A spatial flexible protective shield for restraining debris splashing during the constrained anchoring attachment process

Abstract

The present invention discloses a space flexible shield for restraining debris splashing during the constrained anchoring and attachment process, belonging to the technical field of aerospace space capture, attack and defense. The flexible shield of the present invention is connected to the anchoring and attachment device through a protective connection seat. The flexible shield itself can be folded and retracted, and is held by a cutting device through a locking rope passing through a locking ring to resist the mechanical loads during the launch process. The flexible shield in the folded and retracted state ensures its deployment after the release of the locking rope due to its own elastic buckling characteristics, and the entire process does not need to consider structural damage. The height of its bending part does not exceed the buffer pad, thus ensuring a small space envelope in its retracted state. The present invention adopts structural mechanism function designs such as space deployable structures and flexible skins to achieve the goal of restraining debris splashing during the constrained anchoring and attachment process, and has the technical characteristics of being lightweight and efficient.

Description

Technical Field

[0001] The present invention belongs to the technical field of aerospace space capture, offense and defense, and relates to a space flexible shield for restraining debris splash during the constrained anchoring and attachment process. Background Art

[0002] With the increase in human space exploration activities, a large number of space debris have been generated, which have seriously threatened the safe operation of spacecraft. In order to avoid collision risks, spacecraft need to frequently perform orbital maneuvers, greatly shortening the in-orbit life of spacecraft. Therefore, the research on space debris capture has always been the focus of research in the field of space applications. In particular, the space capture scheme proposed based on the concept of anchoring and attachment has attracted more attention at home and abroad. A variety of capture schemes have been proposed around this, such as the "Harpoon" scheme of the European Space Agency and the "Adaptive Penetration Deployment Attachment Device" of the Beijing Institute of Space Mechanics and Electricity.

[0003] The above schemes all adopt platform close-range launch and rely on kinetic energy to penetrate the target surface to establish a connection with the target body. During this process, there is no space constraint ability for the externally splashed debris generated during the penetration process, and there are potential hazards such as damage to the drag rope and collision between the satellite launch platform and the debris. Regarding space debris protection, the volume and weight of traditional rigid protection structures cannot be applied to the anchoring and attachment device, and due to a series of system components such as drive and locking in the traditional mechanism, the volume and weight cannot match the requirements of the anchoring and attachment device even more. Summary of the Invention

[0004] In order to solve the above technical problems, in view of the actual needs of restraining debris splash, protecting the drag rope and the satellite launch platform during the anchoring penetration process in space debris removal, and aiming at the defects that the schemes of traditional rigid protection screens and deployment mechanisms are complex and their volume and weight are difficult to match the anchoring device, the present invention provides a space flexible shield device for restraining debris splash during the constrained anchoring and attachment process. The present invention adopts structural mechanism function designs such as space deployable structures and flexible skins to achieve the goal of restraining debris splash during the constrained anchoring and attachment process, and it has the technical characteristics of being lightweight and efficient.

[0005] The present invention is implemented as follows:

[0006] A space flexible shield for restraining debris splash during the constrained anchoring attachment process, including a flexible shield, characterized in that the flexible shield can be folded and retracted, and the flexible shield is connected to the anchoring attachment device through a protective connection seat; the protective connection seat and the anchoring attachment device are of an integral structure, and the protective connection seat and the anchoring attachment device are integrated (it is recommended to adopt the mode of initially designing a section of the protective connection seat on the anchoring attachment device. Since it is a functional component, its spatial layout position only needs to avoid the anchor tip and be arranged according to the volume envelope. Moreover, due to its flexible deployable characteristics, it also provides a large design space and margin for the layout parts of the protective connection seat and the anchoring attachment device).

[0007] The flexible shield includes a number of sets of super-elastic hinges connected to the protective connection seat. The super-elastic hinges and the protective connection seat (1) are connected by M2.5 screws. The ends of four sets of super-elastic hinges are connected by a strengthening support sheet. A flexible skin is arranged in the area between the super-elastic hinges and the strengthening support sheet;

[0008] The flexible skin is of a trapezoidal structure, including a first restraint sleeve, a second restraint sleeve, a third restraint sleeve and a flexible fabric. The first restraint sleeve and the second restraint sleeve have the same size and are the waists of the trapezoidal structure; the first restraint sleeve and the second restraint sleeve are connected to the super-elastic hinges, and the super-elastic hinges are restrained through the first restraint sleeve and the second restraint sleeve; the third restraint sleeve is the bottom of the trapezoidal structure, and the third restraint sleeve is connected to the strengthening support sheet, and the strengthening support sheet is restrained through the third restraint sleeve;

[0009] The first restraint sleeve and the second restraint sleeve are respectively provided with a second locking ring and a first locking ring at the bottom end. A locking rope is arranged between the second locking ring and the first locking ring. After passing through the locking rings, it will surround the entire trapezoidal structure. At this time, the trapezoidal structure is retracted together. When the flexible shield is retracted during the launch stage, it is restrained by the locking rope to keep its retracted and folded state.

[0010] Furthermore, the cross-sectional perimeter size of the first restraint sleeve and the second restraint sleeve is consistent with the perimeter of the super-elastic hinge. The first restraint sleeve, the second restraint sleeve and the super-elastic hinge are sewn together with aramid yarn and flexible composite fabric. The first restraint sleeve and the second restraint sleeve are similar to forming a cloth sleeve to enclose the super-elastic hinge. The size of the third restraint sleeve is consistent with the perimeter of the strengthening support sheet, and the third restraint sleeve and the strengthening support sheet are also sewn together with aramid yarn and flexible composite fabric.

[0011] Furthermore, the protective connection seat and the anchoring attachment device are an integrated structure; an even number of conformal interfaces are arranged on the protective connection seat, the cross-section of the super-elastic hinge is connected to the conformal interface, the size of the conformal interface is matched with the cross-sectional size of the super-elastic hinge, and each interface has a through hole for passing an M2.5 screw and is connected to the super-elastic hinge.

[0012] Furthermore, the superelastic hinge is made of composite material T300, with a single layer thickness of 0.02 mm and a 45 / -45 / 0 / -45 / 45 ply. The cross section of the superelastic hinge (2) is a double Ω configuration. The double Ω configuration can store energy during the folding process and self-rigidify after unfolding. The curvature section R of the superelastic hinge (2) includes six arcs, which together with the central angle Φ form a double Ω configuration with a cross-sectional length W and a height h.

[0013] Furthermore, the cross-sectional configuration of the reinforcing support sheet (4) is the same as that of the single piece of the superelastic hinge (2), which is a single Ω structure. The material of the reinforcing support sheet (4) is the composite material T300, the single layer thickness is 0.02 mm, and a 45 / -45 / 0 / -45 / 45 ply is used; the reinforcing support sheet cooperates with the superelastic hinge to form a quasi-rigid frame, thereby constraining the internal flexible skin.

[0014] Furthermore, the flexible skin is a fabric Kevlar layer with a thickness of 0.05 mm. After the flexible skin collides with the debris, under the joint action of the superelastic hinge and the reinforced support sheet, the flexible skin forms a net bag configuration to resist the collision of the debris, thereby restraining the splashing of the debris.

[0015] Furthermore, the locking rope is held by a cutter, which has a small hole. After the locking rope passes through the hole, the cutter itself is fixed, thereby fixing the locking rope to resist the mechanical load during the launch process; in this patent, the cutter is installed using the M4 threaded interface provided by the platform surface of the launch device. The installation of the cutter can also be arranged at other locations.

[0016] Furthermore, when the anchoring and attaching device penetrates the target object and only relies on the buffer pad to provide debris protection, the debris-free area is a cone angle of 9°. After installing the flexible protective shield, the protection cone angle is 54°. Compared with before this patent was adopted, the unilateral protection range has expanded by 45°, thus more effectively protecting the drag rope and the satellite platform. When the flexible protective shield is not installed, its protection is only provided by the buffer pad, which is a cone angle of 9°. After installing the flexible protective shield, the protection cone angle is 54°, thus protecting the drag rope and the satellite platform. Two seconds before the anchoring and attaching device is in the launch state, the cutter cuts off the locking rope, and the super-elastic hinge of the flexible protective shield stores and releases energy, driving the flexible skin to unfold. Under the combined action of the system damping of the super-elastic hinge, the strengthening support piece, and the flexible skin, stability is achieved. The symmetrical super-elastic hinge ensures that the initial launch state of the anchoring and attaching device will not be disturbed due to mass asymmetry. When debris splashes onto the flexible protective shield, the debris trajectory is constrained to ensure the safety of the drag rope and the satellite launch platform.

[0017] Furthermore, the working sequence of the flexible protective shield is as follows:

[0018] Step 1: The satellite launch platform scouts the target, and after selection, determines the anchoring target.

[0019] Step 2: In the triggering sequence of the anchoring and attaching device, the cutter ignites and operates.

[0020] Step 3: The locking rope is cut off, and the protective shield unfolds relying on its own energy storage.

[0021] Step 4: It reaches stability through the self-oscillation energy consumption of the protective shield.

[0022] Step 5: The anchoring device is launched, leaving the satellite launch platform with the protective shield and the drag rope.

[0023] Step 6: The anchoring device approaches and penetrates the anchoring target.

[0024] Step 7: The protective shield inhibits the debris splashing path and constrains the debris trajectory.

[0025] Step 8: The anchoring device operates normally, and the satellite platform safely flies away.

[0026] The beneficial effects of the present invention compared with the prior art are as follows:

[0027] 1) The scheme for constraining debris splashing during the anchoring and attaching process in the present invention, 2) the connection method between the flexible protective shield and the anchoring and attaching device, 3) the initial locking method and the unfolding driving method, 4) the connection method between the flexible skin and the super-elastic hinge, and 5) the super-elastic hinge material and the laying method in the present invention are all creative compared with the prior art.

[0028] The device of the present invention adopts a space deployable structure, which has the characteristics of passive driving, small impact upon reaching the position, self-rigidifying after deployment, etc. It integrates the functions of driving elements, damping devices, locking devices, etc. of traditional driving mechanisms, avoiding the defects of complex system composition such as driving and rigidifying, and realizing the functions of foldable launch and self-driven deployment in orbit. Through the flexible skin attached to the deployable structure, the protection area is expanded, thus realizing the spatial constraint on flying debris. At the same time, this protective shield can also reduce the excessive penetration speed to avoid the risk of the anchoring and attachment device completely penetrating into the target body.

[0029] During the initial folding and unfolding and in-orbit deployment of the device of the present invention to achieve anchoring and attachment, it protects the drag rope and the satellite launch platform, reducing the risk of their damage; the present invention can meet the requirements of space debris capture and removal, and has the possibility of expanding to the space attack and defense field of capturing other non-cooperative space targets.

[0030] The present invention is applicable to various space systems that need protection. Based on flexible protection, it provides a space protective shield for constraining the flying debris during the anchoring and attachment process, and can also be used in the military and civilian impact protection fields, etc. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 It is a schematic structural diagram of a space flexible protective shield for constraining the flying debris during the anchoring and attachment process of the present invention;

[0032] Figure 2 It is a schematic structural diagram of the protective connection seat of a space flexible protective shield for constraining the flying debris during the anchoring and attachment process of the present invention;

[0033] Figure 3 It is a schematic cross-sectional diagram of the super-elastic hinge of a space flexible protective shield for constraining the flying debris during the anchoring and attachment process of the present invention;

[0034] Figure 4 It is a schematic diagram of the flexible skin of a space flexible protective shield for constraining the flying debris during the anchoring and attachment process of the present invention;

[0035] Figure 5 It is a schematic diagram of the strengthening support sheet of a space flexible protective shield for constraining the flying debris during the anchoring and attachment process of the present invention;

[0036] Figure 6 It is a diagram of the retracted and locked state of a space flexible protective shield for constraining the flying debris during the anchoring and attachment process of the present invention;

[0037] Figure 7 It is a top view schematic diagram of a space flexible protective shield for constraining the flying debris during the anchoring and attachment process of the present invention;

[0038] Figure 8Front view schematic diagram of the spatial flexible shield for restraining debris splashing during the constrained anchoring and attachment process of the present invention;

[0039] Figure 9 Schematic diagram of the flexible shield during the anchoring process of the spatial flexible shield for restraining debris splashing during the constrained anchoring and attachment process of the present invention;

[0040] Figure 10 Working timing diagram of the spatial flexible shield for restraining debris splashing during the constrained anchoring and attachment process of the present invention.

[0041] Among them, 1 - protection connection seat, 2 - super-elastic hinge, 3 - flexible skin, 4 - strengthening support piece, 5 - first restraint sleeve, 6 - second restraint sleeve, 7 - first locking ring, 8 - third restraint sleeve, 9 - second locking ring, 10 - satellite platform, 11 - anchoring and attachment device, 12 - flexible shield, 13 - launch device, 14 - locking rope, 15 - cutter, 16 - target body, 17 - buffer pad, 18 - resistance rope. Detailed implementation method

[0042] To make the purpose, technical solution and effects of the present invention clearer and more definite, the following examples are listed to further elaborate on the present invention in detail. It should be noted that the specific implementation described here is only used to explain the present invention and is not used to limit the present invention.

[0043] As Figures 1 to 9 shown, a spatial flexible shield for restraining debris splashing during the constrained anchoring and attachment process of the present invention includes 1 protection connection seat, 4 sets of super-elastic hinges, 4 sets of flexible skins and 4 sets of strengthening support pieces, etc. As the main components, when installed on the spear body, 1 set of locking ropes and 2 sets of cutters are required for redundant backup. Specifically, it includes the flexible shield 12. The flexible shield is connected to the anchoring and attachment device 11 through the protection connection seat 1 (by M2.5 screws). The basic composition of the flexible shield 12 is as Figure 1 shown. The flexible shield 12 can be folded and retracted by itself. In this state, it is maintained by the locking rope 14 passing through the locking ring and using the cutter 15 to resist the mechanical load during the launch process. In this patent, the cutter borrows the interface provided by the platform surface of the launch device 13 for installation. The installation of the cutter can also be arranged in other positions. The folded and retracted flexible shield 12 ensures that it can be unfolded after the locking rope is released with its own elastic buckling characteristics, and the entire process does not need to consider structural damage. The height of its bending part does not exceed the buffer pad 17, thus ensuring that its retracted state has a small space envelope.

[0044] The protective connection seat is integrated with the anchoring attachment device (it is recommended to initially design a section of the protective connection seat on the anchoring attachment device. Because it is a functional component, its spatial layout position only needs to avoid the anchor tip and be arranged according to the volume envelope. Moreover, due to its flexible and expandable characteristics, the layout position of the protective connection seat and the anchoring attachment device also has a large design space and margin).

[0045] The flexible protective shield 12 includes a plurality of sets of super-elastic hinges 2 connected to a protective connecting seat 1, and the super-elastic hinges are connected to the protective seat via M2.5 screws. The ends of the four sets of super-elastic hinges 2 are connected by a reinforcing support sheet 4, and a flexible skin 3 is arranged in the area between the super-elastic hinge 2 and the reinforcing support sheet 4; the flexible skin 3 is a trapezoidal structure, including a first restraining sleeve 5, a second restraining sleeve 6, a third restraining sleeve 8 and a flexible fabric, the first restraining sleeve 5 and the second restraining sleeve 6 are of the same size and are the waist of the trapezoidal structure; the first restraining sleeve 5 and the second restraining sleeve 6 are connected to the super-elastic hinge 2, and the super-elastic hinge 2 is constrained by the first restraining sleeve 5 and the second restraining sleeve 6; the third restraining sleeve 8 is the bottom of the trapezoidal structure, the third restraining sleeve 8 is connected to the reinforcing support sheet 4, and the reinforcing support sheet 4 is constrained by the third restraining sleeve 8; the first restraining sleeve 5 and the second restraining sleeve 6 are respectively provided with a second locking ring 9 and a first locking ring 7 at the bottom ends, and a locking rope 14 is arranged between the second locking ring 9 and the first locking ring 7, which will surround the entire trapezoidal structure after passing through the locking ring, and the trapezoidal structure is now gathered together. When the flexible protective shield 12 is folded during the launch phase, it is folded and restrained by the locking rope 14 to maintain its folded state.

[0046] The cross-sectional perimeter size of the first restraint sleeve 5 and the second restraint sleeve 6 is consistent with the perimeter of the superelastic hinge 2. The first restraint sleeve 5, the second restraint sleeve 6 and the superelastic hinge 2 are sewn together with aramid thread and flexible composite fabric. The first restraint sleeve 5 and the second restraint sleeve 6 are similar to forming a cloth sleeve to put the superelastic hinge in. The size of the third restraint sleeve 8 is consistent with the perimeter of the reinforcing support sheet 4. The third restraint sleeve 8 and the reinforcing support sheet 4 are also sewn together with aramid thread and flexible composite fabric.

[0047] The described protective connection seat 1 and the anchoring and attaching device 11 are of an integrated structure; an even number of conforming interfaces are provided on the protective connection seat 1. The cross-section of the super-elastic hinge 2 is connected to the conforming interfaces. The size of the conforming interfaces matches the cross-sectional size of the super-elastic hinge 2. Each interface is provided with a through-hole for passing an M2.5 screw, which is connected to the super-elastic hinge. An even number of conforming interfaces are provided (in this patent, there are 4, and the size of the conforming interfaces matches the cross-sectional size of the super-elastic hinge). Each interface is provided with a through-hole for passing an M2.5 screw for connection to the super-elastic hinge. The use of an even number of interfaces is to ensure that during the unfolding process and after unfolding, the centroid of the anchoring and attaching device does not change significantly, thus preventing the influence on the flight trajectory and further causing a miss.

[0048] As Figure 3 shown, the super-elastic hinge 2 is made of composite material T300 with a single-layer thickness of 0.02 mm and is laid with 45 / -45 / 0 / -45 / 45 plies. The cross-section of the super-elastic hinge 2 is of a double-Ω configuration, and the double-Ω configuration can store energy by itself during the folding process and self-rigidify after unfolding; the curvature section R of the super-elastic hinge 2 includes six arcs, which together with the central angle Φ form the double-Ω configuration of the cross-section length W and height h. In this embodiment, R is 6 mm and Φ is 60° (L1 is 1 mm). The length value of L1 is determined by process parameters. R and Φ are determined by the driving moment formula of the elastic thin shell theory (the driving moment is the sum of the forward folding driving moment and the reverse folding driving moment. In engineering design, the additional moment caused by folding contact can be ignored), where the driving moment should be greater than twice the moment generated by the weight of the flexible fabric to ensure the smooth driving of the flexible fabric to unfold in orbit and resist the collision force of debris. The entire hinge is formed by integrated adhesive bonding.

[0049] The cross-sectional configuration of the strengthening support sheet 4 is the same as that of a single piece of the super-elastic hinge 2. As Figure 5 shown, it is of a single-Ω structure. The material of the strengthening support sheet 4 is composite material T300 with a single-layer thickness of 0.02 mm and is laid with 45 / -45 / 0 / -45 / 45 plies. The function of the strengthening support sheet is to cooperate with the super-elastic hinge to jointly form a quasi-rigid "frame" to constrain the internal flexible skin, and its configuration adopts a single "Ω" structure.

[0050] The flexible skin 3 is a Kevlar fabric layer with a thickness of 0.05 mm; after the flexible skin collides and contacts with debris, under the joint action of the super-elastic hinge 2 and the strengthening support sheet 4, the flexible skin forms a net pocket configuration to resist the collision of debris, thereby constraining the splashing of debris. The flexible skin is in a trapezoidal structure, and on the basis of fully utilizing the original buffer pad of the anchoring and attaching device, the weight is optimized (the fabric material in the overlapping area is removed, so it is changed from a triangle to a trapezoid).

[0051] The locking rope 14 is held by a cutter 15. The cutter has a small hole. After the locking rope passes through the hole, due to the fixation of the cutter itself, the locking rope is fixed to withstand the mechanical load during the launch process. In this patent, the cutter is installed by borrowing the M4 thread interface provided by the platform surface of the launch device 13. The basic installation schematic diagram is as shown in Figure 9 shown. The installation of the cutter can also be arranged in other positions.

[0052] When the anchoring and attaching device 11 penetrates the target body 16, when only relying on the buffer pad 17 to provide debris protection, the debris-free area is a cone angle of 9°. After installing the flexible protective shield 12, the protection cone angle is 54°. Compared with before adopting this patent, the unilateral protection range is expanded by 45°, thus more effectively protecting the drag rope 18 and the satellite platform 10. When the flexible protective shield 12 is not installed, its protection is only provided by the buffer pad 17, which is a cone angle of 9°. After installing the flexible protective shield 12, the protection cone angle is 54°, thus protecting the drag rope 18 and the satellite platform 10.

[0053] Two seconds before the anchoring and attaching device 11 is in the launch state, the cutter cuts off the locking rope, and the super-elastic hinge energy storage of the flexible protective shield 12 is released, driving the flexible skin 3 to unfold. Under the combined action of the system damping of the super-elastic hinge, the strengthening support piece 4, and the flexible skin, it reaches stability. The symmetric super-elastic hinge ensures that the initial launch state of the anchoring and attaching device will not be disturbed due to mass asymmetry. When debris splashes onto the flexible protective shield, the debris trajectory is constrained to ensure the safety of the drag rope and the satellite launch platform.

[0054] As shown in Figure 10 shown, the working sequence of the flexible protective shield 12 is as follows:

[0055] Step 1: The satellite launch platform scouts the target, and after selection, determines the anchoring target;

[0056] Step 2: Trigger the timing sequence of the anchoring and attaching device, and the cutter ignites and works;

[0057] Step 3: The locking rope is cut off, and the protective shield unfolds relying on its own energy storage;

[0058] Step 4: Reach stability through the energy consumption of the self-oscillation of the protective shield;

[0059] Step 5: The anchoring device is launched, and leaves the satellite launch platform with the protective shield and the drag rope;

[0060] Step 6: The anchoring device approaches and penetrates the anchoring target;

[0061] Step 7: The protective shield inhibits the debris splashing path and constrains the debris trajectory;

[0062] Step eight, the anchoring device works normally and the satellite platform safely flies away.

[0063] The above are only the preferred embodiments of the present invention. It should be noted that for those of ordinary skill in the art, several improvements can be made without departing from the principle of the present invention, and these improvements should also be regarded as the protection scope of the present invention.

Claims

1. A space flexible shield for restraining debris splash during constrained anchoring attachment, comprising a flexible shield (12), characterized in that, The flexible protective shield (12) can be folded and retracted, and the flexible protective shield (12) is connected to the anchoring and attaching device (17) through the protective connecting seat (1); the protective connecting seat (1) and the anchoring and attaching device (17) are of an integral structure. The flexible protective shield (12) includes a number of sets of super-elastic hinges (2) connected to the protective connecting seat (1). The ends of four sets of super-elastic hinges (2) are connected by a strengthening support sheet (4). A flexible skin (3) is arranged in the area between the super-elastic hinges (2) and the strengthening support sheet (4). The flexible skin (3) is of a trapezoidal structure, including a first restraint sleeve (5), a second restraint sleeve (6), a third restraint sleeve (8) and a flexible fabric. The first restraint sleeve (5) and the second restraint sleeve (6) are of the same size and are the waists of the trapezoidal structure. The first restraint sleeve (5) and the second restraint sleeve (6) are connected to the super-elastic hinge (2), and the super-elastic hinge (2) is constrained by the first restraint sleeve (5) and the second restraint sleeve (6). The third restraint sleeve (8) is the bottom of the trapezoidal structure, and the third restraint sleeve (8) is connected to the strengthening support sheet (4), and the strengthening support sheet (4) is constrained by the third restraint sleeve (8). The second locking ring (9) and the first locking ring (7) are respectively arranged at the bottom ends of the first restraint sleeve (5) and the second restraint sleeve (6). A locking rope (14) is arranged between the second locking ring (9) and the first locking ring (7). When the flexible protective shield (12) is retracted during the launching stage, it is retracted and constrained by the locking rope (14) to maintain its retracted and folded state.

2. The space flexible shield for restraining debris splash during constrained anchoring attachment according to claim 1, characterized in that, The cross-sectional perimeter dimensions of the first restraint sleeve (5) and the second restraint sleeve (6) are the same as the perimeter of the super-elastic hinge (2). The first restraint sleeve (5), the second restraint sleeve (6) and the super-elastic hinge (2) are sewn together with aramid yarn and flexible composite fabric. The size of the third restraint sleeve (8) is the same as the perimeter of the strengthening support sheet (4). The third restraint sleeve (8) and the strengthening support sheet (4) are also sewn together with aramid yarn and flexible composite fabric.

3. The space flexible shield for restraining debris splash during constrained anchoring attachment according to claim 1, characterized in that, The protective connecting seat (1) and the anchoring and attaching device (17) are of an integrated structure; an even number of conforming interfaces are arranged on the protective connecting seat (1). The cross-section of the super-elastic hinge (2) is connected to the conforming interface. The size of the conforming interface matches the cross-sectional size of the super-elastic hinge (2). Each interface has a through-hole for passing an M2.5 screw and is connected to the super-elastic hinge.

4. The space flexible shield for restraining debris splash during constrained anchoring attachment according to claim 1, characterized in that, The super-elastic hinge (2) is made of composite material T300 with a single-layer thickness of 0.02 mm and is laid with 45 / -45 / 0 / -45 / 45. The cross-section of the super-elastic hinge (2) is of a double-Ω configuration, and the double-Ω configuration can store energy by itself during the folding process and self-rigidify after unfolding; the super-elastic hinge (2) includes an adhesive butt joint (11). The curvature section R of the super-elastic hinge (2) includes six arcs, which together with the central angle Φ form a double-Ω configuration of the cross-sectional length W and height h.

5. The space flexible shield for restraining debris splash during constrained anchoring attachment according to claim 1, characterized in that, The cross-sectional configuration of the reinforcing support sheet (4) is the same as that of the single piece of the superelastic hinge (2), which is a single Ω structure. The material of the reinforcing support sheet (4) is the composite material T300, the single layer thickness is 0.02 mm, and a 45 / -45 / 0 / -45 / 45 ply is used; the reinforcing support sheet (4) cooperates with the superelastic hinge (2) to form a quasi-rigid frame, thereby constraining the internal flexible skin.

6. The space flexible shield for restraining debris splash during constrained anchoring attachment according to claim 5, characterized in that, The flexible skin (3) is a Kevlar fabric layer with a thickness of 0.05 mm. After the flexible skin collides with the debris, under the joint action of the superelastic hinge (2) and the reinforcing support sheet (4), the flexible skin forms a net bag configuration to resist the collision of the debris, thereby restraining the splash of the debris.

7. The space flexible shield for restraining debris splash during constrained anchoring attachment according to claim 1, characterized in that, The locking rope (14) is held by a cutter (15) to resist the mechanical load during the launching process; the cutter is installed by using the M4 threaded interface provided by the platform surface of the launching device (13).

8. The space flexible shield for restraining debris splash during constrained anchoring attachment according to claim 1, characterized in that, When the anchoring attachment device (17) penetrates the target body (16), the area not affected by the debris is a cone angle of 9°, and after the flexible protective shield (12) is installed, the protection cone angle is 54°. Compared with before adopting this patent, the unilateral protection range is expanded by 45°, thereby more effectively protecting the resistance rope (18) and the satellite platform (10); Two seconds before the anchoring attachment device (17) is in the firing state, the cutter cuts off the locking rope, and the flexible protective shield (12) drives the flexible skin (3) to unfold under the energy storage release of the superelastic hinge; stability is achieved under the combined effect of the superelastic hinge, the reinforcing support sheet (4), and the system damping of the flexible skin; the symmetrical superelastic hinge ensures that the anchoring attachment device will not be disturbed by mass asymmetry in the initial state of firing; When the fragments splash onto the flexible protective shield, the trajectory of the fragments is constrained to ensure the safety of the resistance rope and the satellite launch platform.

9. The space flexible shield for restraining debris splash during constrained anchoring attachment according to any one of claims 1 to 8, characterized in that, The working sequence of the flexible protective shield (12) is: Step 1: The satellite launch platform detects the target and determines the anchor target after selection; Step 2: The anchoring attachment device triggers the timing sequence, and the cutter ignites and works; Step 3: The locking rope is cut, and the shield deploys by relying on its own energy storage; Step 4: The shield itself vibrates and consumes energy to reach stability; Step 5: The anchoring device is launched, and the protective shield and resistance rope leave the satellite launch platform; Step 6: The anchoring device approaches and penetrates the anchoring target; Step 7: The shield suppresses the splash path of the fragments and constrains the trajectory of the fragments; Step 8: The anchoring device works normally and the satellite platform flies away safely.

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