Capture net based on space protection

Abstract

The invention provides a capturing net based on space protection, and belongs to the field of on-orbit spacecraft service, the capturing net comprises a hexahedral satellite main body, a fixed connecting device, an unlocking device, an unfolding antenna and an unfolding net, the fixed connecting device is arranged outside the hexahedral satellite main body, the unfolding antenna is hinged to the fixed connecting device, the unlocking device comprises a multi-stage unlocking mechanism, and the unfolding net is arranged in the hexahedral satellite main body. The unlocking mechanisms are arranged on the fixed connecting device and the unfolding antenna, the fixed connecting device and the unfolding antenna are locked in a folded state, the unlocking mechanisms act in sequence to achieve unfolding of the unfolding antenna, and the unfolding net is arranged in the unfolding antenna and is unfolded along with the unfolding antenna to complete fragment capturing. According to the space debris capturing device, space debris of various sizes and irregularity can be captured, kinetic energy of a captured object is effectively reduced by means of the material characteristics of the unfolding net, firm capturing is achieved, and the success rate of capturing the space debris is greatly increased.

Description

Technical Field

[0001] The invention belongs to the field of on-orbit spacecraft services and relates to a capture net based on space protection. Background Art

[0002] With the increasing number of space activities in recent years, the number of space junk and space debris is also increasing. Space junk and space debris pose a serious threat to spacecraft in orbit. When spacecraft and space debris collide with each other, new space debris will be generated, and the consequences are quite serious. Therefore, space debris has become an interference factor that cannot be ignored in the process of human exploration of space. At present, space debris and space junk are mainly captured by mechanical arms, flying claws, harpoons and other capture methods. For example, the invention patent with application number 201910480406.7, "A method for derotating space debris based on a space folding mechanical arm", discloses a method for capturing and derotating space debris and space junk by a foldable mechanical arm. The method captures space debris through the adhesive layer on the end device of the mechanical arm, and completes the derotation by unfolding the mechanical arm in conjunction with the jet attitude control system. However, due to the diversity of the causes of space debris and space junk, their shapes and sizes are not fixed, and some of them are not suitable for capture by existing methods. In addition, some high-speed moving space debris are forcibly captured by existing methods, which will cause damage to the capture host star and cause unnecessary losses. Summary of the invention

[0003] In order to solve the above problems existing in the prior art, the present invention provides a capture net based on space protection to capture space debris and space junk of irregular shapes and sizes, and effectively reduce the kinetic energy of space debris to improve the success rate of capturing space debris.

[0004] The present invention adopts the following technical solution:

[0005] A capture net based on space protection, the capture net comprises a satellite body 1, a fixed connection device, an unlocking device, a deployment antenna 6 and a deployment net 7. The fixed connection device is a foldable structure, arranged outside the satellite body 1, the deployment antenna 6 is hinged with the fixed connection device to realize the switching between the folded and unfolded states of the deployment antenna 6, the unlocking device comprises a multi-level unlocking mechanism, arranged on the fixed connection device and the deployment antenna 6, and locks the fixed connection device and the deployment antenna 6 in a folded and closed state, the satellite body 1 serves as a supporting structure and control mechanism of the entire capture net, and is used to adjust the posture of the capture net and control the fixed connection device, the unlocking device and the deployment antenna 6 to realize unlocking and unfolding or folding and locking; the deployment net 7 is arranged inside the deployment antenna 6, and is unfolded synchronously with the deployment antenna 6, and changes from the folded state to the working state, completing the capture of the debris.

[0006] The satellite body 1 is equipped with an attitude and orbit control system, a control motor, a power system, a binocular recognition system, and the payload required for on-orbit operation. The binocular recognition system is used to collect images of the space debris to be captured and perform positioning and recognition, and the attitude and orbit control system is used to adjust the capture posture of the satellite body 1 and the deployment net 7 according to the positioning information of the space debris to be captured. The power system is used to provide power for the entire capture net. At the same time, it serves as a control system for the unlocking device, and controls the unlocking device by sending an electromagnetic signal to the unlocking device to achieve unlocking, thereby completing the deployment action of the deployment antenna 6. The control motor is used to control the deployment antenna 6 and the fixed connection device in the deployed state to be retracted and restored to the retracted state.

[0007] The fixed connection device includes a fixing device 2, a first connecting rod 3, a fixing plate 4, a second connecting rod 5, and a fixing seat 12; the fixing seat 12 and the fixing device 2 are fixedly arranged at both ends of the outer shell of the satellite body 1; the two ends of the first connecting rod 3 are respectively hinged to the fixing plate 4 and the fixing device 2, the second connecting rod 5 is arranged parallel to the fixing plate 4 and fixed on the fixing plate 4, one end of the deployment antenna 6 is connected to the second connecting rod 5, the second connecting rod 5 is used to support the deployment antenna 6 after deployment on the one hand, and to limit the folded state of the deployment antenna 6 through an unlocking device on the other hand. The deployment antenna 6 in the folded state is limited to the fixing plate 4 by the unlocking device. After the first connecting rod 3 and the fixing plate 4 are folded, they are limited to the satellite body 1 by the fixing seat 12 cooperating with the unlocking device.

[0008] The unlocking device includes a first-level unlocking separation nut 8, a second-level unlocking pin puller 9, a third-level unlocking pin puller 10 and a fourth-level unlocking pin puller 11; the first-level unlocking separation nut 8 is arranged on the fixing seat 12, cooperates with the fixing plate 4, and is used to limit the rotation of the fixed connection device relative to the fixed connection device 2, and the second-level unlocking pin puller 9 is provided in two groups, which are respectively arranged on both sides of the first connecting rod 3, and are used to limit the first connecting rod 3 and the fixing plate 4 to a folded state; the third-level unlocking pin puller 10 is provided in two groups, which are respectively arranged at the two ends of the deployed antenna 6 in the folded state, and cooperate with the two ends of the fixing plate 4, and are used to limit the deployed antenna 6 in the folded state to the fixing plate 4; the fourth-level unlocking pin puller 11 is arranged on the second connecting rod 5, which is an annular structure, surrounding the outer periphery of the deployed antenna 6 in the folded state, so as to limit the unlocking of the folded state of the deployed antenna 6; the unlocking device is in the satellite body 1. The electromagnetic signal sent by the power supply system Under control, the unlocking mechanisms at each level are unlocked in sequence. After the first-level unlocking separation nut 8 is unlocked, the first connecting rod 3 rotates around the hinge between it and the connecting device 2 to complete the first-level unlocking. After the second-level unlocking pin puller 9 is unlocked, the fixed plate 4 rotates in the opposite direction around the hinge between it and the first connecting rod 3 to complete the second-level unlocking. After the third-level unlocking pin puller 10 and the fourth-level unlocking pin puller 11 are unlocked in sequence, the deployment antenna 6 is separated from the fixed plate 4 and deployed; when the deployment antenna 6 is folded, under the drive of the control motor inside the satellite body 1, after the deployment antenna 6 is folded to the minimum volume, the fourth-level unlocking pin puller 11 surrounds the deployment antenna 6 and locks it, and the third-level unlocking pin puller 10 is locked to limit the folded deployment antenna 6 to the second connecting rod 5. After the fixed plate 4 rotates around the hinge between it and the first connecting rod 3 to a folded state, the second-level unlocking pin puller 9 is locked, and after the first connecting rod 3 rotates around the hinge between it and the connecting device 2 to a folded state, the first-level unlocking separation nut 8 is locked to complete the locking.

[0009] The deployable antenna 6 is a frame-type deployable antenna structure, which is composed of deployable rigid trusses, and is used to attach and support the deployable net 7. It is cylindrical in the folded state, and three-level unlocking pin pullers 10 are set at both ends of the cylinder to lock with the two ends of the fixing plate 4; the deployable antenna 6 has a disc-shaped appearance in the deployed state, and the trusses are symmetrically and evenly distributed, which is used to effectively support the deployable net 7 in the deployed state. Driven by the control motor inside the satellite body 1, the various parts of the deployable antenna 6 are folded and compressed inwardly, and folded according to the designed movement path, so that it gradually reduces its volume and returns to the folded state.

[0010] The deployment net 7 has an umbrella-like structure when deployed, and is connected to the deployment antenna 6 by a rope-tied sleeve. In the folded state, the deployment net 7 is folded inside the deployment antenna 6 and can be deployed synchronously with the deployment antenna 6. After deployment, the deployment net 7 is in an appropriately taut state, which is used to effectively reduce the kinetic energy of space debris.

[0011] Furthermore, the unlocking mechanisms at all levels of the unlocking device are made of memory alloy materials, which are heated and deformed under the influence of the electromagnetic effect of the power supply system in the satellite body 1 to achieve the purpose of unlocking.

[0012] Furthermore, the unfolded net 7 is made of wood fibers coated with metal, and the toughness advantage of the material can be maximized when properly tightened.

[0013] Compared with the prior art, the beneficial effect of the present invention is that the present invention can capture space debris and space junk of various sizes and irregular shapes through the unlocking device, the unfolding antenna and the unfolding net. Relying on the material properties of the unfolded net, the kinetic energy of the captured object can be effectively reduced, and a firm capture can be achieved, which greatly improves the success rate of capturing space debris. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of the unfolded state of the present invention.

[0015] Figure 2 It is an overall schematic diagram of the folded state of the present invention, wherein (a) is a front view and (b) is a side view.

[0016] Figure 3 Schematic diagram of the unlocking steps of the present invention, wherein (a) is a schematic diagram of the folded state, (b) is a schematic diagram of the state after the first level of unlocking, (c) is a schematic diagram of the state after the second level of unlocking, and (d) is a schematic diagram of the unfolded state after the third and fourth levels of unlocking.

[0017] In the figure: 1 satellite body; 2 fixing device; 3 first connecting rod; 4 fixing plate; 5 second connecting rod; 6 unfolding antenna; 7 unfolding net; 8 first-level unlocking separation nut; 9 second-level unlocking pin puller; 10 third-level unlocking pin puller; 11 fourth-level unlocking pin puller; 12 fixing seat. DETAILED DESCRIPTION

[0018] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation" and "connection" should be understood in a broad sense.

[0019] In addition, the technical features involved in the different embodiments of the present invention described below can be connected to each other as long as they do not conflict with each other.

[0020] A capture net based on space protection, the capture net comprises a satellite body 1, a fixed connection device, an unfolding antenna 6, an unfolding net 7 and an unlocking device, such as Figure 1 shown.

[0021] The satellite body 1 is provided with an attitude and track control system, a control motor, a power supply system, a binocular recognition system, and a payload required for on-orbit operation. The binocular recognition system is used to collect images of the space debris to be captured and perform positioning and recognition so that the subsequent capture can proceed smoothly; the attitude and track control system is used to adjust the capture posture of the satellite body 1 and the deployment net 7 according to the positioning information of the space debris to be captured. When the space debris is running in space, since not every space debris can be successfully captured by the capture net, the advantages of the attitude and track control system are revealed, and the maneuverability of the on-orbit capture is improved. The attitude and track control system cooperates with the binocular recognition system to locate the space debris through the binocular recognition system, and to adjust the capture posture using the attitude and track control system, which greatly improves the capture probability of the space debris and effectively protects the normal operation of the on-orbit space station. The power supply system is used to provide power for the entire capture net. At the same time, it serves as a control system for the unlocking device, and controls it to unlock by sending an electromagnetic signal to the unlocking device. The control motor is used to control the unfolding antenna 6 and the fixed connection device in the unfolded state to be retracted.

[0022] like Figure 2 As shown, the fixed connection device includes a fixing device 2, a first connecting rod 3, a fixing plate 4, a second connecting rod 5, and a fixing seat 12; the fixing seat 12 and the fixing device 2 are fixedly arranged at both ends of the outer shell of the satellite body 1; the two ends of the first connecting rod 3 are respectively hinged to the fixing plate 4 and the fixing device 2, the second connecting rod 5 is arranged parallel to the fixing plate 4 and fixed on the fixing plate 4, one end of the deployment antenna 6 is connected to the second connecting rod 5, the second connecting rod 5 is used to support the deployment antenna 6 after deployment on the one hand, and to limit the folded state of the deployment antenna 6 through the unlocking device on the other hand; in the folded state, the deployment antenna 6 is folded and restricted on the fixing plate 4, and after the first connecting rod 3 and the fixing plate 4 are folded, they are restricted on the satellite body 1 through the fixing seat 12 cooperating with the unlocking device.

[0023] like Figure 2As shown, the unlocking device includes a first-level unlocking separation nut 8, a second-level unlocking pin puller 9, a third-level unlocking pin puller 10 and a fourth-level unlocking pin puller 11; the first-level unlocking separation nut 8 is arranged on the fixing seat 12, and is used to limit the rotation of the first connecting rod 3 relative to the fixing device 2. The second-level unlocking pin puller 9 has two groups, which are respectively arranged on both sides of the first connecting rod 3, and are used to limit the first connecting rod 3 and the fixing plate 4 to a folded state; the third-level unlocking pin puller 10 has two groups, which are respectively arranged at both ends of the deployed antenna 6 in the folded state, and are used to limit the deployed antenna 6 in the folded state to the fixed plate 4; the four-stage unlocking pin puller 11 is arranged on the second connecting rod 5, which is a ring structure, surrounding the outer periphery of the deployed antenna 6 in the folded state to limit the unlocking of the folded state of the deployed antenna 6; the unlocking mechanisms of each level of the unlocking device are all memory alloy materials, which are special phase-change metal materials. Under the influence of the electromagnetic action of the power supply system in the satellite body 1, the phase-change metal is heated to change its crystal structure, and then deformed to achieve the purpose of unlocking. Correspondingly, during the folding process of the deployed antenna 6 and the fixed connection device, the driving force of the control motor in the satellite body 1 causes the unlocking mechanisms at all levels to deform again to achieve locking. The unlocking device is controlled by the electromagnetic signal sent by the power supply system in the satellite body 1, and its unlocking mechanisms at various levels are unlocked in sequence. After the first-level unlocking separation nut 8 is unlocked, the first connecting rod 3 rotates around the hinge between it and the connecting device 2, completing the first-level unlocking. After the second-level unlocking pin puller 9 is unlocked, the fixed plate 4 rotates in the opposite direction around the hinge between it and the first connecting rod 3, completing the second-level unlocking. After the third-level unlocking pin puller 10 and the fourth-level unlocking pin puller 11 are unlocked in sequence, the deployment antenna 6 is separated from the fixed plate 4 and deployed; when the deployment antenna 6 is folded, under the drive of the control motor inside the satellite body 1, after the deployment antenna 6 is folded to the minimum volume, the fourth-level unlocking pin puller 11 surrounds the deployment antenna 6 and locks it, and the third-level unlocking pin puller 10 is locked to limit the folded deployment antenna 6 on the second connecting rod 5. After the fixed plate 4 rotates around the hinge between it and the first connecting rod 3 to a folded state, the second-level unlocking pin puller 9 is locked, and after the first connecting rod 3 rotates around the hinge between it and the connecting device 2 to a folded state, the first-level unlocking separation nut 8 is locked to complete the locking.

[0024] The deployable antenna 6 is a frame-type deployable antenna structure, which is composed of deployable rigid trusses, and is used to attach and support the deployable net 7. It is cylindrical in the folded state, and three-level unlocking pin pullers 10 are set at both ends of the cylinder, which cooperate with the two ends of the first connecting rod 3 to limit the deployable antenna 6 in the folded state to the fixed plate 4; the deployable antenna 6 has a disc-shaped appearance structure in the deployed state, and the trusses are symmetrically and evenly distributed, which can effectively support the opening of the deployable net 7. Driven by the control motor inside the satellite body 1, the various parts of the deployable antenna 6 are folded and compressed inwardly, and folded according to the designed movement path, so that it gradually reduces its volume and returns to the folded state.

[0025] The deployment net 7 has an umbrella-like structure after being deployed, and is connected to the deployed deployment antenna 6 by a rope-tied sleeve. In the folded state, the deployment net 7 is folded inside the deployment antenna 6 and can be deployed synchronously with the deployment antenna 6. The deployment net 7 is made of wood fibers plated with metal. After being deployed, the deployment net 7 is in an appropriately taut state, which can maximize the toughness advantage of the material, effectively reduce the kinetic energy of space debris, and greatly improve the success rate of capture.

[0026] The working process of the capture net is as follows Figure 3 As shown, specifically: after the binocular recognition system of the satellite body 1 finds the target, the attitude and orbit control system controls the satellite body 1 to approach the moving space debris; the power supply system in the satellite body 1 sends out an electromagnetic signal, so that the first-level unlocking separation nut 8 is unlocked by thermal phase change under the influence of electromagnetic action, and the first connecting rod 3 rotates around the hinge with the fixing device 2. At this time, the first connecting rod 3, the fixing plate 4, the second connecting rod 5, the unlocking device, the deployment antenna 6 and the deployment net 7 rely on the fixing device 2 to support part of the weight; after the second-level unlocking pin puller 9 is unlocked by thermal deformation under the action of the electromagnetic signal, the fixing plate 4 rotates in the opposite direction around the hinge with the first connecting rod 3, and the deployment antenna 6 moves synchronously with the fixing plate 4; the third-level unlocking pin puller 10 and the fourth-level unlocking pin puller 11 are respectively After being heated, deformed and unlocked under the action of electromagnetic signals for the first time, the deployment antenna 6 is deployed, and the deployment net 7 installed inside it is deployed synchronously and enters the working state. At this time, the weight of the deployment antenna 6 and the deployment net 7 is borne by the connecting rod 5 on the fixed plate 4; the deployment net 7 contacts the space debris, and uses the toughness of its material to reduce the kinetic energy of the space debris to achieve capture; after capture, the deployment antenna 6 is controlled by the control motor inside the satellite body 1 to return to the retracted state. At this time, the space debris is stored in the internal gap of the deployment antenna 6, and the unlocking mechanisms at all levels are deformed under the force of the control motor, and rely on the special properties of the memory alloy to return to the original state and lock again; the captured space debris is cleaned up by the astronauts in the orbiting space station, and the captured net can be put into use again after cleaning.

[0027] The present invention targets the space debris in motion and is not limited by the shape and size of the space debris. It is also applicable to irregular space debris. The present invention can withstand the impact of fast-moving debris and utilizes the material properties of the unfolded net 7 to effectively reduce the kinetic energy of the space debris.

[0028] The above description is only a preferred embodiment of the present invention, and does not limit the present invention in any form. The embodiment does not describe all the details in detail. According to the content of this specification, many modifications and changes can be made. Any modification, equivalent replacement and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. A capture net based on space protection, characterized in that: The capture net comprises a satellite body (1), a fixed connection device, an unlocking device, a deployment antenna (6) and a deployment net (7); the fixed connection device is a foldable structure, arranged outside the satellite body (1); the deployment antenna (6) is hinged to the fixed connection device; the unlocking device comprises a multi-stage unlocking mechanism, arranged on the fixed connection device and the deployment antenna (6), and locks the fixed connection device and the deployment antenna (6) in a folded and closed state; the satellite body (1) serves as a supporting structure and control mechanism for the entire capture net, and is used to adjust the posture of the capture net and control the fixed connection device, the unlocking device and the deployment antenna (6) to achieve unlocking, deployment or folding and locking; the deployment net (7) is arranged inside the deployment antenna (6) and is deployed synchronously with the deployment antenna (6).

2. A capture net based on space protection according to claim 1, characterized in that: The specific structure of the capture net is: The fixed connection device comprises a fixing device (2), a first connecting rod (3), a fixing plate (4), a second connecting rod (5), and a fixing seat (12); the fixing seat (12) and the fixing device (2) are fixedly arranged at two ends of the outer shell of the satellite body (1); the two ends of the first connecting rod (3) are respectively hinged to the fixing plate (4) and the fixing device (2); the second connecting rod (5) is arranged parallel to the fixing plate (4) and fixed on the fixing plate (4); the deployment antenna (6) is connected to the second connecting rod (5); the second connecting rod (5) is used to support the deployment antenna (6) after deployment on the one hand, and to limit the folding state of the deployment antenna (6) through an unlocking device on the other hand; the deployment antenna (6) in the folded state is limited to the fixing plate (4) through the unlocking device; after the first connecting rod (3) and the fixing plate (4) are folded, they are limited to the satellite body (1) through the fixing seat (12) in cooperation with the unlocking device; The unlocking device comprises a first-stage unlocking separation nut (8), a second-stage unlocking pin puller (9), a third-stage unlocking pin puller (10) and a fourth-stage unlocking pin puller (11); the first-stage unlocking separation nut (8) is arranged on a fixing seat (12), cooperates with a fixing plate (4), and is used to limit the rotation of the fixing connection device relative to the fixed connection device (2); the second-stage unlocking pin puller (9) is provided in two groups, which are respectively arranged on both sides of the first connecting rod (3), and are used to limit the first connecting rod (3) and the fixing plate (4) to a folded state; the third-stage unlocking pin puller (10) is provided in two groups, which are respectively arranged at both ends of the unfolded antenna (6) in the folded state, and cooperate with the fixing plate (4) to limit the rotation of the fixed connection device relative to the fixed connection device (2); The plate (4) cooperates with the satellite body (1) to restrict the deployed antenna (6) in the folded state to the fixed plate (4); the four-stage unlocking pin puller (11) is arranged on the second connecting rod (5), which is a ring-shaped structure, surrounding the outer periphery of the deployed antenna (6) in the folded state to restrict the deployed antenna (6) from being unlocked in the folded state; the unlocking mechanisms of each level of the unlocking device are unlocked in sequence under the control of the satellite body (1), so that the deployed antenna (6) and the fixed connection device are unfolded from the folded state to the working state; conversely, the satellite body (1) controls the deployed antenna (6) and the fixed connection device to fold and fold, and the unlocking mechanisms of each level of the unlocking device are locked in sequence in the opposite order to complete the locking in the folded state; The deployable antenna (6) is composed of deployable rigid trusses, which are cylindrical in shape when folded and disc-shaped in shape when deployed, and the trusses are symmetrically and evenly distributed; The deployment net (7) is in an umbrella-like structure after being deployed and is connected to the deployment antenna (6). The deployment net (7) is folded inside the deployment antenna (6) and can be deployed synchronously with the deployment antenna (6). After being deployed, the deployment net (7) is in a taut state and is used to reduce the kinetic energy of space debris.

3. A capture net based on space protection according to claim 1 or 2, characterized in that: The satellite body (1) is provided with an attitude and orbit control system, a control motor, a power supply system, a binocular recognition system and a payload required for on-orbit operation; the binocular recognition system is used to collect images of the space debris to be captured and perform positioning and recognition, and the attitude and orbit control system adjusts the capture posture according to the positioning information; The power supply system is used to provide power to the entire capture net and, at the same time, controls the unlocking of the unlocking device by sending an electromagnetic signal to the unlocking device; the control motor is used to control the folding of the unfolded antenna (6) and the fixed connection device in the unfolded state.

4. A capture net based on space protection according to claim 1 or 2, characterized in that: The unlocking mechanisms at all levels of the unlocking device are all made of memory alloy material, and are deformed by heat under the control of the satellite body (1) to achieve unlocking. During the retraction process, the driving force of the satellite body (1) causes the unlocking mechanisms at all levels to deform again to achieve locking.

5. A capture net based on space protection according to claim 1 or 2, characterized in that: The unfolded net (7) is made of wood fibers coated with metal and has toughness.

6. A capture net based on space protection according to claim 3, characterized in that: The working process of the capture net is as follows: after the satellite body (1) finds the target, the attitude and orbit control system controls the satellite body (1) to approach the moving space debris; the power system in the satellite body (1) sends an electromagnetic signal, the first-level unlocking separation nut (8) is heated and phase-changed to achieve unlocking, and the first connecting rod (3) rotates around the hinge between it and the fixed connection device (2); after the second-level unlocking pin puller (9) is heated and deformed and unlocked, the fixing plate (4) rotates around the hinge between it and the first connecting rod (3), and the unfolded antenna (6) moves synchronously with the fixing plate (4); the third-level unlocking After the pin puller (10) and the four-stage unlocking pin puller (11) are heated, deformed and unlocked in turn, the deployment antenna (6) is deployed, and the deployment net (7) is deployed synchronously to enter a working state; the deployment net (7) captures the space debris; after the capture, the deployment antenna (6) is controlled by a control motor inside the satellite body (1) to return to a folded state, at which time the space debris is stored in the internal gap of the deployment antenna (6), and the unlocking mechanisms at various levels are deformed under the action of the control motor to achieve locking; after the captured space debris is cleared, the capture net is put into use again.

Images