second joint 702 rotates relative to the first joint 701, and at the same time the first joint 701 rotates relative to the fixing portion 601, the second joint 702 rotates relative to the first pusher 703, and the first pusher 703 rotates relative to the shell flap assembly 3, thereby causing the telescopic assembly 7 to reach an extended state; during the extension of the telescopic assembly 7, the second joint 702 applies a driving force to the shell flap assembly 3 through the first pusher 703, thereby driving the shell flap assembly 3 to rotate toward the inner side of the middle panel 2. By driving the middle panel 2 to rotate, the ends of the shell flap assembly 3 can be brought closer to each other. Such a drive assembly structure and its drive method are more flexible and simple, which not only helps to reduce the weight of the entire mechanism, reduce the manufacturing cost and maintenance cost of the mechanism, but also makes it easier to control the mechanism action, so that the task can be carried out more smoothly.

[0053] Furthermore, the shell valve assembly 3 includes a first panel 301 and a second panel 302 rotatably connected to the middle panel 2. The middle panel 2, the first panel 301 and the second panel 302 are all regular pentagonal panels. One side of the first panel 301 is rotatably connected to one side of the middle panel 2. The second panel 302 is located on the side of the first panel 301 opposite to the middle panel 2 and is rotatably connected to the first panel 301; one side of the second panel 302 is connected to a third panel 303 in the shape of an isosceles triangle, and the third panel 303 is located on the side of the second panel 302 opposite to the first panel 301; the first push member 703 is rotatably connected to the middle part of the outer side of the first panel 301.

[0054] Furthermore, the telescopic assembly 7 also includes a third joint 704, a fourth joint 705 and a second pusher 706. The third joint 704 is rotatably connected to the fourth joint 705 and both are rotatably connected to the first pusher 703 and the second pusher 706 respectively; the second pusher 706 is rotatably connected to the middle part of the outer side of the second panel 302; the rotation axis of the third joint 704 relative to the first pusher 703 and the rotation axis of the fourth joint 705 relative to the second pusher 706 are both perpendicular to the rotation axis of the fourth joint 705 relative to the third joint 704; when the middle panel 2 rotates, the first panel 301, the second panel 302, the third panel 303 and the middle panel 2 can form a closed accommodating cavity 306.

[0055] During the rotation of the middle panel 2, the first joint 701 rotates relative to the fixing portion 601, the first joint 701 and the second joint 702 rotate relative to each other, the second joint 702 rotates relative to the first pushing member 703, and the first pushing member 703 rotates relative to the first panel 301, so that the telescopic assembly 7 is extended, and the first pushing member 703 pushes the first panel 301 to rotate toward the inner side of the middle panel 2; at the same time, the third joint 704 rotates relative to the first pushing member 703, the third joint 704 and the fourth joint 705 rotate relative to each other, the fourth joint 705 rotates relative to the second pushing member 706, and the second pushing member 706 rotates relative to the second panel 302, so that the telescopic assembly 7 is further extended, and the second panel 302 is pushed to rotate toward the inner side of the first panel 301 through the second pushing member 706, and finally the third panels 303 are brought closer to each other. The first panel 301, the second panel 302 and the middle panel 2 are unified into regular pentagonal panels, which are easier to produce and process. In addition, the accommodating cavity 306 surrounded by such first panel 301, the second panel 302, the third panel 303 and the middle panel 2 has good sealing performance, which can greatly reduce the probability of debris escaping the accommodating cavity 306.

[0056] Other features, working principles and beneficial effects of this embodiment are consistent with those of embodiment 1.

[0057] Example 3

[0058] This embodiment is based on embodiment 2. Figure 1 or Figure 3As shown, the satellite housing 1 is equipped with a battery (not shown). A first solar panel 8 is installed on the inner sides of the intermediate panel 2, the first panel 301, and the second panel 302. The first solar panel 8 is electrically connected to the battery. When the ends of the shell petal assembly 3 are separated from each other, the first solar panel 8 is exposed, absorbing solar energy and converting it into electricity, which is stored in the battery. This provides power for the entire capture device, reducing its reliance on external power sources and lowering the operating costs of the entire device.

[0059] Furthermore, a second solar panel 9 is provided on the exterior of the satellite housing 1 and is electrically connected to the battery. Similarly, the second solar panel 9 absorbs solar energy and converts it into electrical energy, which is stored in the battery. This provides a continuous and stable power source for the entire device, improving the stability and safety of the entire device's operation.

[0060] Other features, working principles and beneficial effects of this embodiment are consistent with those of Example 2.

[0061] Example 4

[0062] This embodiment is based on embodiment 3. Figure 4 and Figure 8 As shown, the outer sides of the middle panel 2, the first panel 301, the second panel 302, and the third panel 303 are each provided with a plurality of weight-reducing grooves 304. Reinforcing ribs 305 are formed between adjacent weight-reducing grooves 304 on the same panel. The reinforcing ribs 305 ensure sufficient strength for each panel, while the provision of multiple weight-reducing grooves 304 helps reduce the weight of each panel, making the entire capture assembly even lighter.

[0063] Furthermore, the first joint 701, the second joint 702, the third joint 704 and the fourth joint 705 are all triangular in shape, which has higher stability, and a through cavity is opened in the middle of each of them, which helps to reduce the weight of the capture component.

[0064] Other features, working principles and beneficial effects of this embodiment are consistent with those of Example 3.

[0065] Obviously, the above embodiments of the present invention are merely examples for the purpose of clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Those skilled in the art will appreciate that other variations or modifications can be made based on the above description, and it is not necessary and impossible to enumerate all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the claims of the present invention.

Claims

1. A multifunctional space debris capture device, comprising a satellite housing (1), a drive assembly arranged outside the satellite housing (1), and a capture assembly connected to the drive assembly, characterized in that: The capture assembly comprises an intermediate panel (2), a plurality of shell petal assemblies (3) are rotatably connected to the intermediate panel (2), and the drive assembly is used to drive the shell petal assemblies (3) to rotate relative to the intermediate panel (2) so that the ends of the shell petal assemblies (3) move closer to or farther away from each other; when the ends of the shell petal assemblies (3) move closer to each other, a receiving cavity (306) for receiving space debris is formed between the shell petal assemblies (3) and the intermediate panel (2); the satellite housing (1) is further provided with a storage bin (4) and a clamping mechanical arm (5), the storage bin (4) being provided with a storage cavity (401), and the clamping mechanical arm (5) being used to grab the space debris captured by the receiving cavity (306) into the storage cavity (401); The shell petal assemblies (3) are circumferentially distributed on the middle panel (2); the driving assembly comprises a driver (6) and a telescopic assembly (7) arranged on the satellite housing (1); the driver (6) is provided with a fixing portion (601); one end of the telescopic assembly (7) is connected to the fixing portion (601), and the other end is connected to the shell petal assembly (3); the driver (6) is used to drive the telescopic assembly (7) to extend and retract; when the telescopic assembly (7) is extended, the ends of the shell petal assemblies (3) move closer to each other, and when the telescopic assembly (7) is shortened, the ends of the shell petal assemblies (3) move away from each other; The telescopic assembly (7) comprises a first joint (701), a second joint (702) and a first pusher (703); the first joint (701) and the second joint (702) are rotatably connected and are rotatably connected to the fixing portion (601) and the first pusher (703) respectively; the first pusher (703) is rotatably connected to the outer side of the shell petal assembly (3); the rotation axis of the first joint (701) relative to the fixing portion (601) and the rotation axis of the second joint (702) relative to the first pusher (703) are both perpendicular to the rotation axis of the second joint (702) relative to the first joint (701); the rotation axis of the first pusher (703) relative to the shell petal assembly (3) is perpendicular to the rotation axis of the second joint (702) relative to the first pusher (703); The driver (6) is used to drive the middle panel (2) to rotate, and the rotation axis of the middle panel (2) is perpendicular to the rotation axis of the first joint (701) relative to the fixed portion (601). When the middle panel (2) rotates, the second joint (702) rotates relative to the first joint (701) to extend or shorten the telescopic assembly (7).

2. The multifunctional space debris capture device according to claim 1, characterized in that: The satellite housing (1) is provided with an inner cavity (101) and a through-port (102) communicating with the inner cavity (101); a linear drive mechanism is provided in the inner cavity (101); the storage bin (4) is connected to a power output end of the linear drive mechanism; the linear drive mechanism is used to drive the storage bin (4) to translate into and out of the inner cavity (101) through the through-port (102).

3. The multifunctional space debris capture device according to claim 2, characterized in that: The storage bin (4) is slidably connected to the satellite housing (1), and the linear drive mechanism is used for the sliding of the storage bin (4).

4. The multifunctional space debris capture device according to claim 2, characterized in that: The linear drive mechanism comprises a linear motor, the linear motor is arranged on the inner wall of the inner cavity (101), and the output shaft of the linear motor is connected to the storage bin (4).

5. The multifunctional space debris capture device according to claim 1, characterized in that: The shell petal assembly (3) comprises a first panel (301) and a second panel (302) rotatably connected to the middle panel (2); the middle panel (2), the first panel (301) and the second panel (302) are all regular pentagonal panels; one side of the first panel (301) is rotatably connected to one side of the middle panel (2); the second panel (302) is located on a side of the first panel (301) opposite to the middle panel (2) and is rotatably connected to the first panel (301); one side of the second panel (302) is connected to a third panel (303) in the shape of an isosceles triangle; the third panel (303) is located on a side of the second panel (302) opposite to the first panel (301); the first pusher (703) is rotatably connected to the middle portion of the outer side of the first panel (301); The telescopic assembly (7) further comprises a third joint (704), a fourth joint (705) and a second pusher (706), wherein the third joint (704) is rotatably connected to the fourth joint (705) and both are rotatably connected to the first pusher (703) and the second pusher (706) respectively; the second pusher (706) is rotatably connected to the middle portion of the outer side of the second panel (302); the rotation axis of the third joint (704) relative to the first pusher (703) and the rotation axis of the fourth joint (705) relative to the second pusher (706) are both perpendicular to the rotation axis of the fourth joint (705) relative to the third joint (704); when the middle panel (2) rotates, the first panel (301), the second panel (302), the third panel (303) and the middle panel (2) can enclose the closed accommodating cavity (306).

6. The multifunctional space debris capture device according to claim 5, characterized in that: A storage battery is provided on the satellite housing (1); first solar panels (8) are provided on the inner sides of the middle panel (2), the first panel (301) and the second panel (302); and the first solar panel (8) is electrically connected to the storage battery.

7. The multifunctional space debris capture device according to claim 6, characterized in that: A second solar cell panel (9) is provided on the outside of the satellite housing (1), and the second solar cell panel (9) is electrically connected to the battery.

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