Protection and capture mechanism based on composite fold collaborative deformation and satellite

Abstract

The invention provides a protection and capture mechanism based on composite fold collaborative deformation and a satellite, and relates to the technical field of satellite protection. The protection and capture mechanism comprises an energy-absorbing foldable bottom plate and two bent mark folding plates which are made of shape memory materials, in the protection mode, the portions, between the starting point and the end point, of the bent mark folding plates are arched upwards, the remaining portions of the bent mark folding plates are bent upwards through preset linear folds, and the shape memory materials are arranged in the shape memory materials. A satellite is encircled by the two bent mark folding plates; and in the capturing mode, the part, between the starting point and the ending point, of each bent mark folding plate is arched downwards, and the remaining part of each bent mark folding plate is bent downwards through a preset linear folding mark, so that the two bent mark folding plates capture the non-cooperative target.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of satellite protection, and particularly relates to a protection and capturing mechanism based on composite fold coordination deformation and a satellite. BACKGROUND

[0002] With the development of space technology, the challenges faced by the satellite in-orbit operation environment are increasingly prominent. In the launch phase, the satellite needs to withstand the complex vibration environment of the rocket body transferred to the inside of the fairing; during in-orbit operation, it faces the dual threats of space radiation and space debris impact. The existing protection technology is difficult to solve these multi-physical field coupling problems at the same time, which seriously affects the service life of the satellite and the normal work of the effective load. On the other hand, with the increasing frequency of human space activities, the number of non-cooperative targets in space has increased dramatically, not only occupying valuable orbital resources, but also posing a serious security threat to in-orbit spacecraft. Traditional non-cooperative target capture mainly relies on mechanical rigid grippers, but they have inherent defects such as poor impact resistance, large weight, and bulky size, which are not conducive to satellite launch and in-orbit operation. SUMMARY

[0003] The problem solved by the present application is how to realize the intelligent protection and capturing of the satellite in the whole cycle.

[0004] To solve the above problems, on the one hand, the present application provides a protection and capturing mechanism based on composite fold coordination deformation, which comprises a piece of energy-absorbing foldable bottom plate and two pieces of fold plate with folds, all made of shape memory material. The energy-absorbing foldable bottom plate is located between the two pieces of fold plate with folds and is used to connect with the satellite. The energy-absorbing foldable bottom plate comprises a plurality of straight folds, and the plurality of straight folds are arranged in parallel along a first calibration direction of the energy-absorbing foldable bottom plate. The energy-absorbing foldable bottom plate comprises a side edge located in a second calibration direction, and the first calibration direction is perpendicular to the second calibration direction. The fold plate with folds comprises a connecting edge corresponding to the side edge, and a preset curved fold and a preset straight fold. The starting point and the ending point of the preset curved fold are both located between the two ends of the connecting edge. The two ends of the side edge in the first calibration direction are located at the starting point and the ending point respectively, and are connected with the connecting edge respectively. One end of the preset straight fold starts from the midpoint of the preset curved fold, and the other end extends to the other end of the fold plate with folds along the second calibration direction. In the protection mode, the energy-absorbing foldable bottom plate is folded, and the two outermost straight folds in the first calibration direction are bent upwards. The side edge drives the fold plate with folds to fold along the preset curved fold, so that the part of the fold plate with folds surrounded by the preset curved fold is arched upwards, and the remaining part is bent upwards while bending towards the other fold plate with folds with the preset straight fold as the reference line, so that the two fold plates with folds enclose the satellite. In the capturing mode, the energy-absorbing foldable bottom plate is folded, and the two straight creases located at the outermost side in the first designated direction are bent downward, the side edges drive the curved crease folding plates to fold along the preset curved creases, so that the part of the curved crease folding plates surrounded by the preset curved creases arches downward, and the remaining part bends downward while bending toward another curved crease folding plate with the preset straight creases as the reference line, so as to enclose the two curved crease folding plates to capture the non-cooperative target.

[0005] Optionally, in the unfolded state, each of the curved crease folding plates is rectangular, and the two curved crease folding plates are enclosed to form a cylindrical shape.

[0006] Optionally, in the on-orbit operation stage, when it is detected that the satellite enters a predetermined orbit position or a ground instruction is received, the energy-absorbing foldable bottom plate and the curved crease folding plates restore to the planar state through the shape memory effect, and the energy-absorbing foldable bottom plate is attached to the surface of the satellite.

[0007] Optionally, the energy-absorbing foldable bottom plate comprises a honeycomb buffer structure in an outer layer, a corrugated plate energy dissipation layer in a middle layer, and a shape memory polymer matrix in an inner layer, and the corrugated plate energy dissipation layer is connected between the shape memory polymer matrix and the honeycomb buffer structure.

[0008] Optionally, the thickness of the energy-absorbing foldable bottom plate and the curved crease folding plates in the planar state is not more than 10 mm.

[0009] Optionally, in the capturing mode, the energy-absorbing foldable bottom plate and the curved crease folding plates complete the folding deformation within a first time, and the first time ranges from 1 to 5 seconds.

[0010] Optionally, the shape memory intelligent protective capturing mechanism further comprises a temperature / strain sensor network for real-time monitoring of the deformation state.

[0011] Optionally, the shape memory intelligent protective capturing mechanism further comprises a self-diagnosis system for evaluating the integrity of the protective structure and a wireless communication module for realizing data interaction with the satellite main control system.

[0012] Optionally, the outer surface of the energy-absorbing foldable bottom plate and the curved crease folding plates is coated with a multi-layer buffer and anti-radiation coating, and the crease area is subjected to wear-resistant strengthening treatment.

[0013] Compared with the related art, the protection and capture mechanism based on composite fold line cooperative deformation of the application can make the energy-absorbing foldable bottom plate fold or expand through the plurality of straight fold lines on the energy-absorbing foldable bottom plate, can make the curved fold plate fold or expand through the preset curved fold line and the preset straight fold line 3 of the curved fold plate, can make the curved fold plate deform along with the folding of the energy-absorbing foldable bottom plate through the fact that the starting point and the ending point of the preset curved fold line are located between the two ends of the connecting edge, the two ends of the side edge in the first calibration direction are respectively located at the starting point and the ending point, and the two ends are respectively connected with the connecting edge, thereby realizing the intelligent switching of the vibration impact protection in the launch stage and the debris protection and non-cooperative target capture in the on-orbit stage through the unique "straight fold line-curved fold line" cooperative deformation mechanism, breaking through the limitation that the traditional spacecraft needs to independently configure passive protection structures and active mechanical arms, significantly reducing the system mass and structural complexity, and through the integrated curved fold structure design, not only ensuring the high reliability and accuracy of the deformation process, but also significantly improving the energy absorption efficiency of the system. The intelligent response mechanism of the shape memory material can also endow the system with excellent adaptive ability, so that the system can autonomously decide and switch the optimal working mode according to the dynamic changes of the space environment, effectively breaking through the limitation of the single function of the traditional rigid protection structure. When impacting, the folding of the energy-absorbing foldable bottom plate can convert the vibration impact energy in the vertical direction (the thickness direction of the energy-absorbing foldable bottom plate) into horizontal compression deformation, which can effectively buffer the high-frequency vibration in the launch stage and the ultra-high-speed impact of micro meteoroids in the on-orbit stage, and improve the satellite environmental adaptability and survivability. The bidirectional deformation capability of the energy-absorbing foldable bottom plate and the curved fold plate makes the energy-absorbing foldable bottom plate and the curved fold plate have the advantages of rigid protection and flexible storage, ensures to provide all-around protection, and realizes extremely high space utilization, thereby providing a new technical route and development direction for the intelligent protection of future spacecrafts.

[0014] In another aspect, the application also provides a satellite comprising the protection and capture mechanism based on composite fold line cooperative deformation as described above.

[0015] The satellite has all the beneficial effects of the protection and capture mechanism based on composite fold line cooperative deformation, which will not be repeated here. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 FIG. 1 is a structural schematic diagram of an energy-absorbing foldable bottom plate and a curved fold plate in an embodiment of the application; Figure 2 FIG. 2 is a structural schematic diagram of the energy-absorbing foldable bottom plate when folding in an embodiment of the application; Figure 3 FIG. 3 is a structural schematic diagram of the energy-absorbing foldable bottom plate and the curved fold plate in a protection mode in an embodiment of the application; Figure 4This is a schematic diagram of the structure of the two curved folded plates in the protective mode when they are fully closed in an embodiment of the present invention; Figure 5 This is a schematic diagram of the energy-absorbing foldable base plate and the curved foldable plate in the capture mode according to an embodiment of the present invention. Figure 6 This is a schematic diagram of the structure of the two curved folded plates in the capture mode when they are fully closed in an embodiment of the present invention.

[0017] Explanation of reference numerals in the attached figures: 1-Energy-absorbing foldable base plate; 11-Straight crease; 12-Side edge; 2-Curved crease folding plate; 21-Connecting edge; 22-Preset curved crease; 23-Preset straight crease. Detailed Implementation

[0018] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0019] In the accompanying drawings, the X-axis represents left and right positions, with the positive direction of the X-axis representing the right side and the negative direction representing the left side; the Y-axis represents front and back positions, with the positive direction of the Y-axis representing the front and the negative direction representing the back; and the Z-axis represents up and down positions, with the positive direction of the Z-axis representing the top and the negative direction representing the bottom. It should be noted that the aforementioned representations of the X, Y, and Z axes are merely for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as limiting the invention.

[0020] It should be noted that the terms "first," "second," etc., used in the specification and claims of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in sequences other than those illustrated or described herein.

[0021] Preliminary instructions: The shape memory composite material comprises a matrix material of polycaprolactone (PCL) or polyurethane (PU) type shape memory polymer; a reinforcing phase of 5%-20% by mass of carbon nanotubes or graphene; and a radiation-resistant additive of 1%-5% by mass of metal oxide nanoparticles. The shape recovery rate of the composite material under vacuum environment is not less than 98%.

[0022] Both the energy-absorbing foldable base plate 1 and the foldable plate with curved marks are made of shape memory composite material, with the shape memory transition temperature set between -10℃ and 60℃.

[0023] The straight creases 11 of the energy-absorbing foldable base plate 1 can be designed as needed, and there are no requirements on the number, length and shape of the straight creases 11.

[0024] The preset curved crease 22 of the curved fold plate 2 can be designed as needed, as long as it ensures that the curved fold plate 2 can fully cover the satellite according to the deformation of the curved crease. The curved fold plate 2 adopts a variable curvature crease design, specifically including: micro creases with a radius of 0.5-1.5mm in stress concentration areas; continuously varying curvature creases in the main deformation areas, with a curvature radius ranging from 2-15mm; and straight reinforcing creases in the edge connection areas.

[0025] The connection between the energy-absorbing foldable base plate 1 and the two curved foldable plates 2 can adopt a connection scheme with tight power transmission and integrated structure. For example, mechanical hinge connection: a rigid-flexible coupling is achieved through a high-strength micro-rotor shaft and a limiting buckle, which can ensure the effective transmission of force and maintain tight structural linkage; or elastic deformation connection: shape memory alloy or super-elastic metal strip is used for integrated bending and forming. For example, two elastic metal strips are extended along the preset curve folds 22 of the two curved foldable plates 2, and the two ends of each elastic metal strip are connected to the corresponding side 12 of the energy-absorbing foldable base plate 1, so that the base plate and the shell form a continuous deformable integral structure; or embedded interlocking connection: an interlocking tooth structure is formed on the connection surface by laser etching, which keeps the contact surface tightly engaged during deformation; or prestressed strap connection: carbon fiber composite braided tape is used to wrap the connection part, and the tension is adjusted by shape memory alloy to achieve dynamic control of the connection tightness; or 3D printed integrated structure: additive manufacturing technology is used to print the base plate and the shell as an integral component with the characteristics of a live hinge.

[0026] The connection mechanism between the protection and capture mechanism based on the composite crease collaborative deformation and the satellite may include a detachable electromagnetic adsorption array (the adsorption force of a single adsorption unit is not less than 50N) or a shape memory alloy locking mechanism to achieve active locking and unlocking under temperature triggering; or a mechanical quick-release connector to support on-orbit replacement operations by an extravehicular robot.

[0027] Combination Figures 1 to 6As shown, this embodiment of the invention provides a protection and capture mechanism based on composite crease cooperative deformation, including an energy-absorbing foldable base plate 1 and two crease foldable plates 2, both made of shape memory material. The energy-absorbing foldable base plate 1 is located between the two crease foldable plates 2 and is used for connection with a satellite. The energy-absorbing foldable base plate 1 includes multiple straight creases 11, which are arranged parallel to each other along a first calibration direction of the energy-absorbing foldable base plate 1. The energy-absorbing foldable base plate 1 includes a side 12 located in its second calibration direction. The first calibration direction is perpendicular to the second calibration direction; the curved folding plate 2 includes a connecting edge 21 corresponding to the side edge 12, as well as a preset curved fold 22 and a preset straight fold 23. The starting point and the ending point of the preset curved fold 22 are both located between the two ends of the connecting edge 21. The two ends of the side edge 12 in the first calibration direction are located at the starting point and the ending point, respectively, and are connected to the connecting edge 21. One end of the preset straight fold 23 starts at the midpoint of the preset curved fold 22, and the other end extends along the second calibration direction to the other end of the curved folding plate 2. In protection mode, such as Figure 3 and Figure 4 As shown, the energy-absorbing foldable base plate 1 is folded, and the two outermost straight creases 11 located in the first calibration direction bend upward. The side 12 drives the curved fold plate 2 to fold along the preset curve crease 22, so that the part of the curved fold plate 2 surrounded by the preset curve crease 22 arches upward, and the remaining part bends upward while bending towards another curved fold plate 2 with the preset straight crease 23 as the baseline, so that the two curved fold plates 2 surround the satellite. In capture mode, such as Figure 5 and Figure 6 As shown, the energy-absorbing foldable base plate 1 is folded, and the two outermost straight creases 11 located in the first calibration direction bend downwards. The side 12 drives the curved fold plate 2 to fold along the preset curve crease 22, so that the part of the curved fold plate 2 surrounded by the preset curve crease 22 arches downwards, and the remaining part bends downwards while bending towards another curved fold plate 2 with the preset straight crease 23 as the baseline, so that the two curved fold plates 2 surround each other to capture non-cooperative targets.

[0028] Specifically, the energy-absorbing foldable base plate 1 is rectangular in shape. The first calibration direction is the length direction of the energy-absorbing foldable base plate 1, and the second calibration direction is the width direction of the energy-absorbing foldable base plate 1. The energy-absorbing foldable base plate 1 has multiple straight creases 11, each extending along the second calibration direction, and the multiple straight creases 11 are arranged along the first calibration direction. In the first calibration direction, the multiple straight creases 11 include the two outermost straight creases 11. The curved folding plate 2 can also be in a long-direction shape. In the second calibration direction, the two curved folding plates 2 are located at both ends of the energy-absorbing foldable base plate 1. The curved folding plate 2 includes a connecting edge 21 near the side edge 12 of the energy-absorbing foldable base plate 1. The starting point and the ending point of the preset curved fold 22 are both located between the two ends of the connecting edge 21 in the length direction. The two ends of the side edge 12 in the first calibration direction are located at the starting point and the ending point, respectively, and are connected to the connecting edge 21. One end of the preset straight fold 23 starts at the midpoint of the preset curved fold 22, and the other end extends along the second calibration direction to the other end of the curved folding plate 2.

[0029] The protection and capture mechanism based on composite crease cooperative deformation in this embodiment includes at least a protection mode and a capture mode, and in both modes, the energy-absorbing foldable base plate 1 and the curved crease folding plate 2 fold in opposite directions. Specifically, in the protection mode, when the ambient temperature reaches a set threshold or an electrical signal is received, the foldable base plate 1 triggers a shape memory effect. Guided by the preset creases, the energy-absorbing foldable base plate 1 folds along the first calibration direction, and the two outermost straight creases 11 bend upwards. The two ends of the side 12 apply a downward force to the curved crease folding plate 2 at the starting and ending points of the preset curved creases 22, respectively. Due to the proximity of the two ends of the side 12 during the folding process of the energy-absorbing foldable base plate 1, the side 12 can drive the curved crease folding plate 2 to be... The portion enclosed by the preset curved crease 22 arches upwards. Simultaneously, the remaining portion of the curved folded plate 2 bends and converges through the preset straight crease 23. As the energy-absorbing foldable base plate 1 folds, the arching and bending degree of the curved folded plate 2 increases, allowing the remaining portion of the curved folded plate 2 to shift towards the energy-absorbing foldable base plate 1 until the two curved folded plates 2 can be closed to form a columnar enclosing shell. The inner surface of the curved folded plate 2 maintains a 20-40mm protective gap with the outer surface of the satellite to ensure proper absorption of subsequent vibrations and impacts and successful deformation. In protective mode, when subjected to vibration and impact, the crease design of the foldable base plate 1 can convert vertical vibration energy into horizontal compressive deformation. This energy conversion mechanism not only achieves effective vibration absorption but also further enhances the tightness of the two curved folded plates 2 in enclosing the satellite.

[0030] In capture mode, the energy-absorbing foldable base plate 1 is still folded along the first calibration direction, but the two outermost straight creases 11 in the first calibration direction bend downwards. The two ends of the side 12 apply an upward force to the curved fold plate 2 at the starting point and the ending point of the preset curved crease 22, respectively. As the two ends of the side 12 approach each other during the folding process of the energy-absorbing foldable base plate 1, the side 12 can drive the part of the curved fold plate 2 between the starting point and the ending point to arch downwards. After arching, the remaining part of the curved fold plate 2 bends and approaches again through the preset straight crease 23. As the energy-absorbing foldable base plate 1 is folded, the degree of arching and bending of the curved fold plate 2 increases, and the remaining part of the curved fold plate 2 can shift downwards toward the energy-absorbing foldable base plate 1 until the two curved fold plates 2 can be enclosed to form a columnar capture structure so that the two curved fold plates 2 can complete the grasping task of the non-cooperative target.

[0031] Therefore, in this embodiment, the multiple straight creases 11 on the energy-absorbing foldable base plate 1 allow the energy-absorbing foldable base plate 1 to be folded or extended. The preset curved creases 22 and preset straight creases 23 of the curved crease 2 allow the curved crease 2 to be folded or extended. Furthermore, since the starting point and ending point of the preset curved crease 22 are both located between the two ends of the connecting edge 21, and the two ends of the side edge 12 in the first calibration direction are located at the starting point and the ending point respectively, and are connected to the connecting edge 21 respectively, the curved crease 2 can deform as the energy-absorbing foldable base plate 1 is folded. Thus, through the unique "straight crease-curved crease" collaborative deformation mechanism, the intelligent switching between vibration and shock protection during the launch phase and debris protection and non-cooperative target acquisition during the on-orbit phase is realized. This breaks through the limitations of traditional spacecraft that require independent configuration of passive protection structures and active robotic arms, significantly reducing system mass and structural complexity. Moreover, through the integrated curved crease origami structure design, not only is the high reliability and accuracy of the deformation process ensured, but the energy absorption efficiency of the system is also significantly improved. Furthermore, the intelligent response mechanism of shape memory materials endows the system with outstanding adaptive capabilities, enabling it to autonomously make decisions and switch to the optimal operating mode based on dynamic changes in the space environment, effectively overcoming the limitations of the single function of traditional rigid protective structures. Upon impact, the folding of the energy-absorbing foldable base plate 1 converts the vertical (thickness direction of the energy-absorbing foldable base plate 1) vibrational impact energy into horizontal compressive deformation, effectively buffering high-frequency vibrations during launch and ultra-high-speed impacts from on-orbit micrometeoroids, thus enhancing the satellite's environmental adaptability and survivability. The bidirectional deformation capability of the energy-absorbing foldable base plate 1 and the curved folding plate 2 combines the advantages of rigid protection and flexible storage, ensuring comprehensive protection while achieving extremely high space utilization, providing a new technical route and development direction for the intelligent protection of future spacecraft.

[0032] Optionally, in the unfolded state, each curved folded plate 2 is rectangular, and two curved folded plates 2 together form a cylindrical shape. In this way, interference with other structures on the satellite can be reduced after the curved folded plates 2 are unfolded.

[0033] Optionally, during the on-orbit operation phase, when the satellite is detected to have entered the predetermined orbital position or when ground commands are received, the energy-absorbing foldable base plate 1 and the curved foldable plate 2 are restored to a planar state through the shape memory effect, and the energy-absorbing foldable base plate 1 is attached to the surface of the satellite.

[0034] Specifically, when the satellite enters its predetermined orbit or receives a ground control signal, the energy-absorbing foldable base plate 1 and the curved foldable plate 2, made of shape memory material, are activated to restore their recovery properties. A phase transition temperature is applied to the entire protective structure via a temperature control module, allowing residual stress accumulated in the folded state to be released through material molecular chain reconstruction. The predetermined orbital position is determined by continuous monitoring of orbital parameters by the onboard navigation system. When the ground station needs to intervene urgently, control commands are sent via an encrypted communication channel. During the recovery process, the originally folded energy-absorbing foldable base plate 1 and the curved foldable plate 2 gradually unfold under the action of material contraction force, ultimately restoring the entire protective structure to a flat thin plate structure. The unfolded energy-absorbing foldable base plate 1 maintains a tight fit with the satellite shell through a pre-set fixing interface, preventing the formation of additional protrusions.

[0035] Thus, during the on-orbit operation phase, when the satellite is detected to have entered its predetermined orbital position or when ground commands are received, the energy-absorbing foldable base plate 1 and the curved foldable plate 2 can be restored to a planar state through the shape memory effect. The energy-absorbing foldable base plate 1 is attached to the satellite surface. The planar attachment method allows the energy-absorbing foldable base plate 1 to be attached to the satellite shell to form an integrated structure, which can avoid the energy-absorbing foldable base plate 1 and the curved foldable plate 2 from blocking or interfering with sensitive components such as satellite optical equipment and antennas.

[0036] Optionally, the energy-absorbing foldable base plate 1 includes an outer honeycomb buffer structure, a middle corrugated plate energy dissipation layer, and an inner shape memory polymer matrix, with the corrugated plate energy dissipation layer connected between the shape memory polymer matrix and the honeycomb buffer structure.

[0037] Specifically, a honeycomb buffer structure refers to a porous topological configuration with a periodic arrangement of hexagons, which can be made of aluminum alloy honeycomb core material or carbon fiber reinforced composite material. Its porous nature can disperse impact loads through cell wall buckling deformation. A corrugated plate energy dissipation layer refers to a thin metal plate structure with a sinusoidal or trapezoidal waveform, which can be made of titanium alloy thin plate by roll forming process. Its periodic undulating structure converts kinetic energy into internal defect energy of the material through plastic deformation. A shape memory polymer matrix refers to an organic polymer material with a thermo-induced shape memory effect, which can be made of polyurethane-based shape memory polymer injection molding, and can recover a preset shape under specific temperature stimulation.

[0038] When an external impact load is applied to the honeycomb buffer structure, the hexagonal lattice absorbs the initial kinetic energy through progressive crushing, while simultaneously transferring stress evenly to the corrugated plate layer. Under compressive loads, the corrugated plate layer undergoes directional folding deformation, achieving secondary energy dissipation through the plastic yielding process of the metal sheet. The shape memory polymer matrix, acting as a support carrier, maintains structural stiffness at room temperature and drives the overall structure to restore its original shape upon thermal activation. The three layers of materials are bonded together through a hot-pressing composite process. The honeycomb structure performs the initial impact attenuation function, the corrugated plate layer serves as an energy conversion transition layer, and the shape memory matrix simultaneously achieves structural support and shape reconstruction.

[0039] Thus, a gradient energy dissipation mechanism is constructed by combining a honeycomb structure with a corrugated plate layer. The unique anisotropic deformation characteristics of the corrugated plate layer can guide the direction of shock wave propagation, avoiding interface delamination failure of the shape memory polymer matrix due to local stress concentration. This enables the coordinated operation of a multi-level energy management system. The honeycomb structure disperses and buffers the impact load, the corrugated plate layer achieves kinetic energy conversion through plastic deformation, and the shape memory matrix maintains the overall structural stability and provides programmable deformation capability. While ensuring energy absorption efficiency, this composite structure controls the overall mass within the satellite's load-bearing range through lightweight material combination. Under vibration and impact conditions, it can convert axial impact energy into radial deformation energy. The converted deformation energy is evenly distributed to the two curved folded plates 2 through the crease conduction mechanism.

[0040] Optionally, the thickness of both the energy-absorbing foldable base plate 1 and the curved foldable plate 2 in the planar state does not exceed 10 mm.

[0041] Specifically, the overall thickness of the energy-absorbing foldable base plate 1 and the corrugated foldable plate 2 is controlled within 10mm when no folding deformation occurs. For example, an ultra-thin honeycomb core material combined with nano-level reinforcing fibers can be used to achieve lightweighting while meeting impact resistance requirements. This allows the energy-absorbing foldable base plate 1 and the corrugated foldable plate 2 to maintain an ultra-thin shape in a planar state, enabling them to adhere tightly to the satellite surface during launch and effectively reducing the space occupied by the launch vehicle's payload. During in-orbit operation, this thickness control, combined with the phase change characteristics of shape memory materials, ensures sufficient rigidity support during folding deformation, while avoiding shape recovery lag caused by excessive material thickness. By designing a thickness gradient between the honeycomb buffer structure and the corrugated plate energy dissipation layer, the overall structural thickness is strictly controlled within a set range while achieving gradual dissipation of impact energy.

[0042] Thus, by setting the thickness of both the energy-absorbing foldable base plate 1 and the curved foldable plate 2 to no more than 10mm in the planar state, the thinning design of the energy-absorbing foldable base plate 1 and the curved foldable plate 2 is achieved. Under the same protection performance, the structural thickness is reduced. At the same time, through the folding collaborative deformation mechanism, the mechanism can still maintain structural integrity in the folded state. This solves the volume and weight limitations of the satellite protection and capture mechanism during the launch phase, allowing it to be integrated into the satellite surface in an ultra-thin form, significantly improving launch efficiency. During the on-orbit operation phase, it ensures that the energy-absorbing foldable base plate 1 and the curved foldable plate 2 maintain stable mechanical response characteristics during the folding and unfolding process, and avoids the risk of space environment adaptability caused by excessive structural thickness.

[0043] Optionally, when the space debris monitoring system detects a collision risk, the energy-absorbing foldable base plate 1 and the foldable plate 2 fold and deform within a first time, which ranges from 1 to 5 seconds.

[0044] Specifically, completing the folding deformation within the first time refers to the total time from the issuance of an early warning signal by the monitoring system to the completion of the form change by the protective structure, which ranges from 1 to 5 seconds. For example, when the space debris monitoring system detects a risk of overlap between the collision trajectory and the satellite, a trigger signal is transmitted to the drive units of the energy-absorbing foldable base plate 1 and the curved folding plate 2. The shape memory material undergoes a phase change under external stimulation, and the straight creases of the energy-absorbing foldable base plate 1 and the curved creases of the curved folding plate 2 fold synchronously along a preset path. Within a time range of 1 to 5 seconds, the outermost straight crease of the energy-absorbing foldable base plate 1 completes its downward bend, causing displacement of the connecting edge of the curved folding plate 2, resulting in the remaining portion of the curved folding plate 22 bending along the preset straight crease to form a capture configuration. This time window is achieved through a dynamic balance between the crease unfolding angle and the material restoring force, ensuring that the deformation is completed before the collision occurs while avoiding structural damage due to excessive bending of the creases.

[0045] Thus, when the space debris monitoring system detects a collision risk, it can shorten the response time to less than 5 seconds through the intrinsic deformation characteristics and crease synergy mechanism of shape memory materials, enabling rapid switching of the protective configuration within the critical time when space debris approaches the satellite.

[0046] Optionally, the shape memory intelligent protection capture mechanism also includes a network of temperature / strain sensors that monitor the deformation state in real time.

[0047] Specifically, a temperature / strain sensor network is used to monitor the temperature or strain of the energy-absorbing foldable base plate 1 and the crease-lined foldable plate 2 in real time. Temperature sensors can be thin-film thermocouples or fiber Bragg grating temperature sensors, providing thermodynamic parameter feedback for the shape recovery process by measuring the temperature gradient distribution in key crease areas. Strain sensors can be microelectromechanical system strain gauges or distributed fiber optic strain sensors, establishing a mapping relationship between deformation and driving parameters by capturing the local deformation in the crease area.

[0048] Sensor networks can use star or mesh topologies to acquire data, and spatial distribution optimization can ensure full coverage of curved areas, arched areas, and connecting boundaries.

[0049] For example, during folding or unfolding, temperature sensors collect real-time phase transition temperature field data of the shape memory material and determine whether the material response meets preset driving conditions based on the temperature change rate. Strain sensors simultaneously measure the deformation of the crease area and, combined with preset thresholds, identify local overload or abnormal deformation. The sensor network fuses the temperature and strain data and transmits it to a self-diagnostic system. By comparing the preset deformation curve with real-time monitoring data, the system dynamically adjusts the power output of the micro-heating element or triggers compensation actions for redundant creases. For instance, when the strain value of a straight crease exceeds the safe range, the system can immediately reduce the heating temperature of the corresponding area to slow down the deformation rate and prevent structural damage.

[0050] Thus, by using a network of temperature / strain sensors to monitor the deformation state in real time, multi-dimensional monitoring of temperature and strain is achieved, enabling closed-loop control of the deformation process. This allows the protective structure to adaptively adjust its driving strategy based on real-time feedback data, effectively preventing crease failure or structural fracture caused by monitoring gaps. Furthermore, it can accurately identify abnormal deformations caused by local overload, material fatigue, or external impacts, providing data support for the dynamic optimization of the control strategy and thereby improving the reliability and response accuracy of the protective structure under complex working conditions.

[0051] Optionally, the shape memory intelligent protection capture mechanism also includes a miniature heating element for precise local temperature control.

[0052] Specifically, the micro heating element can be understood as a miniaturized thermal excitation device embedded in the crease structure. It can be implemented using a thin-film resistance heating element with a thickness of less than 0.5 mm, generating a directional thermal field through current drive. This element is positioned within the crease region sandwiched between the straight crease 11 or the preset curved crease 22 of the shape memory polymer matrix, directly acting on the preset crease path to achieve rapid heating of the deformable area. Precise local temperature control refers to independent temperature control of specific crease regions. This can be achieved using a closed-loop feedback system of distributed temperature sensors and the micro heating element, dynamically adjusting the heating power by monitoring temperature changes in the crease region in real time. This control method applies thermal excitation only to the crease region requiring deformation, avoiding ineffective energy input to non-deformable areas.

[0053] For example, in the protection mode, the micro heating element directionally heats the area of ​​the outermost straight crease 11 in the first calibration direction of the energy-absorbing foldable base plate 1, causing the shape memory polymer matrix to reach the phase transition temperature within 5 seconds. The heating range is limited to the straight crease with a width of 3 mm, and the heating power distribution is optimized through a heat conduction model to ensure that the temperature gradient on both sides of the straight crease 11 does not exceed 10℃ / cm. Simultaneously, the micro heating element arranged at the midpoint of the preset curved crease 22 of the curved fold plate 2 is activated synchronously, causing the curved crease area to complete the phase transition response within 3 seconds. During the heating process, the temperature sensor network monitors the temperature of the crease area in real time. When the local temperature exceeds the preset threshold, the heating power is automatically reduced to prevent overheating damage to the material. In the capture mode, the micro heating element switches to the preset straight crease area for pulse heating, and the bending angle of the crease is precisely controlled by adjusting the duty cycle.

[0054] In this way, the micro heating element with precise local temperature control can act precisely on the fold structure, so that the energy-absorbing foldable base plate 1 and the folded plate 2 only undergo phase change response on the preset deformation path, avoiding heat input in unnecessary areas, meeting the emergency protection requirements of space debris collision warning, and the local temperature control design also avoids the interference of traditional overall heating on the satellite thermal environment.

[0055] Optionally, the shape memory intelligent protection capture mechanism also includes a self-diagnostic system for assessing the integrity of the protection structure and a wireless communication module for enabling data interaction with the satellite master control system.

[0056] Specifically, the self-diagnostic system can be understood as a monitoring device that collects multi-dimensional physical parameters through an embedded sensor network. This can be achieved by using a distributed fiber optic sensor and piezoelectric thin-film sensor array working in tandem, establishing a structural health assessment model through multi-source data fusion analysis. For example, during deformation, the self-diagnostic system continuously collects strain distribution, temperature gradient, and vibration spectrum data through sensor nodes distributed at key locations on the energy-absorbing foldable base plate 1 and the folded plate 2. This data is then combined with a pre-set structural damage feature library for pattern matching. When abnormal stress concentration or material delamination is detected in the folded area, a protective structural integrity assessment report is generated. The wireless communication module encapsulates the assessment results and operational status parameters into standardized data packets via the onboard communication protocol stack and periodically transmits them to the satellite main control system. Simultaneously, it receives folding mode switching commands from the main control system. This collaborative operation allows the health status of the protective structure to be quantified in real time, and enables closed-loop control of fault warning and command response through bidirectional data interaction.

[0057] In this way, by utilizing a self-diagnostic system for assessing the integrity of the protective structure and a wireless communication module for data interaction with the satellite master control system, online quantitative assessment of the damage level of the shape memory intelligent protection capture mechanism was achieved, thereby enabling autonomous diagnosis of the protective structure's full life cycle status and avoiding the lag of traditional manual inspection. A real-time data channel between the protective mechanism and the satellite master control system was established, enabling structural health status data to directly participate in the on-orbit maintenance decision-making process and improving the satellite system's autonomous operation capability.

[0058] Optionally, the outer surfaces of the energy-absorbing foldable base plate 1 and the crease folding plate 2 are coated with multiple layers of cushioning and radiation-proof coatings, and the crease areas are treated with wear-resistant reinforcement.

[0059] Specifically, the multilayer buffer and radiation-shielding coating can be understood as a composite protective layer composed of alternating layers of elastic polymer and metallized thin film. For example, it can be achieved through alternating deposition of polyurethane and aluminum foil. The elastic polymer layer absorbs impact kinetic energy, while the metallized thin film layer reflects high-energy particle radiation. The wear-resistant strengthening treatment can be understood as forming a silicon carbide-reinforced metal-based composite material layer on the surface of the crease area using laser cladding technology. Specifically, this can be achieved by selectively laser-sintering a mixture of titanium alloy powder and nano-silicon carbide particles, thereby improving surface wear resistance while maintaining the material's bending flexibility.

[0060] During protection, the multi-layered coating on the outer surface converts the shock wave energy generated by the impact of space debris into damped vibrations within the material through an elastic polymer layer, thereby reducing the risk of penetration. Meanwhile, the metallized thin film layer forms a continuous conductive network, guiding charged particles from cosmic rays to the edges of the structure for dissipation. The wear-resistant reinforcement layer in the crease area disperses stress concentration through high-hardness silicon carbide particles, suppressing the initiation of microcracks caused by repeated folding.

[0061] Thus, by coating the outer surfaces of the energy-absorbing foldable base plate 1 and the folded plate 2 with multiple layers of buffer and radiation-proof coatings, the composite coating achieves multi-functional integrated protection. The structural flexibility and durability requirements are balanced by local reinforcement treatment. By performing wear-resistant reinforcement treatment on the folded area, deformation failure caused by material fatigue in the folded area is avoided. The overall reliability of the protection system is improved while maintaining the lightweight design of the satellite.

[0062] Optionally, the shape memory intelligent protection and capture mechanism includes an automatic mode that autonomously deforms based on environmental sensor data, a remote control mode that triggers deformation by receiving commands from a ground station or satellite master control, and a backup mode that allows manual unfolding or folding via external operation in case of system failure.

[0063] Specifically, the automatic mode refers to a deformation mechanism that autonomously responds to changes in the space environment by collecting temperature and strain data in real time through environmental sensors. This can be achieved using a distributed network of temperature and strain sensors, with embedded algorithms processing sensor signals and generating deformation commands to address the limitations of traditional single-control modes in adapting to dynamic environments. The remote control mode refers to a control method that triggers deformation by receiving external commands through a communication link. This can be achieved by establishing a data exchange channel between the onboard wireless communication module and the ground station, allowing operators to remotely control the deformation process based on real-time monitoring data, enhancing operational accuracy under complex conditions. The backup mode is an emergency mechanism for manual operation via a mechanical interface in case of electronic system failure. This can be achieved using a mechanical transmission device independent of the electronic control system and an external operating handle, ensuring that form switching can still be completed in the event of sensor failure or communication interruption, reducing the risk of single-point failure.

[0064] In automatic mode, the environmental sensor network continuously collects data such as space radiation intensity and debris collision risk, triggering preset folding or unfolding programs to enable the mechanism to adaptively adjust to the dynamic environment. In remote control mode, the satellite main control system or ground station sends control commands through an encrypted communication protocol to drive the shape memory material to deform along a predetermined trajectory to meet specific mission requirements. In standby mode, astronauts manually operate the transmission device through an external mechanical interface, bypassing the electronic control system to directly drive the folded structure to complete the unfolding or folding action. The three modes achieve coordinated control through priority logic, with automatic mode executed first, switching to remote control mode when communication is normal, and activating standby mode in case of system failure.

[0065] Thus, through a collaborative mechanism of three modes—an automatic mode based on environmental sensor data for autonomous deformation, a remote-controlled mode that triggers deformation upon receiving commands from a ground station or satellite, and a backup mode for manual deployment / folding via external operation in case of system failure—this system retains autonomous response capabilities, expands the channels for manual intervention, and provides a mechanical emergency operation interface. This multi-layered control redundancy overcomes the problem of insufficient scenario adaptability caused by a single deformation mode, reduces the system's over-reliance on the electronic control unit, and improves operational reliability in fault conditions. Furthermore, in the event of a sudden space debris impact, the mechanism can autonomously switch to a protective mode; when capturing non-cooperative targets, the shell closure angle can be precisely adjusted via remote control; and even when the electronic system is damaged, basic functions can still be maintained through the backup mode.

[0066] Another embodiment of the present invention provides a satellite, including the protection and capture mechanism based on composite crease cooperative deformation as described above.

[0067] The satellite possesses all the beneficial effects of the protection and capture mechanism based on composite fold collaborative deformation, which will not be elaborated here.

[0068] While the present invention has been disclosed above, its scope of protection is not limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention, and all such changes and modifications will fall within the scope of protection of the present invention.

Claims

1. A protection and capture mechanism based on composite crease synergistic deformation, characterized in that, The system includes an energy-absorbing foldable base plate (1) and two curved foldable plates (2), both made of shape memory material. The energy-absorbing foldable base plate (1) is located between the two curved foldable plates (2) and is used for connection with a satellite. The energy-absorbing foldable base plate (1) includes multiple straight creases (11) arranged parallel to a first calibration direction of the energy-absorbing foldable base plate (1). The energy-absorbing foldable base plate (1) includes a side (12) located in a second calibration direction, the first calibration direction being perpendicular to the second calibration direction. The curved foldable plates (2) Includes a connecting edge (21) corresponding to the side edge (12), a preset curved crease (22) and a preset straight crease (23). The starting point and the ending point of the preset curved crease (22) are both located between the two ends of the connecting edge (21). The two ends of the side edge (12) in the first calibration direction are located at the starting point and the ending point, respectively, and are connected to the connecting edge (21). One end of the preset straight crease (23) starts at the midpoint of the preset curved crease (22), and the other end extends along the second calibration direction to the other end of the curved fold plate (2). In the protection mode, the energy-absorbing foldable base plate (1) is folded, and the two outermost straight creases (11) located in the first calibration direction are bent upward. The side (12) drives the curved fold plate (2) to fold along the preset curve crease (22), so that the part of the curved fold plate (2) surrounded by the preset curve crease (22) arches upward, and the remaining part bends upward while bending towards the other curved fold plate (2) with the preset straight crease (23) as the baseline, so that the two curved fold plates (2) surround the satellite. In capture mode, the energy-absorbing foldable base plate (1) is folded, and the two outermost straight creases (11) located in the first calibration direction bend downward. The side (12) drives the curved fold plate (2) to fold along the preset curve crease (22), so that the part of the curved fold plate (2) surrounded by the preset curve crease (22) arches downward, and the remaining part bends downward while bending towards the other curved fold plate (2) with the preset straight crease (23) as the baseline, so that the two curved fold plates (2) surround each other to capture non-cooperative targets.

2. The protection and capture mechanism based on composite crease synergistic deformation according to claim 1, characterized in that, In the unfolded state, each of the curved folded plates (2) is rectangular, and when two curved folded plates (2) are joined together, they form a cylindrical shape.

3. The protection and capture mechanism based on composite crease synergistic deformation according to claim 1, characterized in that, During the on-orbit operation phase, when the satellite is detected to have entered the predetermined orbital position or when a ground command is received, the energy-absorbing foldable base plate (1) and the curved foldable plate (2) are restored to a planar state through the shape memory effect, and the energy-absorbing foldable base plate (1) is attached to the surface of the satellite.

4. The protection and capture mechanism based on composite crease synergistic deformation according to claim 1, characterized in that, The energy-absorbing foldable base plate (1) includes an outer honeycomb buffer structure, a middle corrugated plate energy dissipation layer and an inner shape memory polymer matrix, wherein the corrugated plate energy dissipation layer is connected between the shape memory polymer matrix and the honeycomb buffer structure.

5. The protection and capture mechanism based on composite crease synergistic deformation according to claim 2, characterized in that, The thickness of both the energy-absorbing foldable base plate (1) and the crease foldable plate (2) in the planar state does not exceed 10 mm.

6. The protection and capture mechanism based on composite crease synergistic deformation according to claim 1, characterized in that, In the capture mode, the energy-absorbing foldable base plate (1) and the curved fold plate (2) complete the folding deformation in the first time, which ranges from 1 to 5 seconds.

7. The protection and capture mechanism based on composite crease synergistic deformation according to claim 1, characterized in that, The shape memory intelligent protection and capture mechanism also includes a network of temperature / strain sensors that monitor the deformation state in real time.

8. The protection and capture mechanism based on composite crease synergistic deformation according to claim 1, characterized in that, The shape memory intelligent protection and capture mechanism also includes a self-diagnostic system for assessing the integrity of the protection structure and a wireless communication module for enabling data interaction with the satellite master control system.

9. The protection and capture mechanism based on composite crease synergistic deformation according to claim 1, characterized in that, The outer surfaces of the energy-absorbing foldable base plate (1) and the crease folding plate (2) are coated with multiple layers of buffer and radiation-proof coatings, and the crease area is treated with wear-resistant reinforcement.

10. A satellite, characterized in that, Including the protection and capture mechanism based on composite crease synergistic deformation as described in any one of claims 1-9.

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