Space station fragment protection device based on initiating explosive device pressing seat

Abstract

The invention relates to the technical field of space station fragment protection, in particular to a space station fragment protection device based on an initiating explosive device pressing seat, which comprises a protection assembly, a first connecting assembly and a second connecting assembly, the protection assembly is used for covering a space station cabin, preventing space debris from directly impacting the cabin and bearing the impact of the space station debris. When the fragment protection device is additionally arranged on the ascending area of the mechanical arm in an on-orbit mode, firstly, the universal handle is connected with the first connecting assembly, and an astronaut drives the protection assembly to move to the ascending area of the mechanical arm through the universal handle so as to prevent the protection assembly from drifting at will. And then, a waste initiating explosive device pressing seat is used as an installation point position of the protection assembly, so that the second connection assembly is connected with the initiating explosive device pressing seat, the fragment protection device installation task is completed, the overall fragment protection capacity of the space station is further improved, and the on-orbit service life of the space station is prolonged.

Description

Technical Field

[0001] The present invention relates to the technical field of space station debris protection, and in particular to a space station debris protection device based on a pyrotechnic product compression seat. Background Art

[0002] During the on-orbit operation phase of the space station, some surfaces of the cabin do not have debris protection structures, such as the upward area of ​​the robotic arm. In order to further improve the debris protection capability of the space station, it is necessary to install a debris protection device in orbit in the upward area of ​​the robotic arm. Currently, before launch, no interface for installing a debris protection device is reserved in the upward position of the robotic arm, and the surface of this area has been covered with multiple layers, with no handrails or other fixed interfaces around it. Therefore, how to install a debris protection device in orbit in the upward area of ​​the robotic arm has become a technical problem that technicians in this field need to solve urgently. Summary of the invention

[0003] The present invention provides a space station debris protection device based on an pyrotechnic product pressing seat, which is used to solve the problem of how to install the debris protection device in the upward region of a mechanical arm on track.

[0004] The present invention provides a space station debris protection device based on an pyrotechnic product compression seat, comprising:

[0005] Protection components, used to withstand the impact of space station debris;

[0006] A first connection assembly, mounted on the guard assembly, adapted to connect or disconnect with the universal handle;

[0007] The second connecting component is installed on the protection component and is suitable for connecting or disconnecting with the pyrotechnic product compression seat.

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

[0009] The locking disk has a plug connector formed on the bottom surface; the plug connector is suitable for being inserted into or detached from the plug connector on the pyrotechnic pressing seat; a receiving cavity is formed inside the plug connector, and three first clearance holes are formed on the side wall along the circumferential direction and are respectively connected to the receiving cavity;

[0010] There are three locking beads, all installed in the accommodating cavity;

[0011] The transmission shaft has its bottom end inserted in the accommodating cavity and can move downward so that one side of the three locking beads respectively passes through the corresponding first clearance holes and protrudes out of the accommodating cavity, or move upward so that the three locking beads retract into the accommodating cavity.

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

[0013] A housing, which is arranged outside the transmission shaft;

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

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

[0016] The damper includes:

[0017] The lower limit plate has guide blocks matched with the vertical guide grooves on two opposite sides, and a circle of limit teeth on the top surface;

[0018] The upper limit plate is sleeved on the upper part of the transmission shaft, and a circle of limit teeth is also arranged on the bottom surface;

[0019] The tightening spring is sleeved on the upper part of the transmission shaft, the bottom end of which is fixedly connected to the top end of the locking disk, and the top end of which abuts against the bottom surface of the lower limit disk.

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

[0021] The operating wheel is installed on the top of the transmission shaft.

[0022] In some embodiments, it also includes:

[0023] The adapter has one end mounted on the protection component and the other end mounted on the second connection component.

[0024] In some of the embodiments, a second clearance hole is provided on the protective component; the second clearance hole is opposite to the second connecting component and can allow the pyrotechnic product compression seat to pass through.

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

[0026] A 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 connecting 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 cloths; each inner flame-retardant cloth is coated with ten layers of aramid cloth stacked in sequence to form a buffer body; four buffer bodies are stacked in sequence;

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

[0032] In some embodiments, the protection component further comprises:

[0033] The heat insulation component is coated on the first buffer layer, the second buffer layer and the third connection component.

[0034] The beneficial effects of the present invention are as follows: The space station debris protection device based on the pyrotechnic compression seat of the present invention is provided with a protection component, and the protection component is used to cover the space station cabin, block space debris from directly hitting the cabin, and withstand the impact of space station debris. When installing the debris protection device in orbit to the upward area of ​​the robotic arm, first, connect the universal handle with the first connecting component, and the astronaut uses the universal handle to drive the protection component and the second connecting component to move to the upward area of ​​the robotic arm to prevent the protection component and the second connecting component from drifting at will. Then, use the discarded pyrotechnic compression seat as the installation point of the protection component, and connect the second connecting component to the pyrotechnic compression seat to complete the task of installing the debris protection device, further improving the overall debris protection capability of the space station and extending its on-orbit life. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 It is a structural schematic diagram of some specific embodiments of a space station debris protection device based on an pyrotechnic compression seat of the present invention;

[0036] Figure 2 yes Figure 1 A schematic structural diagram of a space station debris protection device based on an pyrotechnic compression seat when the second connecting assembly is installed on the pyrotechnic compression seat;

[0037] Figure 3 is a schematic diagram of an enlarged structure of a second connection component;

[0038] Figure 4 yes Figure 1 A schematic diagram of the partial structure of the protection components in the space station debris protection device based on the pyrotechnic compression seat is shown.

[0039] In the accompanying drawings, 110, protective component; 111, second clearance hole; 112, third clearance hole; 113, first buffer layer; 114, second buffer layer; 115, third connecting component; 1151, screw; 1152, sleeve; 1153, washer; 1154, nut; 120, first connecting component; 130, second connecting component; 131, locking disk; 1311, plug connector; 132, locking bead; 133, transmission shaft; 134, housing; 135, damper; 1351, upper limit disk; 1352, lower limit disk; 1353, tensioning spring; 136, operating wheel; 140, adapter; 200, pyrotechnic pressure seat. DETAILED DESCRIPTION

[0040] The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0041] As described in the background technology, currently, before launch, there is no interface reserved for installing a debris protection device in the upward position of the robotic arm, and the surface of this area has been covered with multiple layers, with no handrails or other fixed interfaces around it. Therefore, how to install a debris protection device in orbit in the upward area of ​​the robotic arm has become a technical problem that needs to be urgently solved by technical personnel in this field.

[0042] It should be noted that during launch, the pyrotechnic hold-down seat is connected to the robotic arm to limit the movement of the robotic arm. After entering orbit, the pyrotechnic hold-down seat explodes and disconnects from the robotic arm, allowing the robotic arm to move and perform tasks. The pyrotechnic hold-down seat after the explosion is left outside the cabin as waste.

[0043] To solve the above problems, refer to Figure 1 , Figure 2 , Figure 3 and Figure 4 The present invention provides a space station debris protection device based on a pyrotechnic compression seat, comprising a protection component 110, a first connection component 120, and a second connection component 130. The protection component 110 is used to cover the space station cabin, prevent space debris from directly hitting the cabin, and withstand the impact of space station debris. The first connection component 120 is installed on the protection component 110, and is suitable for connecting or disconnecting with a universal handle. The second connection component 130 is installed on the protection component 110, and is suitable for connecting or disconnecting with the pyrotechnic compression seat 200.

[0044] When installing the debris protection device on-orbit to the upward region of the robotic arm, first, the universal handle is connected to the first connecting assembly 120, and the astronaut uses the universal handle to drive the protection assembly 110 and the second connecting assembly 130 to move to the upward region of the robotic arm to prevent the protection assembly 110 and the second connecting assembly 130 from drifting at will. Then, the abandoned pyrotechnic pressing seat 200 is used as the installation point of the protection assembly 110, and the second connecting assembly 130 is connected to the pyrotechnic pressing seat 200 to complete the task of installing the debris protection device, further improving the overall debris protection capability of the space station and extending its on-orbit life.

[0045] Specifically, in the example, Figure 1 , Figure 2 and Figure 3As shown, the second connecting assembly 130 includes a locking disk 131, three locking beads 132, a transmission shaft 133, a housing 134, a damper 135 and an operating wheel 136. A plug connector 1311 is formed on the bottom surface of the locking disk 131. The plug connector 1311 is suitable for being inserted into or detached from the socket on the pyrotechnic compression seat 200. A receiving cavity is formed inside the plug connector 1311, and three first clearance holes respectively connected to the receiving cavity are formed circumferentially on the side wall of the plug connector 1311. The three locking beads 132 are all installed in the receiving cavity. The bottom end of the transmission shaft 133 is inserted into the receiving cavity, and can move downward so that one side of the three locking beads 132 respectively passes through the corresponding first clearance holes and protrudes out of the receiving cavity, or moves upward so that the three locking beads 132 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 bead 132 from completely escaping from the accommodating chamber. The inner wall of the accommodating chamber is provided with a thread, and the outer wall of the transmission shaft 133 is also provided with a thread, and the outer wall of the transmission shaft 133 is connected to the inner wall of the accommodating chamber by a screw connection. A circle of grooves is provided at the bottom end of the transmission shaft 133 for temporarily accommodating the locking bead 132. When the transmission shaft 133 rotates, the bottom end of the transmission shaft 133 moves downward or upward to force one side of the three locking beads 132 to pass through the corresponding first clearance hole to protrude out of the accommodating chamber or retract into the accommodating chamber. The housing 134 is provided on the outside of the transmission shaft 133 to protect the internal components and prevent the external interference with the movement of the internal components. The damper 135 is installed in the housing 134 to limit the spontaneous rotation of the transmission shaft 133 and to limit the spontaneous axial movement of the transmission shaft 133 to prevent misoperation. The operating wheel 136 is installed at the top of the transmission shaft 133 to facilitate the astronaut to operate the transmission shaft 133 by hand.

[0046] The connection process and principle of the second connection assembly 130 and the pyrotechnic pressing seat 200 are as follows: First, insert the plug connector 1311 of the locking disk 131 into the socket at the top of the pyrotechnic pressing seat 200, and the bottom end of the locking disk 131 presses against the top of the pyrotechnic pressing seat 200 to preliminarily connect the second connection assembly 130 and the pyrotechnic pressing seat 200. Next, rotate the operating wheel 136 to drive the transmission shaft 133 to rotate, and the bottom end of the transmission shaft 133 moves downward. During this process, the groove on the outer wall of the transmission shaft 133 forces one side of the locking bead 132 to pass through the first clearance hole and protrude out of the accommodating cavity, and the locking bead 132 presses against the inner wall of the socket of the pyrotechnic pressing seat 200, further improving the stability of the connection between the second connection assembly 130 and the pyrotechnic pressing seat 200.

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

[0048] Preferably, a plurality of weight-reducing holes are provided on the locking disk 131 to reduce the weight of the locking disk 131 and provide a certain shock-absorbing function. In addition, it is convenient for astronauts to observe through the weight-reducing holes whether the plug connector 1311 of the locking disk 131 is aligned with the plug hole of the pyrotechnic pressing seat 200, thereby improving the installation efficiency of the protective assembly 110.

[0049] Preferably, a plurality of first clearance holes are formed along the circumferential direction on the side wall of the plug connector 1311. One side of the locking bead 132 can pass through any of the clearance holes, thus effectively improving the locking efficiency.

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

[0051] Preferably, a plurality of limiting grooves are provided on the side wall of the operating wheel 136 along the circumferential direction to increase the friction between human fingers and the operating wheel 136 and improve the operating effect.

[0052] Preferably, a vertical guide groove is formed on the inner walls on opposite sides of the shell 134. The damper 135 includes a lower limit plate 1352, an upper limit plate 1351 and a tightening spring 1353. A guide block adapted to the vertical guide groove is provided on opposite sides of the lower limit plate 1352. The guide blocks on both sides can slide up and down along the vertical guide grooves on the corresponding sides. It should be pointed out that the lower limit plate 1352 can only move up and down, but cannot rotate around its own axis. A circle of limit teeth is provided on the top surface of the lower limit plate 1352. The upper limit plate 1351 is sleeved on the upper part of the transmission shaft 133, and a circle of limit teeth is also provided on the bottom surface. When the upper limit plate 1351 rotates with the transmission shaft 133, since the lower limit plate 1352 cannot rotate, the limit teeth of the lower limit plate 1352 and the limit teeth of the upper limit plate 1351 are used to provide a damping force for the rotation of the transmission shaft 133 to prevent the transmission shaft 133 from rotating spontaneously. The tightening spring 1353 is sleeved on the upper part of the transmission shaft 133, and the bottom end is fixedly connected to the top of the locking plate 131, and the top end abuts against the bottom surface of the lower limit plate 1352, so that the top surface of the lower limit plate 1352 is closely fitted with the top surface of the upper limit plate 1351, and the top surface of the upper limit plate 1351 abuts against the top of the housing 134, thereby limiting the transmission shaft 133 from spontaneously moving in the axial direction. When the upper limit plate 1351 moves downward with the transmission shaft 133, the axial length of the tightening spring 1353 is gradually shortened, and the tightening force is gradually increased.

[0053] Specifically, in the example, Figure 1As shown, the space station debris protection device based on the pyrotechnic compression 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 disk 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 , one end of which is respectively mounted on the top surface of the protective assembly 110 , and the other end of which is respectively mounted on four sides of the locking disk 131 , so as to improve the stability of the connection between the second connecting assembly 130 and the protective assembly 110 .

[0055] Preferably, each adapter 140 is in a “Z”-shaped structure and has a certain shock-absorbing 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 component 110 via a screw, and the other end is detachably connected to the locking disk 131 via a screw, so that the disassembly and assembly of the second connecting component 130 is facilitated.

[0058] Specifically, in the example, Figure 1 As shown, a second clearance hole 111 is provided on the protection component 110. The second clearance hole 111 is directly opposite to the second connection component 130, and can be used for the pyrotechnic product compression seat 200 to pass through.

[0059] Preferably, at least one third clearance hole 112 is provided on the protection component 110, and the third clearance hole 112 is used for other structures outside the cabin to pass through. In this way, the movement of the protection component 110 can be restricted by at least two points, which improves the stability of the position of the protection component 110 and ensures the protection effect.

[0060] Preferably, the second clearance hole 111 is opened at one end of the protection component 110. The first connection component 120 is detachably mounted on the middle of the top surface of the protection component 110, and the second connection component 130 is detachably mounted on one end of the top surface of the protection component 110 through the adapter 140.

[0061] Preferably, the first connection assembly 120 includes a connection seat and a limiting protrusion. There are multiple limiting protrusions, which are installed on the side wall of the connection seat along the circumference of the connection seat.

[0062] Specifically, in the example, Figure 1 and Figure 4As shown, the protective component 110 includes a first buffer layer 113, a second buffer layer 114 and a third connecting component 115. The second buffer layer 114 is arranged above the top surface of the first buffer layer 113, and a buffer cavity is reserved between the bottom surface and the top surface of the first buffer layer 113. When hit by debris from the space station, the first buffer layer 113, the second buffer layer 114 and the buffer cavity cooperate to play a good buffering role. The third connecting component 115 is used to connect the second buffer layer 114 and the first buffer layer 113.

[0063] Preferably, the first buffer layer 113 includes four inner flame-retardant cloths and an outer flame-retardant cloth. Each inner flame-retardant cloth is coated with ten layers of aramid cloth stacked in sequence to form a buffer body. Four buffer bodies are stacked in sequence. The outer flame-retardant cloth is coated outside the four buffer bodies. The aramid cloth has a good buffering effect. The flame-retardant cloth is used for flame retardancy. The flame-retardant cloth and the aramid cloth are sewn together 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 the space station is hit by debris, the second buffer layer 114 plays a primary 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 connection components 115 to improve the stability of the connection between the second buffer layer 114 and the first buffer layer 113. Each third connection component 115 includes a screw 1151, a sleeve 1152, a washer 1153 and a nut 1154. The sleeve 1152 is sleeved outside the screw 1151, with the top end abutting against the bottom surface of the second buffer layer 114, and the bottom surface abutting against the top surface of the washer 1153. The washer 1153 is sleeved outside the screw 1151, with the bottom surface abutting against the top surface of the first buffer layer 113. The sleeve 1152 and the washer 1153 are used to adjust the distance between the bottom surface of the second buffer layer 114 and the top surface of the first buffer layer 113, thereby adjusting the debris protection effect.

[0066] Preferably, the space station debris protection device based on the pyrotechnics compression seat also includes a heat insulation component, which is coated on the first buffer layer 113, the second buffer layer 114 and the third connection component 115 to play a heat insulation role, thereby facilitating the control of the on-orbit temperature of the protection component 110 and maintaining the temperature stability of the protection component 110. At the same time, it plays a sealing role for the protection component 110. The heat insulation layer can be connected to the first buffer layer 113 by Velcro.

[0067] It should be noted that the overall shape of the protective assembly 110 is designed according to the surface of the space station cabin at the installation location, and holes are opened at corresponding locations to avoid protruding equipment and brackets on the cabin 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 cabin is controlled to be about 100 mm.

[0068] On the whole, during installation, you only need to insert the plug connector 1311 into the socket on the pyrotechnic clamping seat 200 on track, and then rotate the operating wheel 136, which makes the installation very convenient. The second connecting assembly 130 has an anti-loosening function. Without being subjected to continuous torsional external force, the transmission shaft 133 will not loosen, and there is no risk of it coming off on track. Since the size of the socket of the pyrotechnic clamping seat 200 is unknown in the on-track state, the method of rotational expansion is used, which is suitable for sockets of various sizes and has high adaptability. Using the discarded pyrotechnic clamping seat 200 as the installation interface solves the problem of no reserved interface on the cabin, saving other interface resources of the space station. The overall structure is simple and convenient for processing and assembly.

[0069] In the description of the present invention, it is to be understood that the terms “center”, “longitudinal”, “lateral”, “length”, “width”, “thickness”, “up”, “down”, “front”, “back”, “left”, “right”, “vertical”, “horizontal”, “top”, “bottom”, “inside”, “outside”, “clockwise”, “counterclockwise”, “axial”, “radial”, “circumferential”, etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0070] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0071] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0072] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the described specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0073] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. A space station debris protection device based on an pyrotechnic compression seat, characterized in that: include: Protection components, used to withstand the impact of space station debris; a first connection assembly, mounted on the protection assembly, adapted to connect or disconnect with the universal handle; The second connecting component is installed on the protective component and is suitable for connecting or disconnecting with the pyrotechnic product compression seat.

2. The space station debris protection device based on the pyrotechnic pressing seat according to claim 1 is characterized in that: The second connection component comprises: The locking disk has a plug connector formed on the bottom surface; the plug connector is suitable for being inserted into or detached from the plug hole on the pyrotechnic pressing seat; a receiving cavity is formed inside the plug connector, and three first clearance holes respectively connected to the receiving cavity are formed on the side wall along the circumferential direction; There are three locking beads, all installed in the accommodating cavity; The transmission shaft, whose bottom end is inserted into the accommodating cavity, can move downward so that one side of the three locking beads respectively passes through the corresponding first clearance holes and protrudes out of the accommodating cavity, or move upward so that the three locking beads retract into the accommodating cavity.

3. The space station debris protection device based on the pyrotechnic pressing seat according to claim 2 is characterized in that: The second connection component also includes: A housing, which is disposed outside the transmission shaft; The damper is installed in the housing and is used to limit the spontaneous rotation of the transmission shaft and to limit the spontaneous axial movement of the transmission shaft.

4. The space station debris protection device based on the pyrotechnic pressing seat according to claim 3 is characterized in that: Vertical guide grooves are respectively formed on the inner walls of the two opposite sides of the shell; The damper comprises: The lower limit plate has guide blocks matched with the vertical guide grooves on two opposite sides, and a circle of limit teeth on the top surface; An upper limit plate is sleeved on the upper part of the transmission shaft, and a circle of limit teeth is also arranged on the bottom surface; The tightening spring is sleeved on the upper part of the transmission shaft, the bottom end of which is fixedly connected to the top end of the locking disk, and the top end of which abuts against the bottom surface of the lower limit disk.

5. The space station debris protection device based on the pyrotechnic pressing seat according to claim 2 is characterized in that: The second connection component also includes: An operating wheel is mounted on the top end of the transmission shaft.

6. The space station debris protection device based on the pyrotechnic pressing seat according to any one of claims 1 to 5, characterized in that: Also includes: An adapter, one end of which is mounted on the protection component, and the other end of which is mounted on the second connection component.

7. The space station debris protection device based on the pyrotechnic pressing seat according to any one of claims 1 to 5, characterized in that: A second clearance hole is provided on the protection component; the second clearance hole is directly opposite to the second connecting component and can allow the pyrotechnic product compression seat to pass through.

8. The space station debris protection device based on the pyrotechnic pressing seat according to any one of claims 1 to 5, characterized in that: The protection component comprises: A first buffer layer; a second buffer layer, disposed above the top surface of the first buffer layer, with a buffer cavity reserved between the bottom surface and the top surface of the first buffer layer; The third connecting component is used to connect the second buffer layer and the first buffer layer.

9. The space station debris protection device based on the pyrotechnic pressing seat according to claim 8 is characterized in that: The first buffer layer comprises: There are four inner flame-retardant cloths; each inner flame-retardant cloth is coated with ten layers of aramid cloth stacked in sequence to form a buffer body; four buffer bodies are stacked in sequence; The outer flame-retardant cloth is coated outside the four buffer bodies.

10. The space station debris protection device based on the pyrotechnic pressing seat according to claim 8 is characterized in that: Also includes: The heat insulation component is coated on the first buffer layer, the second buffer layer and the third connection component.

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