Space station debris shield based on pyrotechnic compression seat

Abstract

The present application relates to the technical field of space station debris protection, and particularly relates to a space station debris protection device based on a pyrotechnic compact seat, which comprises a protection assembly, a first connecting assembly and a second connecting assembly; the protection assembly is used for shielding a space station cabin body, blocking space debris from directly impacting the cabin body and bearing the impact of space station debris. When the debris protection device is installed on the uplink area of a mechanical arm in orbit, first, a universal handle is connected with the first connecting assembly, and an astronaut drives the protection assembly to the uplink area of the mechanical arm by means of the universal handle, so as to prevent the protection assembly from drifting randomly. Then, the second connecting assembly is connected with the pyrotechnic compact seat by using the discarded pyrotechnic compact seat as the installation point of the protection assembly, so as to complete the installation task of the debris protection device and further improve the overall debris protection capability of the space station and prolong the on-orbit life of the space station.

Description

Technical Field

[0001] This invention relates to the field of space station debris protection technology, and in particular to a space station debris protection device based on a pyrotechnic clamping seat. Background Technology

[0002] During the space station's operational phase, some modules lack debris protection structures on their surfaces, such as the upper region of the robotic arm. To further enhance the space station's debris protection capabilities, it is necessary to install debris protection devices in orbit on the upper region of the robotic arm. Currently, no interface for installing debris protection devices has been reserved in the upper region of the robotic arm before launch, and this area is already covered by multiple layers, with no handrails or other fixed interfaces nearby. Therefore, how to install debris protection devices in orbit on the upper region of the robotic arm has become a technical problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0003] This invention provides a space station debris protection device based on a pyrotechnic clamping seat, which solves the problem of how to install a debris protection device on orbit in the upward region of a robotic arm.

[0004] This invention provides a space station debris protection device based on a pyrotechnic clamping seat, comprising:

[0005] Protective components designed to withstand impacts from debris from the space station;

[0006] The first connection component, mounted on the protective component, is suitable for connecting or disconnecting from a universal handle;

[0007] The second connection component, mounted on the protective component, is suitable for connecting or disconnecting from the pyrotechnic clamping seat.

[0008] In some embodiments, the second connection component includes:

[0009] The locking disc has a connector formed on its bottom surface; the connector is suitable for insertion into or removal from the socket on the pyrotechnic pressure seat; the interior of the connector forms a receiving cavity, and three first clearance holes are formed on the side wall along the circumferential direction, which are respectively connected to the receiving cavity.

[0010] There are three locking beads, all installed inside the receiving cavity;

[0011] The drive shaft, with its bottom end inserted into the receiving cavity, can move downwards so that one side of each of the three locking balls protrudes out of the receiving cavity through the corresponding first clearance hole, or move upwards so that the three locking balls retract into the receiving cavity.

[0012] In some embodiments, the second connection component further includes:

[0013] The housing is installed outside the drive shaft;

[0014] The damper, installed inside the housing, is used to limit the spontaneous rotation of the drive shaft and to limit the spontaneous axial movement of the drive shaft.

[0015] In some embodiments, vertical guide grooves are formed on the inner walls of opposite sides of the housing;

[0016] The damper includes:

[0017] The lower limit plate has guide blocks on both sides that are adapted to the vertical guide groove, and a ring of limit teeth on the top surface;

[0018] The upper limit plate is fitted onto the upper part of the drive shaft, and a ring of limit teeth is also provided on the bottom surface;

[0019] The top spring is sleeved on the upper part of the drive shaft, with its bottom end fixedly connected to the top end of the locking disc, and its top end abutting against the bottom surface of the lower limit disc.

[0020] In some embodiments, the second connection component further includes:

[0021] The operating wheel is mounted on the top of the drive shaft.

[0022] In some embodiments, it also includes:

[0023] The adapter is mounted on the protective component at one end and on the second connecting component at the other end.

[0024] In some embodiments, the protective component has a second clearance hole; the second clearance hole is directly opposite the second connecting component and allows the pyrotechnic clamping seat to pass through.

[0025] In some embodiments, the protective component includes:

[0026] First buffer layer;

[0027] The second buffer layer is disposed above the top surface of the first buffer layer, and a buffer cavity is reserved between the bottom surface and the top surface of the first buffer layer.

[0028] The third connection component is used to connect the second buffer layer and the first buffer layer.

[0029] In some embodiments, the first buffer layer includes:

[0030] There are four inner flame-retardant fabrics; each inner flame-retardant fabric is covered with ten layers of aramid fabric stacked in sequence to form a buffer body; the four buffer bodies are stacked in sequence.

[0031] The outer flame-retardant fabric is wrapped around the four buffer bodies.

[0032] In some embodiments, the protective component further includes:

[0033] The thermal insulation component is wrapped around the first buffer layer, the second buffer layer and the third connecting component.

[0034] The beneficial effects of this invention are as follows: The space station debris protection device based on a pyrotechnic clamping seat of this invention, by setting up a protective component, is used to shield the space station hull, preventing space debris from directly impacting the hull and withstanding the impact of space station debris. When installing the debris protection device in orbit to the upper region of the robotic arm, firstly, the universal handle is connected to the first connecting component. Astronauts use the universal handle to move the protective component and the second connecting component to the upper region of the robotic arm to prevent the protective component and the second connecting component from drifting randomly. Then, a discarded pyrotechnic clamping seat is used as the installation point for the protective component, and the second connecting component is connected to the pyrotechnic clamping seat to complete the debris protection device installation task, further improving the overall debris protection capability of the space station and extending its on-orbit lifespan. Attached Figure Description

[0035] Figure 1 This is a schematic diagram of some specific embodiments of a space station debris protection device based on a pyrotechnic clamping seat according to the present invention;

[0036] Figure 2 yes Figure 1 The diagram shown is a structural schematic of the second connecting component in the space station debris protection device based on the pyrotechnic clamping seat when it is installed in the pyrotechnic clamping seat.

[0037] Figure 3 This is an enlarged structural diagram of the second connecting component;

[0038] Figure 4 yes Figure 1 The diagram shows a partial structural schematic of the protective components in a space station debris protection device based on a pyrotechnic clamping seat.

[0039] In the attached diagram, 110 is a protective component; 111 is a second clearance hole; 112 is a third clearance hole; 113 is a first buffer layer; 114 is a second buffer layer; 115 is a third connecting component; 1151 is a screw; 1152 is a sleeve; 1153 is a washer; 1154 is a nut; 120 is a first connecting component; 130 is a second connecting component; 131 is a locking disc; 1311 is a connector; 132 is a locking ball; 133 is a drive shaft; 134 is a housing; 135 is a damper; 1351 is an upper limit plate; 1352 is a lower limit plate; 1353 is a clamping spring; 136 is an operating wheel; 140 is an adapter; and 200 is a pyrotechnic clamping seat. Detailed Implementation

[0040] The technical solution of the present invention will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0041] As described in the background section, currently, no interface for installing a debris protection device is reserved at the upper position of the robotic arm before launch, and the surface of this area is already covered by multiple layers, with no handrails or other fixed interfaces around it. Therefore, how to install a debris protection device on track in the upper area of ​​the robotic arm has become a technical problem that urgently needs to be solved by those skilled in the art.

[0042] It should be noted that during launch, the pyrotechnic ballast is connected to the robotic arm to restrict its movement. After orbit insertion, the pyrotechnic ballast explodes, disconnecting from the robotic arm and allowing it to move and perform its tasks. The exploded pyrotechnic ballast remains outside the launch site as waste.

[0043] To solve the above problems, refer to Figure 1 , Figure 2 , Figure 3 and Figure 4 This invention provides a space station debris protection device based on a pyrotechnic clamping seat, comprising a protective component 110, a first connecting component 120, and a second connecting component 130. The protective component 110 is used to shield the space station hull, preventing space debris from directly impacting the hull and absorbing the impact of the debris. The first connecting component 120 is mounted on the protective component 110 and is suitable for connecting or disconnecting with a universal handle. The second connecting component 130 is mounted on the protective component 110 and is suitable for connecting or disconnecting with a pyrotechnic clamping seat 200.

[0044] When installing debris protection devices in orbit to the upper region of the robotic arm, firstly, the universal handle is connected to the first connecting assembly 120. Astronauts then use the universal handle to move the protective assembly 110 and the second connecting assembly 130 to the upper region of the robotic arm to prevent them from drifting. Next, a discarded pyrotechnic clamping seat 200 is used as the installation point for the protective assembly 110, and the second connecting assembly 130 is connected to the pyrotechnic clamping seat 200 to complete the debris protection device installation. This further improves the overall debris protection capability of the space station and extends its on-orbit lifespan.

[0045] Specifically, in the example, such as Figure 1 , Figure 2 and Figure 3As shown, the second connecting assembly 130 includes a locking disc 131, three locking balls 132, a drive shaft 133, a housing 134, a damper 135, and an operating wheel 136. A connector 1311 is formed on the bottom surface of the locking disc 131. The connector 1311 is suitable for insertion into or disengagement from a socket on the pyrotechnic pressure seat 200. A receiving cavity is formed inside the connector 1311, and three first clearance holes, each communicating with the receiving cavity, are formed circumferentially on the side wall of the connector 1311. All three locking balls 132 are installed within the receiving cavity. The bottom end of the drive shaft 133 is inserted into the receiving cavity and can move downwards to allow one side of each of the three locking balls 132 to protrude out of the receiving cavity through the corresponding first clearance hole, or move upwards to allow the three locking balls 132 to retract into the receiving cavity. It should be noted that the outer diameter of the first clearance hole is smaller than the inner diameter to prevent the locking ball 132 from completely disengaging from the receiving cavity. The inner wall of the receiving cavity is threaded, and the outer wall of the drive shaft 133 is also threaded. The outer wall of the drive shaft 133 is connected to the inner wall of the receiving cavity by a screw connection. A groove is provided at the bottom end of the drive shaft 133 to temporarily accommodate the locking ball 132. When the drive shaft 133 rotates, the bottom end of the drive shaft 133 moves downwards or upwards, forcing one side of each of the three locking balls 132 to protrude out of the receiving cavity or retract into the receiving cavity through the corresponding first clearance hole. The housing 134 covers the outside of the drive shaft 133, protecting the internal components and preventing external interference with their movement. The damper 135 is installed inside the housing 134 to limit the spontaneous rotation of the drive shaft 133 and to limit its spontaneous axial movement to prevent misoperation. The operating wheel 136 is mounted on the top of the drive shaft 133 to facilitate the astronaut's hand operation of the drive shaft 133.

[0046] The connection process and principle between the second connecting assembly 130 and the pyrotechnic pressure seat 200 are as follows: First, the plug 1311 of the locking disc 131 is inserted into the insertion hole at the top of the pyrotechnic pressure seat 200, and the bottom end of the locking disc 131 presses against the top end of the pyrotechnic pressure seat 200 to initially connect the second connecting assembly 130 and the pyrotechnic pressure seat 200. Next, the operating wheel 136 is rotated, driving the drive shaft 133 to rotate. The bottom end of the drive shaft 133 moves downward. During this process, the groove on the outer wall of the drive shaft 133 forces one side of the locking ball 132 to pass through the first clearance hole and protrude outside the receiving cavity, and makes the locking ball 132 press against the inner wall of the insertion hole of the pyrotechnic pressure seat 200, further improving the stability of the connection between the second connecting assembly 130 and the pyrotechnic pressure seat 200.

[0047] Preferably, the locking disc 131 has a disc structure, which effectively increases the contact area between the locking disc 131 and the pyrotechnic pressure seat 200, thereby improving the connection stability.

[0048] Preferably, the locking disc 131 has multiple weight-reducing holes to reduce its weight and provide some shock absorption. Additionally, the weight-reducing holes allow astronauts to easily observe whether the connector 1311 of the locking disc 131 is aligned with the insertion hole of the pyrotechnic pressure seat 200, improving the installation efficiency of the protective assembly 110.

[0049] Preferably, a plurality of first clearance holes are formed circumferentially on the side wall of the connector 1311. One side of the locking bead 132 can pass through any one of the clearance holes, thereby effectively improving the locking efficiency.

[0050] Preferably, the top end of the drive shaft 133 is connected to the middle part of the operating wheel 136 by screws to facilitate the disassembly and assembly of the operating wheel 136.

[0051] Preferably, the side wall of the operating wheel 136 is provided with a plurality of limiting grooves along the circumference to increase the friction between the human finger and the operating wheel 136 and improve the operating effect.

[0052] Preferably, a vertical guide groove is formed on the inner wall of each of the opposite sides of the housing 134. The damper 135 includes a lower limiting plate 1352, an upper limiting plate 1351, and a clamping spring 1353. A guide block adapted to the vertical guide groove is provided on each of the opposite sides of the lower limiting plate 1352. The guide blocks on both sides can slide up and down along the vertical guide groove on the corresponding side. It should be noted that the lower limiting plate 1352 can only move up and down, and cannot rotate around its own axis. A ring of limiting teeth is provided on the top surface of the lower limiting plate 1352. The upper limiting plate 1351 is sleeved on the upper part of the transmission shaft 133, and a ring of limiting teeth is also provided on its bottom surface. When the upper limit plate 1351 rotates with the drive shaft 133, the lower limit plate 1352 cannot rotate. The limiting teeth of both the lower and upper limit plates provide damping force to prevent the drive shaft 133 from rotating spontaneously. The tension spring 1353 is sleeved on the upper part of the drive shaft 133, its bottom end fixedly connected to the top end of the locking plate 131, and its top end abutting against the bottom surface of the lower limit plate 1352, ensuring a tight fit between the top surface of the lower limit plate 1352 and the top surface of the upper limit plate 1351. The top surface of the upper limit plate 1351 abuts against the top of the housing 134, thus restricting the spontaneous axial movement of the drive shaft 133. As the upper limit plate 1351 moves downwards with the drive shaft 133, the shaft length of the tension spring 1353 gradually shortens, and the tensioning force gradually increases.

[0053] Specifically, in the example, such as Figure 1As shown, the space station debris protection device based on the pyrotechnic clamping seat also includes an adapter 140. One end of the adapter 140 is respectively installed on the top surface of the protection component 110, and the other end is respectively installed on the locking plate 131 of the second connecting component 130, so that the second connecting component 130 is connected to the protection component 110.

[0054] Preferably, there are four adapters 140, with one end installed on the top surface of the protective component 110 and the other end installed on the four sides of the locking plate 131, so as to improve the stability of the connection between the second connecting component 130 and the protective component 110.

[0055] Preferably, each adapter 140 has a "Z" shaped structure, which has a certain shock absorption and buffering effect.

[0056] Preferably, each adapter 140 is provided with a weight-reducing hole to reduce the weight of the adapter 140.

[0057] Preferably, one end of each adapter 140 is detachably connected to the top surface of the protective assembly 110 by a screw, and the other end is detachably connected to the locking disc 131 by a screw, thus facilitating the assembly and disassembly of the second connecting assembly 130.

[0058] Specifically, in the example, such as Figure 1 As shown, a second clearance hole 111 is provided on the protective component 110. The second clearance hole 111 is directly opposite the second connecting component 130 and allows the pyrotechnic clamping seat 200 to pass through.

[0059] Preferably, at least one third clearance hole 112 is provided on the protective component 110, allowing other structures outside the cabin to pass through. In this way, the movement of the protective component 110 can be restricted by at least two points, improving the stability of the protective component 110's position and ensuring the protective effect.

[0060] Preferably, the second clearance hole 111 is formed at one end of the protective component 110. The first connecting component 120 is detachably mounted in the middle of the top surface of the protective component 110, and the second connecting component 130 is detachably mounted at one end of the top surface of the protective component 110 via the adapter 140.

[0061] Preferably, the first connecting assembly 120 includes a connecting seat and limiting protrusions. Multiple limiting protrusions are mounted on the side wall of the connecting seat along its circumference.

[0062] Specifically, in the example, such as Figure 1 and Figure 4As shown, the protective assembly 110 includes a first buffer layer 113, a second buffer layer 114, and a third connecting assembly 115. The second buffer layer 114 is disposed above the top surface of the first buffer layer 113, and a buffer cavity is reserved between its bottom surface and the top surface of the first buffer layer 113. When impacted by debris from the space station, the first buffer layer 113, the second buffer layer 114, and the buffer cavity work together to provide a good buffering effect. The third connecting assembly 115 is used to connect the second buffer layer 114 and the first buffer layer 113.

[0063] Preferably, the first buffer layer 113 comprises four inner flame-retardant fabrics and an outer flame-retardant fabric. Each inner flame-retardant fabric is covered with ten layers of sequentially stacked aramid fabric to form a buffer body. The four buffer bodies are stacked sequentially. The outer flame-retardant fabric covers the four buffer bodies. The aramid fabric has good cushioning properties. The flame-retardant fabric is used for flame retardancy. The flame-retardant fabric is sewn to the aramid fabric using flame-retardant thread to maintain the stability of the structure of the first buffer layer 113.

[0064] Preferably, the second buffer layer 114 is an aluminum plate, which has a good buffering effect. When subjected to impact from debris from the space station, the second buffer layer 114 plays an initial buffering role, and the second buffer layer 114 plays a secondary buffering role.

[0065] Preferably, the second buffer layer 114 and the first buffer layer 113 are connected by a plurality of third connecting components 115 to improve the stability of the connection between the second buffer layer 114 and the first buffer layer 113. Each third connecting component 115 includes a screw 1151, a sleeve 1152, a washer 1153, and a nut 1154. The sleeve 1152 is fitted over the screw 1151, with its top end abutting against the bottom surface of the second buffer layer 114 and its bottom surface abutting against the top surface of the washer 1153. The washer 1153 is fitted over the screw 1151, with its bottom surface abutting against the top surface of the first buffer layer 113. The spacing between the bottom surface of the second buffer layer 114 and the top surface of the first buffer layer 113 is adjusted using the sleeve 1152 and the washer 1153, thereby adjusting the fragment protection effect.

[0066] Preferably, the space station debris protection device based on the pyrotechnic clamping seat further includes a heat insulation component, which covers the first buffer layer 113, the second buffer layer 114, and the third connecting component 115 to provide heat insulation, thereby facilitating the control of the on-orbit temperature of the protection component 110 and maintaining the temperature stability of the protection component 110. It also provides a sealing function for the protection component 110. The heat insulation layer can be connected to the first buffer layer 113 via Velcro.

[0067] It should be noted that the overall shape of the protective component 110 is designed to conform to the surface of the space station module at the installation location, and openings are made at the corresponding locations to avoid protruding equipment and supports on the module surface. The shape of the adapter 140 can be set according to the on-orbit installation direction and angle, and the distance between the bottom surface of the first buffer layer 113 and the surface of the module is controlled to be about 100mm.

[0068] Overall, during installation, in orbit, simply insert the connector 1311 into the socket on the pyrotechnic clamping seat 200 and then rotate the operating wheel 136; installation is very convenient. The second connecting component 130 has an anti-loosening function; the drive shaft 133 will not loosen unless subjected to continuous torsional force, eliminating the risk of it coming off in orbit. Since the socket size of the pyrotechnic clamping seat 200 is unknown in orbit, the rotational tightening method is suitable for sockets of various sizes, exhibiting high adaptability. Utilizing a discarded pyrotechnic clamping seat 200 as an installation interface solves the problem of no pre-reserved interfaces on the module, saving other interface resources on the space station. The overall structure is simple and easy to process and assemble.

[0069] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0070] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0071] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0072] In this invention, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0073] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A space station debris protection device based on a pyrotechnic clamping seat, characterized in that, include: Protective components designed to withstand impacts from debris from the space station; A first connecting component, mounted on the protective component, is adapted to connect or disconnect with a universal handle; The second connecting component is installed on the protective component and is suitable for connecting or disconnecting from the pyrotechnic pressure seat. The second connection component includes: The locking disc has a connector formed on its bottom surface; The connector is suitable for insertion into or removal from the socket on the pyrotechnic clamping seat; the interior of the connector forms a receiving cavity, and three first clearance holes are formed circumferentially on the side wall, which are respectively connected to the receiving cavity; There are three locking beads, all of which are installed inside the receiving cavity; The drive shaft, with its bottom end inserted into the receiving cavity, can move downward so that one side of each of the three locking beads protrudes out of the receiving cavity through the corresponding first clearance hole, or move upward so that the three locking beads retract into the receiving cavity.

2. The space station debris protection device based on a pyrotechnic clamping seat according to claim 1, characterized in that, The second connection component also includes: A housing, covering the outside of the drive shaft; A damper, installed within the housing, is used to limit the spontaneous rotation of the drive shaft and to limit the spontaneous axial movement of the drive shaft.

3. The space station debris protection device based on a pyrotechnic clamping seat according to claim 2, characterized in that, Vertical guide grooves are formed on the inner walls of opposite sides of the housing; The damper includes: The lower limit plate has guide blocks on both sides that are adapted to the vertical guide groove, and a ring of limiting teeth on the top surface; An upper limit plate is sleeved on the upper part of the drive shaft, and a ring of the limit teeth is also provided on the bottom surface; A tensioning spring is sleeved on the upper part of the drive shaft, with its bottom end fixedly connected to the top end of the locking disc, and its top end abutting against the bottom surface of the lower limit disc.

4. The space station debris protection device based on a pyrotechnic clamping seat according to claim 1, characterized in that, The second connection component also includes: An operating wheel is mounted on the top of the drive shaft.

5. The space station debris protection device based on a pyrotechnic clamping seat according to any one of claims 1 to 4, characterized in that, Also includes: The adapter is mounted on the protective component at one end and on the second connecting component at the other end.

6. The space station debris protection device based on a pyrotechnic clamping seat according to any one of claims 1 to 4, characterized in that, The protective component has a second clearance hole; the second clearance hole is directly opposite the second connecting component and allows the pyrotechnic clamping seat to pass through.

7. The space station debris protection device based on a pyrotechnic clamping seat according to any one of claims 1 to 4, characterized in that, The protective components include: First buffer layer; The second buffer layer is disposed above the top surface of the first buffer layer, and a buffer cavity is reserved between the bottom surface and the top surface of the first buffer layer. A third connection component is used to connect the second buffer layer and the first buffer layer.

8. The space station debris protection device based on a pyrotechnic clamping seat according to claim 7, characterized in that, The first buffer layer includes: There are four inner flame-retardant fabrics; each inner flame-retardant fabric is covered with ten layers of aramid fabric stacked in sequence to form a cushioning body; the four cushioning bodies are stacked in sequence. An outer flame-retardant fabric is used to cover the four aforementioned buffer bodies.

9. The space station debris protection device based on a pyrotechnic clamping seat according to claim 7, characterized in that, Also includes: A heat insulation component is wrapped around the first buffer layer, the second buffer layer, and the third connecting component.

Images