Spacecraft protection system and method of protection thereof

Abstract

The application provides a spacecraft protection system and a protection method, and belongs to the technical field of aerospace. The spacecraft protection system is applied to a spacecraft and comprises a space debris early warning device, a protection screen and a driving device. The protection screen is arranged on the outer cabin wall of the spacecraft. The space debris early warning device is electrically connected with the driving device. The driving device is drivingly connected with the protection screen. The protection screen is made of a shape memory polymer composite material. The structure of the protection screen is a paper folding structure, which comprises a folded state and an unfolded state. In the spacecraft launching process, the protection screen is in the folded state. After the spacecraft reaches an operating orbit, the protection screen is converted from the folded state to the unfolded state by applying external stimulation. The spacecraft protection system provided by the application can realize active defense according to the trajectory of the space debris, improve the active defense capability of the protection screen, thereby protecting the spacecraft in all directions and avoiding damage to the spacecraft.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular to a spacecraft protection device and a protection method thereof. BACKGROUND

[0002] With the increasing frequency of human space activities, the space debris such as satellite fragments and abandoned satellites in space is increasing. According to research data, there are about 330 million space debris with a diameter of more than 1mm in the Earth's orbit, which seriously threatens the safe on-orbit operation of manned spaceflight, space stations, large satellite platforms and micro-nano satellites. In the prior art, in order to reduce the harm of space debris, a Whipple protection screen is generally installed on large platforms such as space stations to protect precision instruments by two layers of metal plates, ceramic materials or fiber reinforced composite materials.

[0003] However, the protection screen in the prior art can only protect specific precision components, important protection parts or important extravehicular instruments, and it is difficult to achieve all-round protection of the satellite platform. In addition, the protection screen in the prior art is fixed on the outer cabin wall of the satellite platform, and can only achieve passive defense by being hit by space debris, and cannot achieve active defense according to the trajectory of space debris, thereby limiting the protection ability of the protection screen. SUMMARY

[0004] The problem solved by the present application is how to provide a spacecraft protection system capable of achieving active defense and improving protection ability.

[0005] To solve at least one aspect of the above problems, the present application provides a spacecraft protection system applied to a spacecraft, comprising a space debris early warning device, a protection screen and a driving device;

[0006] The space debris early warning device is used to predict the impact point of space debris, the protection screen is arranged on the outer cabin wall of the spacecraft, the space debris early warning device is electrically connected with the driving device, and the driving device is drivingly connected with the protection screen.

[0007] The protection screen is made of a shape memory polymer composite material, the structure of the protection screen is a paper folding structure, comprising a folded state and an unfolded state, the area of the protection screen in the folded state is smaller than that in the unfolded state, the protection screen is in the folded state during the launching process of the spacecraft, and the protection screen is converted from the folded state to the unfolded state by applying external stimulation when the spacecraft reaches the operating orbit.

[0008] Preferably, the protective screen comprises an upper panel surface, a lower panel surface, and a sandwich layer between the upper panel surface and the lower panel surface, the upper panel surface, the lower panel surface, and the sandwich layer are all made of the shape memory polymer composite material, and the sandwich layer comprises a lattice metamaterial sandwich layer.

[0009] Preferably, the protective screen is provided with a plurality of groups of preset creases at a central position and a periphery, the plurality of groups of preset creases at the periphery are centrally symmetrically distributed along the center of the protective screen, when the protective screen (3) is in the unfolded state, the areas formed by all the preset creases (34) are located in the same plane, and when the protective screen (3) is converted from the unfolded state to the folded state, the areas formed by the plurality of groups of preset creases (34) at the periphery are rotated and folded downward below the preset creases at the central position.

[0010] Preferably, the protective screen is connected to the outer cabin wall of the spacecraft through a steering mechanism, and the driving device is drivingly connected to the steering mechanism.

[0011] Preferably, the protective screen is connected to the steering mechanism through a plurality of connecting rods, each of the connecting rods comprises a first connecting rod, a second connecting rod, a third connecting rod, a first hinge, and a second hinge, the first connecting rod, the first hinge, the second connecting rod, the second hinge, and the third connecting rod are connected in sequence, and the first connecting rod is connected to the steering mechanism, and the third connecting rod is connected to the protective screen.

[0012] The first hinge and the second hinge are both made of the shape memory polymer composite material, when the protective screen is in the folded state, the first hinge and the second hinge are both in a bent state, or the first hinge is in a straightened state and the second hinge is in a bent state, and when the protective screen is in the unfolded state, the first hinge and the second hinge are both in a straightened state.

[0013] Preferably, a plurality of the third connecting rods are respectively connected to the areas formed by the plurality of groups of preset creases at the periphery of the protective screen.

[0014] Preferably, the lattice metamaterial sandwich layer comprises one or more of a BCC lattice metamaterial sandwich layer, an Octet lattice metamaterial sandwich layer, a three-dimensional hexagonal honeycomb lattice metamaterial sandwich layer, and a Kelvin lattice metamaterial sandwich layer.

[0015] The spacecraft protection system provided by the application comprises a space debris early warning device, a protection screen and a driving device, wherein the space debris early warning device can predict the impact point of space debris, the driving device can drive the protection screen to move to a suitable position according to the prediction result of the space debris early warning device, so as to avoid damage of the space debris to the spacecraft, and the active defense capability of the protection screen is significantly improved, and the spacecraft is protected in all directions. Since the protection screen is made of a shape memory polymer composite material, the protection screen has shape memory performance, including a folded state and an unfolded state. When the spacecraft is launched, the protection screen is in the folded state, and the area is smaller, so that the resistance in the launching process is reduced. When the spacecraft reaches the operating orbit, in order to improve the protection capability of the protection screen, the protection screen can be deformed under the stimulation of the outside world to convert into the unfolded state, and the origami structure of the protection screen ensures the smooth transformation of the protection screen between the folded state and the unfolded state. The spacecraft protection system provided by the application can realize active defense according to the trajectory of the space debris, improve the active defense capability of the protection screen, and ensure the operation of the protection screen in different states through the shape memory performance of the protection screen, so as to protect the spacecraft in all directions and avoid damage to the spacecraft.

[0016] The application further provides a spacecraft protection method for protecting by using the spacecraft protection system described above, comprising the following steps:

[0017] Step S1, installing the spacecraft protection system on the spacecraft, wherein the initial structure of the protection screen is the unfolded state;

[0018] Step S2, applying external stimulation to the protection screen to convert the protection screen into a temporary state of the folded structure by shaping;

[0019] Step S3, launching the spacecraft to the operating orbit, applying external stimulation to the protection screen to convert the protection screen from the folded state to the unfolded state;

[0020] Step S4, predicting the impact point of space debris on the spacecraft by using the space debris early warning device, and driving the protection screen to shield the area of the impact point by the driving device according to the prediction result, so as to avoid damage of the space debris to the spacecraft.

[0021] Preferably, the step S2 comprises:

[0022] Applying external stimulation to the protection screen to increase the temperature of the protection screen to above the glass transition temperature, then applying a load to convert the protection screen from the unfolded state to the folded state, reducing the temperature of the protection screen to below the glass transition temperature while maintaining the protection screen in the folded state, so that the structure of the protection screen forms the folded state.

[0023] Preferably, the form of the external stimulus comprises one or more of thermal drive, magnetic drive, solution drive, radio frequency drive, microwave drive and light drive.

[0024] The spacecraft protection method provided by the present application has the same advantages as the spacecraft protection system, which will not be repeated here. BRIEF DESCRIPTION OF DRAWINGS

[0025] Figure 1 The structural schematic diagram of the spacecraft protection system in the embodiment of the present application is shown in the figure;

[0026] Figure 2 The structural schematic diagram of the protection screen in the embodiment of the present application is shown in the figure;

[0027] Figure 3 The structural schematic diagram of the BCC lattice metamaterial unit cell and the BCC lattice metamaterial sandwich layer composed of the same in the embodiment of the present application is shown in the figure;

[0028] Figure 4 The structural schematic diagram of the Octet lattice metamaterial unit cell and the BCC lattice metamaterial sandwich layer composed of the same in the embodiment of the present application is shown in the figure;

[0029] Figure 5 The structural schematic diagram of the three-dimensional hexagonal honeycomb lattice metamaterial unit cell and the BCC lattice metamaterial sandwich layer composed of the same in the embodiment of the present application is shown in the figure;

[0030] Figure 6 The structural schematic diagram of the Kelvin lattice metamaterial unit cell and the BCC lattice metamaterial sandwich layer composed of the same in the embodiment of the present application is shown in the figure;

[0031] Figure 7 The structural schematic diagram of the protection screen in the embodiment of the present application is shown in the figure;

[0032] Figure 8 The structural schematic diagram of the protection screen in the embodiment of the present application is shown in the figure;

[0033] Figure 9 The structural schematic diagram of the overall structure of the protection screen and the steering mechanism in the embodiment of the present application is shown in the figure;

[0034] Figure 10 The structural schematic diagram of the universal joint in the embodiment of the present application is shown in the figure;

[0035] Figure 11 The structural schematic diagram of the connecting rod in the embodiment of the present application is shown in the figure

[0036] Figure 12 The structural schematic diagram of the overall structure of the protection screen and the steering mechanism in the embodiment of the present application is shown in the figure;

[0037] Figure 13 Fig. 9 is a structural schematic diagram of the overall structure of the protective screen and the steering mechanism in the first stage of expansion in an embodiment of the present application;

[0038] Figure 14 Fig. 10 is a structural schematic diagram of the overall structure of the protective screen and the steering mechanism in the second stage of expansion in an embodiment of the present application;

[0039] Figure 15 Fig. 11 is a flowchart of a spacecraft protection method in an embodiment of the present application;

[0040] Figure 16 Fig. 12 is a structural schematic diagram of a spacecraft in an embodiment of the present application when the protective screen is in the expanded state;

[0041] Figure 17 Fig. 13 is a structural schematic diagram of a spacecraft in an embodiment of the present application when the protective screen is in the folded state;

[0042] Figure 18 Fig. 14 is a process schematic diagram of a spacecraft protection system protecting space debris in an embodiment of the present application.

[0043] Explanation of Reference Signs:

[0044] 1, spacecraft; 2, space debris early warning device; 3, protective screen; 31, upper panel; 32, core layer; 33, core layer; 34, preset crease; 4, steering mechanism; 5, connecting rod; 51, first connecting rod; 52, second connecting rod; 53, third connecting rod; 54, first hinge; 55, second hinge; 6, space debris. DETAILED DESCRIPTION

[0045] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, the specific embodiments of the present application are described in detail below.

[0046] It should be noted that the features in the embodiments of the present application can be combined with each other without conflict. At the same time, it should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and do not necessarily describe a specific order or sequence. It should be understood that the data thus used can be interchanged under appropriate circumstances, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein.

[0047] An embodiment of the present application provides a spacecraft protection system applied to a spacecraft 1, as shown in Figure 1 which includes a space debris early warning device 2, a protective screen 3 and a driving device (not shown in the figure);

[0048] The space debris early warning device 2 is used for predicting the impact point of the space debris, the protective screen 3 is arranged on the outer cabin wall of the spacecraft 1, the space debris early warning device 2 is electrically connected with the driving device, and the driving device is drivingly connected with the protective screen 3.

[0049] The protective screen 3 is made of a shape memory polymer composite material, and has a foldable structure including a folded state and an unfolded state. The area of the protective screen 3 in the folded state is smaller than that in the unfolded state. During the launching of the spacecraft 1, the protective screen 3 is in the folded state. When the spacecraft 1 reaches an operating orbit, the protective screen 3 is converted from the folded state to the unfolded state by applying an external stimulus.

[0050] For example, the spacecraft 1 is a manned spacecraft, a satellite or a space station, in particular, a manned spacecraft, a large satellite platform, a micro-nano satellite or a space station.

[0051] The spacecraft protection system provided by the embodiment of the present application comprises a space debris early warning device 2, a protective screen 3 and a driving device. The space debris early warning device 2 can predict the impact point of the space debris. The driving device can drive the protective screen 3 to move to a suitable position according to the prediction result of the space debris early warning device 2, so as to avoid damage to the spacecraft 1 caused by the space debris, and significantly improve the active defense capability of the protective screen 3. The spacecraft 1 is protected in all directions. Since the protective screen 3 is made of a shape memory polymer composite material, it has shape memory performance, including a folded state and an unfolded state. When the spacecraft 1 is launched, the protective screen 3 is in the folded state, and the area is smaller, thereby reducing the resistance during launching. When the spacecraft 1 reaches an operating orbit, in order to improve the protection capability of the protective screen 3, the protective screen 3 can be deformed under the stimulation of the external environment, and be converted to the unfolded state. The foldable structure of the protective screen 3 ensures the smooth transformation of the protective screen 3 between the folded state and the unfolded state. The spacecraft protection system provided by the embodiment of the present application can realize active defense according to the trajectory of the space debris, improve the active defense capability of the protective screen 3, and ensure the operation of the protective screen 3 in different states through the shape memory performance of the protective screen 3, so as to protect the spacecraft 1 in all directions and avoid damage to the spacecraft 1.

[0052] In one embodiment, as shown in Figure 2 The protective screen 3 comprises an upper plate surface 31, a lower plate surface 33 and a core layer 32 between the upper plate surface 31 and the lower plate surface 33. The upper plate surface 31, the lower plate surface 33 and the core layer 32 are all made of the shape memory polymer composite material. The core layer 32 comprises a dot matrix metamaterial core layer.

[0053] The lattice metamaterial sandwich layer has energy absorption characteristics. When the protective screen 3 is impacted by a space debris, the lattice metamaterial sandwich layer absorbs the energy of the space debris through collapse, plastic deformation and the like, so as to prevent the space debris from damaging the spacecraft 1.

[0054] Exemplarily, the lattice metamaterial sandwich layer comprises one or more of a BCC lattice metamaterial sandwich layer, an Octet lattice metamaterial sandwich layer, a three-dimensional hexagonal honeycomb lattice metamaterial sandwich layer and a Kelvin lattice metamaterial sandwich layer.

[0055] In addition, the lattice metamaterial sandwich layer can also be a double-arrow honeycomb lattice metamaterial sandwich layer, a star-shaped honeycomb lattice metamaterial sandwich layer, a three-toughness chiral honeycomb lattice metamaterial sandwich layer or a six-toughness chiral honeycomb lattice metamaterial sandwich layer.

[0056] The lattice metamaterial sandwich layer is formed by arraying lattice metamaterial cells in different directions. By adjusting the parameters such as the rod diameter, the rod angle, the panel thickness and the arrangement mode of the lattice metamaterial cells, the equivalent mechanical properties and the energy absorption characteristics of the mechanical metamaterial can be adjusted.

[0057] Figures 3-6 respectively are structure schematic diagrams of the BCC lattice metamaterial sandwich layer, the Octet lattice metamaterial sandwich layer, the three-dimensional hexagonal honeycomb lattice metamaterial sandwich layer and the Kelvin lattice metamaterial sandwich layer, Figure 3 in (A), Figure 4 in (A), Figure 5 in (A) and Figure 6 respectively are structure schematic diagrams of the BCC lattice metamaterial cell, the Octet lattice metamaterial cell, the three-dimensional hexagonal honeycomb lattice metamaterial cell and the Kelvin lattice metamaterial cell; Figure 3 in (B), Figure 4 in (B), Figure 5 in (B) and Figure 6 respectively are structure schematic diagrams of the BCC lattice metamaterial sandwich layer cell, the Octet lattice metamaterial sandwich layer cell, the three-dimensional hexagonal honeycomb lattice metamaterial sandwich layer cell and the Kelvin lattice metamaterial sandwich layer cell; Figure 3 in (C) is a structure schematic diagram of the BCC lattice metamaterial sandwich layer, Figure 3 in (D) is a front view of the BCC lattice metamaterial sandwich layer; Figure 4 in (C) is a structure schematic diagram of the Octet lattice metamaterial sandwich layer, Figure 4 in (D) is a front view of the Octet lattice metamaterial sandwich layer;

[0058] Figure 5 in (C) is a structure schematic diagram of the three-dimensional hexagonal honeycomb lattice metamaterial sandwich layer,Figure 5 Fig. D is a front view of a three-dimensional hexagonal honeycomb lattice metamaterial core layer, Figure 6 Fig. C is a schematic view of a Kelvin lattice metamaterial core layer, Figure 6 Fig. D is a front view of a Kelvin lattice metamaterial core layer.

[0059] In one embodiment, the shape memory polymer composite comprises a matrix and a reinforcing phase, wherein the matrix comprises one or more of an epoxy-based shape memory polymer, a cyanate ester-based shape memory polymer, a polyimide-based shape memory polymer, and a styrene-based shape memory polymer, and the reinforcing phase comprises one or more of carbon nanotubes, carbon fibers, Kevlar fibers, and aramid fibers.

[0060] The matrix is a shape memory polymer, which ensures that the protective screen has shape memory performance, and the addition of the reinforcing phase can improve the mechanical properties of the protective screen.

[0061] It should be noted that the reinforcing phase comprises carbon nanotubes, carbon fibers, Kevlar fibers, and aramid fibers, which can be in the form of particles, chopped fibers, continuous fibers, or fiber cloth, and can be selected according to different performance requirements.

[0062] In one embodiment, the protective screen 3 is provided with a plurality of groups of preset creases 34 at the center position and the periphery, the plurality of groups of preset creases 34 at the periphery are centrally symmetrically distributed along the center of the protective screen 3, when the protective screen 3 is in the unfolded state, the areas formed by all the preset creases 34 are located in the same plane, and when the protective screen 3 is converted from the unfolded state to the folded state, the areas formed by the plurality of groups of preset creases 34 at the periphery are rotated and folded downward below the preset creases at the center position.

[0063] The crease positions of the preset creases 34 are thinner than other areas, and when the state of the protective screen 3 is converted, folding from the preset creases 34 makes it easier to realize the conversion between different states.

[0064] Figure 7 Fig. A is a schematic view of the protective screen 3, Figure 7 Fig. B is a front view of the protective screen 3, as Figure 7As shown, the protective screen 3 is square, wherein four groups of preset creases 34 located at the periphery are respectively located at the four corners of the square, and are centrally symmetrically distributed, and one group of diamond-shaped preset creases 34 is located at the center position of the square protective screen 3. When the protective screen 3 is in the unfolded state, the areas formed by all the preset creases 34 are located in the same plane, and the protective screen 3 is square. When the protective screen 3 is converted from the unfolded state to the folded state, the four groups of preset creases 34 located at the four corners are folded along the preset crease 34 at the center position, so that the areas formed by the four groups of preset creases 34 located at the four corners are located below the area formed by the preset crease 34 at the center position. Among them, the structures before and after folding are as shown in Figure 8 As shown, Figure 8 The photos of the protective screen 3 of the embodiment of the present application in the unfolded structure and the folded structure are as shown in Figure 8 (A) is the unfolded structure, Figure 8 (B) is the folded structure.

[0065] After the protective screen 3 is converted from the unfolded state to the folded state, the areas formed by different preset creases 34 are stacked with each other, thereby reducing the area of the protective screen 3, that is, the area of the protective screen 3 in the folded state is smaller than the area of the protective screen 3 in the unfolded state, and the resistance can be reduced during launching.

[0066] It should be understood that the protective screen 3 can also be circular or triangular or other shapes.

[0067] In one embodiment, as shown in Figure 9 The protective screen 3 is connected with the outer cabin wall of the spacecraft 1 through the turning mechanism 4, and the driving device is drivingly connected with the turning mechanism 4. The turning mechanism 4 is driven by the driving device to change the direction of the protective screen 3, block the space debris coming from different directions, and realize active defense.

[0068] Exemplarily, the turning mechanism 4 is a universal joint, and the protective screen 3 is connected with the spacecraft 1 through the universal joint, and can change the direction with the position of the universal joint as the center, thereby realizing larger range protection. Among them, Figure 10 is a structural schematic view of the universal joint.

[0069] In one embodiment, the shield 3 is connected with the steering mechanism 4 through a plurality of connecting rods 5, each of the connecting rods 5 comprises a first connecting rod 51, a second connecting rod 52, a third connecting rod 53, a first hinge 54 and a second hinge 55, the first connecting rod 51, the first hinge 54, the second connecting rod 52, the second hinge 55 and the third connecting rod 53 are connected in sequence, and the first connecting rod 51 is connected with the steering mechanism 4, and the third connecting rod 53 is connected with the shield 3; the first hinge 54 and the second hinge 55 are made of the shape memory polymer composite material, and when the shield 3 is in the folded state, the first hinge 54 and the second hinge 55 are in the bent state, or the first hinge 54 is in the straightened state and the second hinge 55 is in the bent state, and when the shield 3 is in the unfolded state, the first hinge 54 and the second hinge 55 are in the straightened state.

[0070] As shown in Figure 9 and Figure 11 , the shield 3 and the universal joint are connected through a plurality of connecting rods 5, each of the connecting rods 5 is divided into a plurality of components, i.e., a first connecting rod 51, a second connecting rod 52, a third connecting rod 53, a first hinge 54 and a second hinge 55, the first connecting rod 51, the first hinge 54, the second connecting rod 52, the second hinge 55 and the third connecting rod 53 are connected in sequence, and the first hinge 54 and the second hinge 55 are made of the shape memory polymer composite material and have the shape memory performance, when the shield 3 is in the folded state, the first hinge 54 and the second hinge 55 are in the bent state, or the first hinge 54 is in the straightened state and the second hinge 55 is in the bent state, when the first hinge 54 and the second hinge 55 are in the bent state, the shield 3 is close to the spacecraft 1, so that the shield 3 is attached to the outer cabin wall of the spacecraft 1, thereby reducing the resistance during the launch of the spacecraft 1, when the first hinge 54 is in the straightened state and the second hinge 55 is in the bent state, the shield 3 is extended outward, and when the position of the shield 3 is changed through the steering mechanism 4, the position of the shield 3 changes more greatly, and the shield 3 has a larger protection area.

[0071] When the first hinge 54 and the second hinge 55 are in the straightened state and the shield 3 is in the unfolded state, the shield 3 is extended outward while being unfolded, forming a two-stage unfolded configuration, and having a larger protection area.

[0072] That is, the embodiment of the present application realizes the change between the folding configuration (the first hinge 54 and the second hinge 55 are both in the bent state, and the protective screen 3 is in the folding state), the first-stage unfolding configuration (the first hinge 54 is in the straightened state, the second hinge 55 is in the bent state, and the protective screen 3 is in the folding state), and the second-stage unfolding configuration (the first hinge 54 and the second hinge 55 are both in the straightened state, and the protective screen 3 is in the unfolded state) through the cooperation of the deformation of the first hinge 54, the second hinge 55, and the protective screen 3. When in the folding configuration, the protective screen 3 is folded and close to the spacecraft 1, reducing the resistance in the launching process. When in the first-stage unfolding configuration, the protective screen 3 extends outward but is not unfolded. When in the second-stage unfolding configuration, the protective screen 3 extends outward while being unfolded, and can be turned under the driving of the universal joint to protect different areas of the spacecraft 1.

[0073] In one embodiment, the plurality of third connecting rods 53 are respectively connected with the areas formed by the plurality of groups of preset creases 34 located at the periphery of the protective screen 3. When the protective screen 3 is in the folding state, the third connecting rods 53 are located below the protective screen 3.

[0074] Since the areas formed by the plurality of groups of preset creases 34 located at the periphery are rotated and folded below the areas formed by the preset creases 34 located at the center position when the protective screen 3 is converted from the unfolded state to the folding state, the connection position of the third connecting rod 53 and the protective screen 3 is arranged in the areas formed by the plurality of groups of preset creases 34 located at the periphery, which can ensure that the overall structure of the protective screen 3 and the turning mechanism 4 is more easily realized in the configuration conversion.

[0075] Figures 12-14 Structure schematic diagrams of the overall structure of the protective screen 3 and the turning mechanism 4 in the folding configuration, the first-stage unfolding configuration, and the second-stage unfolding configuration, respectively.

[0076] Among them, Figure 12 Structure schematic diagram of the overall structure of the protective screen 3 and the turning mechanism 4 in the folding configuration, Figure 12 (A), (B), (C), and (D) are different views of the above structure, at this time, the first hinge 54 and the second hinge 55 are both in the bent state, the protective screen 3 is in the folding state, and the protective screen 3 is close to the turning mechanism 4; Figure 13 Structure schematic diagram of the overall structure of the protective screen 3 and the turning mechanism 4 in the first-stage unfolding configuration, Figure 13 (A), (B), (C), and (D) are different views of the above structure, at this time, the first hinge 54 is in the straightened state, the second hinge 55 is in the bent state, the protective screen 3 is in the folding state, and the protective screen 3 is away from the turning mechanism 4; Figure 14 Structure schematic diagram of the overall structure of the protective screen 3 and the turning mechanism 4 in the second-stage unfolding configuration, Figure 14Fig. 1 shows the different views of the above structure, in which the first hinge 54 and the second hinge 55 are both in the straightened state, the protective screen 3 is in the unfolded state, and the protective screen 3 is away from the steering mechanism 4.

[0077] Another embodiment of the present application provides a spacecraft protection method for protection by using the spacecraft protection system as described above, which comprises the following steps as shown in Fig. 2. Figure 15

[0078] Step S1, installing the spacecraft protection system to the spacecraft 1, in which the initial structure of the protective screen 3 is in the unfolded state.

[0079] Step S2, applying external stimulation to the protective screen 3 to convert the protective screen 3 into the temporary structure in the folded state.

[0080] Step S3, launching the spacecraft 1 to the operating orbit, applying external stimulation to the protective screen 3 to convert the protective screen 3 from the folded state to the unfolded state.

[0081] Step S4, predicting the impact point of the space debris 6 and the spacecraft 1 by using the space debris early warning device 2, and driving the protective screen 3 to shield the impact point according to the prediction result by using the driving device to avoid damage to the spacecraft 1 caused by the space debris 6.

[0082] The spacecraft protection method provided by the embodiment of the present application has the same beneficial effects as the spacecraft protection system of the prior art, which will not be described here.

[0083] In step S1, the initial structure of the protective screen 3 is in the unfolded state (as shown in Fig. 1), and after being shaped into the temporary structure in the folded state (as shown in Fig. 2), the temporary structure in the folded state can be converted into the unfolded state of the initial structure by applying external stimulation, and no external force needs to be applied in this process. Figure 16 Figure 17 In step S2, the specific steps include:

[0084] In step S2, the specific steps include:

[0085] Applying external stimulation to the protective screen 3 to increase the temperature of the protective screen 3 to above the glass transition temperature, then applying a load to convert the protective screen 3 into the folded state, maintaining the protective screen 3 in the folded state, and reducing the temperature of the protective screen 3 to below the glass transition temperature to form the structure of the protective screen 3 in the folded state.

[0086] In the shaping process and the state conversion process, the form of the external stimulation includes one or more of thermal driving, magnetic driving, solution driving, radio frequency driving, microwave driving, and light driving. ​​

[0087] Specifically, if a thermal driving mode is adopted, it can be achieved by surface pasting a resistance heater or by a heating mode of an external heat source; if an electric driving mode is adopted, single-walled carbon nanotubes, multi-walled carbon nanotubes, graphene, carbon black, carbon nanometer paper, carbon nanometer fiber, chopped carbon fiber, continuous carbon fiber or hybrid particles can be doped in the shape memory polymer composite material to increase the conductive reinforcing phase, and an electric circuit is formed by connecting the structure doped with the conductive reinforcing phase with an external power supply; if a microwave driving mode is adopted, carbon nanotubes, graphene oxide or silicon carbide nanoparticles can be doped in the shape memory polymer composite material; if a radio frequency driving mode is adopted, radio frequency sensitive materials such as carbon nanotubes and the like can be doped in the shape memory polymer composite material; if a light driving mode is adopted, light sensitive materials can be doped in the shape memory polymer composite material. A combined driving mode can also be adopted, that is, driving by two or more driving modes, which can be achieved by doping two or more reinforcing phases in the shape memory polymer composite material.

[0088] Correspondingly, when the thermal driving mode is adopted, the protective screen 3, the first hinge 54 and the second hinge 55 are heated, the temperature rises above the glass transition temperature, and the conversion from the folded state to the unfolded state is achieved; and when the electric driving, microwave driving, radio frequency driving and light driving modes are adopted, the protective screen 3, the first hinge 54 and the second hinge 55 are respectively powered on, microwave field is applied, radio frequency field is applied and light field is applied, and the conversion from the folded state to the unfolded state is achieved.

[0089] In step S4, the space debris early warning device 2 predicts the impact point of the space debris 6 on the spacecraft 1, and according to the prediction result, the driving device drives the protective screen 3 to shield the impact point, so as to avoid damage to the spacecraft 1 caused by the space debris 6. That is, the spacecraft protection system in the embodiment of the application can realize active defense and improve the protection range.

[0090] As shown in Figure 18 When the space debris early warning device 2 predicts that the impact point of the space debris 6 on the spacecraft 1 is at the lower left corner of the spacecraft 1, the driving device drives the protective screen 3 to move to the lower left corner, and shields the area, thereby realizing the active defense capability.

[0091] Although the present application is disclosed as above, the protection scope of the present application is not limited to this. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present application, and these changes and modifications will fall within the protection scope of the present application.

Claims

1. A spacecraft protection system, applied to a spacecraft (1), characterized in that, The device comprises a space debris warning device (2), a protective screen (3) and a driving device; The space debris warning device (2) is used for predicting the impact point of space debris, the protective screen (3) is arranged on the outer cabin wall of the spacecraft (1), the space debris warning device (2) is electrically connected with the driving device, and the driving device is drivingly connected with the protective screen (3). The protective screen (3) is made of a shape memory polymer composite material, has a foldable structure, and comprises a folded state and an unfolded state; the area of the protective screen (3) in the folded state is smaller than that in the unfolded state; during the launching process of the spacecraft (1), the protective screen (3) is in the folded state; when the spacecraft (1) reaches an operating orbit, the protective screen (3) is converted from the folded state to the unfolded state by applying external stimulation. A plurality of groups of preset creases (34) are arranged at the center position and the periphery of the protective screen (3), and the plurality of groups of preset creases (34) at the periphery are centrally symmetrically distributed along the center of the protective screen (3). The protective screen (3) is connected with the outer cabin wall of the spacecraft (1) through a steering mechanism (4), the driving device is drivingly connected with the steering mechanism (4), the protective screen (3) is connected with the steering mechanism (4) through a plurality of connecting rods (5), each connecting rod (5) comprises a first connecting rod (51), a second connecting rod (52), a third connecting rod (53), a first hinge (54) and a second hinge (55), the first connecting rod (51), the first hinge (54), the second connecting rod (52), the second hinge (55) and the third connecting rod (53) are sequentially connected, the first connecting rod (51) is connected with the steering mechanism (4), and a plurality of third connecting rods (53) are respectively connected with the areas formed by the plurality of groups of preset creases (34) at the periphery of the protective screen (3).

2. The spacecraft shielding system of claim 1, wherein, The protective screen (3) comprises an upper plate surface (31), a lower plate surface (33) and a core layer (32) between the upper plate surface (31) and the lower plate surface (33), the upper plate surface (31), the lower plate surface (33) and the core layer (32) are made of the shape memory polymer composite material, and the core layer (32) comprises a dot matrix metamaterial core layer.

3. The spacecraft shielding system of claim 1, wherein, When the protective screen (3) is in the unfolded state, all the areas formed by the preset creases (34) are located in the same plane, and when the protective screen (3) is converted from the unfolded state to the folded state, the areas formed by the plurality of groups of preset creases (34) at the periphery are rotated and folded below the preset creases at the center position.

4. The spacecraft shielding system of claim 3, wherein, The protective screen (3) is connected with the steering mechanism (4) through a plurality of connecting rods (5), each of the connecting rods (5) comprises a first connecting rod (51), a second connecting rod (52), a third connecting rod (53), a first hinge (54) and a second hinge (55), the first connecting rod (51), the first hinge (54), the second connecting rod (52), the second hinge (55) and the third connecting rod (53) are sequentially connected, and the first connecting rod (51) is connected with the steering mechanism (4), and the third connecting rod (53) is connected with the protective screen (3); The first hinge (54) and the second hinge (55) are made of the shape memory polymer composite material, when the protective screen (3) is in the folded state, the first hinge (54) and the second hinge (55) are in a bent state, or the first hinge (54) is in a straight state and the second hinge (55) is in a bent state, when the protective screen (3) is in the unfolded state, the first hinge (54) and the second hinge (55) are in a straight state.

5. The spacecraft shielding system of claim 2, wherein, The lattice metamaterial core layer comprises one or more of a BCC lattice metamaterial core layer, an Octet lattice metamaterial core layer, a three-dimensional hexagonal honeycomb lattice metamaterial core layer and a Kelvin lattice metamaterial core layer.

6. A method for shielding a spacecraft with a spacecraft shielding system according to any one of claims 1 to 5, characterized in that The method comprises the following steps: Step S1, installing a spacecraft protection system to a spacecraft (1), wherein the initial structure of the protective screen (3) is an unfolded state; Step S2, applying an external stimulus to the protective screen (3) to convert the protective screen (3) into a temporary structure in a folded state through shaping; Step S3, launching the spacecraft (1) to an operating orbit, applying an external stimulus to the protective screen (3) to convert the protective screen (3) from the folded state to the unfolded state; Step S4, predicting the impact point of a space debris (6) on the spacecraft (1) by using a space debris early warning device (2), and driving the protective screen (3) to shield the area of the impact point through a driving device according to the prediction result, so as to avoid damage to the spacecraft (1) caused by the space debris (6).

7. The method of shielding a spacecraft of claim 6, wherein, The step S2 comprises: Applying an external stimulus to the protective screen (3) to raise the temperature of the protective screen (3) above the glass transition temperature, then applying a load to convert the protective screen (3) from the unfolded state to the folded state, reducing the temperature of the protective screen (3) below the glass transition temperature while maintaining the protective screen (3) in the folded state, so that the structure of the protective screen (3) forms the folded state.

8. The method of shielding a spacecraft of claim 6, wherein, The form of the external stimulus comprises one or more of thermal driving, magnetic driving, solution driving, radio frequency driving, microwave driving and light driving.

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