A deformable spacecraft structure

Abstract

The application discloses a deformable spacecraft structure and relates to the technical field of spacecrafts, which comprises a telescopic module, a cabin module and a plurality of docking modules, the telescopic module is connected with the cabin module, the telescopic module can drive the cabin module to unfold and fold, the cabin module can be inflated to expand and form a movable cabin with a closed space, the docking module is arranged at the end of the cabin module, the docking module can be docked with other spacecrafts, and the cabin module is communicated with the inside of other spacecrafts. The application has strong space expansion capacity and can realize docking with other spacecrafts.

Description

Technical Field

[0001] This invention relates to the field of spacecraft technology, and in particular to a deformable spacecraft structure. Background Technology

[0002] With the rapid development of manned spaceflight, deep space exploration, and space science experiments, spacecraft are evolving from short-term on-orbit flights to long-term stays, multi-functional integration, and multi-mission expansion, placing increasingly stringent demands on the available internal space, equipment carrying capacity, and on-orbit adaptability. Traditional spacecraft cabins are constrained by the size of the launch vehicle fairing, the launch mechanics environment, and mass, requiring highly compact and fixed structural designs. Once assembled on the ground, the configuration and volume are fixed, making on-orbit morphological adjustments and spatial expansion impossible.

[0003] Due to the inherent constraints mentioned above, traditional spacecraft cabins generally suffer from the following technical defects: (1) The internal space is small and the equipment layout is limited: the fixed volume is difficult to accommodate large-size scientific research payloads, life support devices and operating space, the equipment installation density is high and the wiring is complicated, which is not conducive to on-orbit maintenance, upgrading and replacement. (2) Extremely weak on-orbit expansion capability: The cabin is a rigid closed structure with no on-orbit expansion interface or deployment mechanism. When mission requirements change or loads are iterated, the installation space cannot be increased, and the mission adaptability and life cycle are severely limited. (3) Poor scalability and insufficient mission flexibility: It is impossible to dynamically adjust the internal space according to the needs of on-orbit testing, manned stay or extravehicular operations, making it difficult to achieve multi-mission reuse and increasing the cost of spacecraft research and development and launch. Summary of the Invention

[0004] The purpose of this invention is to provide a deformable spacecraft structure to solve the problems existing in the prior art, which has strong spatial expansion capability and can dock with other spacecraft.

[0005] To achieve the above objectives, the present invention provides the following solution: This invention provides a deformable spacecraft structure, including a telescopic module, a cabin module, and several docking modules. The telescopic module is connected to the cabin module and can drive the cabin module to unfold and fold. The cabin module can be inflated to form an active cabin with a closed space. The docking module is located at the end of the cabin module and can dock with other spacecraft, enabling the cabin module to communicate with the interior of other spacecraft.

[0006] Preferably, the telescopic module is a telescopic ladder, and there are two sets of telescopic ladders. The two sets of telescopic ladders are symmetrically arranged, and the two sets of telescopic ladders are used to drive the two ends of the telescopic module to move towards each other or away from each other.

[0007] Preferably, the telescopic ladder includes a central slide rail and multiple extension slide rails, which are sequentially arranged inside and outside each other. The innermost extension slide rail is fitted around the outer periphery of the central slide rail. Adjacent extension slide rails and the innermost extension slide rail and the central slide rail are slidably connected by pulleys. The first end of the central slide rail is connected to the end of the cabin module. The central slide rail and the extension slide rails other than the outermost one can move towards or away from the center of the cabin module. The first end of the outermost extension slide rail is connected to the center of the cabin module. The central slide rail and each extension slide rail inside the outermost extension slide rail can move away from the center of the cabin module and drive the cabin module to unfold, or move towards the center of the cabin module and drive the cabin module to retract.

[0008] Preferably, the outer periphery of the central slide rail and the outer periphery of the non-outermost extended slide rail are provided with a drive motor, a power pulley and a plurality of driven pulleys. The output shaft of the drive motor is connected to the power pulley. The drive motor is used to drive the power pulley to rotate and cause the power pulley to move the central slide rail or the extended slide rail with the assistance of the driven pulleys.

[0009] Preferably, displacement sensors are provided on the outer periphery of the central slide rail and the outer periphery of the extension slide rails (excluding the outermost layer). The displacement sensors are used to detect the displacement of the central slide rail or the displacement of the extension slide rail. Both the displacement sensors and the drive motor are electrically connected to the controller. The displacement information detected by the displacement sensors can be transmitted to the controller, enabling the controller to control the working state of the drive motor.

[0010] Preferably, a liquefied nitrogen tank is provided in the middle of the cabin module. The outlet of the liquefied nitrogen tank is connected to a jet pipe via a valve. The jet pipe is provided with a nitrogen nozzle. The nitrogen nozzle is used to spray nitrogen from the liquefied nitrogen tank into the cabin module, causing the cabin module to inflate. A pressure sensor is also provided in the cabin module. The pressure sensor is used to detect the air pressure inside the cabin module and control the opening and closing of the valve at the outlet of the liquefied nitrogen tank according to the air pressure via a controller.

[0011] Preferably, each end of the cabin module is provided with a position adjustment component, which includes a high-pressure nitrogen tank, an external multi-functional sensor, and multiple position nozzles. An internal multi-functional sensor is provided in the middle of the cabin module. The external and internal multi-functional sensors work together to detect the attitude of the cabin module and control the opening and closing of each position nozzle through a controller. Each position nozzle is connected to the outlet valve of the high-pressure nitrogen tank through a pipe, and each position nozzle on the same side faces different directions. By spraying nitrogen from different position nozzles, the attitude of the cabin module can be adjusted.

[0012] Preferably, each end of the cabin module is provided with a docking module, and each docking module is provided with a laser rangefinder for detecting the distance between the docking module and other spacecraft. The docking module is also provided with a docking hatch, which can be opened when the docking module docks with other spacecraft and forms an airtight connection.

[0013] Preferably, the cabin module is made of a composite membrane, and the composite membrane is deformable. The composite membrane consists of an aluminized polyimide film, a Kevlar fiber woven mesh, an airtight polymer material layer, and a graphene-based phase change material layer from the outside to the inside. A flexible solar panel is provided on the outer periphery of the composite membrane.

[0014] Preferably, before lamination, the interface between the aluminized polyimide film and the Kevlar fiber woven mesh is treated with plasma. The treated aluminized polyimide film, the treated Kevlar fiber woven mesh, and the airtight polymer material layer are then laid out sequentially. Vacuum bagging technology is used to remove air bubbles at the joints, and epoxy resin is injected to fill the tiny gaps at the joints. After the aluminized polyimide film, the treated Kevlar fiber woven mesh, and the airtight polymer material layer are bonded, heat treatment is performed. Finally, a graphene-based phase change material layer is deposited on the inner side of the airtight polymer material layer using a chemical vapor deposition process.

[0015] The present invention achieves the following technical effects compared to the prior art: The deformable spacecraft structure provided by this invention includes a telescopic module, a cabin module, and several docking modules. The telescopic module is connected to the cabin module and can drive the cabin module to unfold and fold. During launch, the telescopic module folds the cabin module, keeping it in a compact state for easy launch. When the deformable spacecraft structure needs to be used, the telescopic module unfolds the cabin module and inflates it to form a movable cabin with a closed space, increasing the internal space and providing strong spatial expansion capabilities. The docking modules are located at the ends of the cabin modules and can dock with other spacecraft, allowing the cabin module to communicate with the interior of other spacecraft, thus facilitating entry into the cabin module for research operations. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the deformable spacecraft structure in this invention during deployment; Figure 2 This is a schematic diagram of the deformable spacecraft structure in this invention when folded. Figure 3 for Figure 2 Side view; Figure 4 This is a schematic diagram of the telescopic ladder in this invention; Figure 5 This is a schematic diagram showing the relative positions of the drive motor and the power pulley in this invention; Figure 6 This is a schematic diagram showing the relative positions of the driving pulley and the driven pulley in this invention; In the diagram: 1-cabin module, 2-telescopic module, 21-center slide rail, 22-extension slide rail, 23-drive motor, 24-power pulley, 25-displacement sensor, 26-driven pulley, 3-docking module, 31-position adjustment nozzle, 32-laser rangefinder, 33-external multi-functional sensor, 34-high-pressure nitrogen tank, 4-filling module, 41-liquefied nitrogen tank, 42-nitrogen nozzle, 43-internal multi-functional sensor. Detailed Implementation

[0018] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. 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.

[0019] The purpose of this invention is to provide a deformable spacecraft structure to solve the problems existing in the prior art, which has strong spatial expansion capabilities and can dock with other spacecraft.

[0020] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0021] like Figures 1-6 As shown, this embodiment provides a deformable spacecraft structure, including a telescopic module 2, a cabin module 1, and several docking modules 3. The telescopic module 2 is connected to the cabin module 1, and the telescopic module 2 can drive the cabin module 1 to unfold and fold. Thus, when launching the deformable spacecraft structure, the telescopic module 2 drives the cabin module 1 to fold, so that the cabin module 1 is in a compact state, occupying only 1 / 10 of the final unfolded volume at the vehicle-rocket interface, which is convenient for launch. When the deformable spacecraft structure needs to be used, the telescopic module 2 drives the cabin module 1 to unfold, and the cabin module 1 is inflated to form an active cabin with a closed space. At this time, the space inside the cabin module 1 can be increased, and the space expansion capability is strong. The docking modules 3 are located at the ends of the cabin module 1, and the docking modules 3 can dock with other spacecraft, and connect the cabin module 1 with the interior of other spacecraft, thereby facilitating entry into the interior of the cabin module 1 for research operations.

[0022] Specifically, the telescopic module 2 is a telescopic ladder, and there are two sets of telescopic ladders. The two sets of telescopic ladders are symmetrically arranged, and the two sets of telescopic ladders are used to drive the two ends of the telescopic module 2 to move towards each other or away from each other, thereby realizing the folding and unfolding of the telescopic module 2.

[0023] The telescopic ladder includes a central slide rail 21 and multiple extension slide rails 22. The extension slide rails 22 are sequentially arranged inside and outside each other, with the innermost extension slide rail 22 fitted around the outer periphery of the central slide rail 21, thus placing the central slide rail 21 at the innermost position. Adjacent extension slide rails 22, as well as the innermost extension slide rail 22 and the central slide rail 21, are slidably connected by pulleys (including a driving pulley 24 and a driven pulley 26). This allows for stable sliding of the central slide rail 21 relative to the innermost extension slide rail 22, and also stable sliding between adjacent extension slide rails 22. The first end of the slide rail 21 is connected to the end of the cabin module 1 so as to drive the end of the cabin module 1 to move. The center slide rail 21 and the non-outermost extension slide rail 22 can move towards or away from the middle of the cabin module 1, thereby controlling the moving distance of the end of the cabin module 1. The first end of the outermost extension slide rail 22 is connected to the middle of the cabin module 1. The center slide rail 21 and the non-outermost extension slide rail 22 can both move away from the middle of the cabin module 1 and drive the cabin module 1 to unfold, or move towards the middle of the cabin module 1 and drive the cabin module 1 to retract.

[0024] In this embodiment, the number of extension slide rails 22 is preferably four. Those skilled in the art can also make adaptive adjustments to the number and length of extension slide rails 22 according to actual needs.

[0025] The first ends of the central slide rails 21 in the two sets of telescopic ladders are respectively bolted to the left and right ends of the cabin module 1, and the outermost extension slide rails 22 in the two sets of telescopic ladders are bolted to the inner wall of the cabin in the middle of the cabin module 1.

[0026] The outer periphery of the central slide rail 21 and the outer periphery of the non-outermost extension slide rail 22 are provided with a drive motor 23, a power pulley 24 and several driven pulleys 26. The output shaft of the drive motor 23 is connected to the power pulley 24. The drive motor 23 is used to drive the power pulley 24 to rotate. As the power pulley 24 rotates, the power pulley 24 on the central slide rail 21 can drive the central slide rail 21 to slide relative to the innermost extension slide rail 22. The power pulley 24 on the extension slide rail 22 can drive the extension slide rail 22 to slide relative to the adjacent extension slide rail 22. During this sliding process, the presence of the driven pulleys 26 makes the sliding process smoother and more stable.

[0027] In this embodiment, the number and position of the driven pulleys 26 on the central slide rail 21 and the extension slide rail 22 can be adapted by those skilled in the art according to actual needs.

[0028] Displacement sensors 25 are provided on the outer periphery of the central slide rail 21 and the outer periphery of the non-outermost extension slide rail 22. That is, the displacement sensor 25 located on the outer periphery of the central slide rail 21 is used to detect the displacement of the central slide rail 21, and the displacement sensor 25 located on the outer periphery of the extension slide rail 22 is used to detect the displacement of the extension slide rail 22. The displacement sensors 25 and the drive motors 23 are electrically connected to the controller. The displacement information detected by the displacement sensors 25 is transmitted to the controller, and the controller controls the working state of each drive motor 23 according to the displacement information to ensure that the end of the cabin module 1 can move into place and automatically stop moving after moving into place, so as to ensure that the cabin module 1 can be unfolded to the required state.

[0029] In this embodiment, nickel-titanium alloy (Nitinol) ribs can also be embedded inside the center slide rail 21 and the extension slide rail 22. The ribs are designed to be in a "pre-deformed" state. When the main telescopic system fails, the ribs can automatically recover to the preset shape through temperature changes. The ribs and the center slide rail 21 / extension slide rail 22 form a "double track" structure, and the center slide rail 21 / extension slide rail 22 are moved by the ribs.

[0030] The central part of the cabin module 1 is equipped with an inflation module 4, which includes a liquefied nitrogen tank 41. The outlet of the liquefied nitrogen tank 41 is connected to a jet pipe via a valve. The jet pipe is equipped with a nitrogen nozzle 42, which is used to spray nitrogen from the liquefied nitrogen tank 41 into the cabin module 1, causing the cabin module 1 to inflate and expand into a spherical or near-spherical movable cabin. That is, the cabin module 1 forms a safe research space several times the launch volume, which facilitates operations. The cabin module 1 is also equipped with a pressure sensor, which is used to detect the air pressure inside the cabin module 1. Based on the air pressure, the controller controls the opening and closing of the valve at the outlet of the liquefied nitrogen tank 41 to prevent the air pressure inside the cabin module 1 from being too low and failing to inflate to the required extent, and also to prevent the air pressure inside the cabin module 1 from being too high and affecting safety.

[0031] Each end of the cabin module 1 is equipped with a position adjustment component, which enables position and attitude adjustment of the cabin module 1. The position adjustment component includes a high-pressure nitrogen tank 34, an external multi-functional sensor 33, and multiple position nozzles. Preferably, there are 8 position nozzles on each side, which are evenly arranged circumferentially. An internal multi-functional sensor 43 is located in the middle of the cabin module 1. The external multi-functional sensor 33 and the internal multi-functional sensor 43 work together to detect the attitude of the cabin module 1 and control the opening and closing of each position nozzle through a controller. Based on the actual attitude of the cabin module 1, the controller determines whether to spray nitrogen at each position nozzle to adjust the attitude of the cabin module 1 to the required attitude, which facilitates docking with other spacecraft. Each position nozzle is connected to the outlet valve of the high-pressure nitrogen tank 34 through a pipe, and the position nozzles on the same side face different directions. By spraying nitrogen from different position nozzles, the attitude of the cabin module 1 can be adjusted.

[0032] In practical applications, the data obtained by the internal multi-functional sensor 43 and the external multi-functional sensor 33 are calculated by a computer, and then nitrogen gas is injected to adjust the attitude and position of the cabin module 1. The internal multi-functional sensor 43 integrates a three-axis gyroscope to measure the attitude angular velocity of the cabin module 1, and a three-axis accelerometer to measure the linear acceleration of the cabin module 1. The external multi-functional sensor 33 integrates a star sensor to determine star positioning and the attitude of the cabin module 1, a GPS receiver to determine the orbital position of the cabin module 1, and a gravity gradient sensor to monitor changes in the Earth's gravitational field.

[0033] Each end of module 1 has a docking module 3. The docking module 3 can be equipped with the International Space Station IDSS standard docking flange, which can be adapted to spacecraft such as the International Space Station. The docking module 3 is equipped with a laser rangefinder 32, which is used to detect the distance between the docking module 3 and other spacecraft, so as to make autonomous judgment on whether the optimal docking distance has been reached. The docking module 3 is equipped with a docking hatch. When the docking module 3 docks with other spacecraft and forms an airtight connection, the docking hatch can be opened, which makes it easier for astronauts to enter the module 1.

[0034] In practical applications, when the deformable spacecraft structure in this embodiment is sent into space, the telescopic ladder drives the two ends of the cabin module 1 to extend to a specified length, after which the cabin module 1 is inflated, thus expanding the cabin module 1 until it reaches a certain size and pressure. Then, the position and attitude of the cabin module 1 are adjusted and maintained by the position adjustment nozzle 31. At this time, other spacecraft can dock through the spacecraft docking interface and then enter this deformable spacecraft structure to carry out research operations.

[0035] The cabin module 1 is made of a composite membrane that is deformable. The composite membrane consists of an aluminized polyimide film, a Kevlar fiber woven mesh, an airtight polymer material layer, and a graphene-based phase change material layer from the outside to the inside. The thickness of the aluminized polyimide film is preferably 0.1 mm, which is used to reflect electromagnetic waves and prevent radiation. The porosity of the Kevlar fiber woven mesh is ≤1%, and the impact strength is ≥500 MPa. The airtight polymer material layer can maintain the air pressure inside the cabin module 1 at 0.1 MPa and has a temperature difference adaptability range of -200℃ to 250℃.

[0036] The composite film has a flexible solar panel on its outer periphery for generating electricity. During installation, a special adhesive based on polyimide is used to firmly attach the flexible solar panel to the aluminized polyimide film through special pretreatment and bonding processes, while maintaining the optical performance of the aluminized layer and the power generation efficiency of the flexible solar panel. The special pretreatment methods include cleaning the surface of the aluminized polyimide film to remove all oil and impurities, using plasma cleaning technology to treat the surface of the aluminized polyimide film to improve surface properties and enhance adhesion, and using laser micro-engraving technology to create a micron-level uneven structure on the surface of the aluminized polyimide film to increase mechanical interlocking points. Finally, a special adhesive based on polyimide is used to install and fix the two together.

[0037] Before lamination, all materials undergo surface treatment to improve interlayer adhesion. The interface between the aluminized polyimide film and the Kevlar fiber woven mesh is treated with plasma. The treated aluminized polyimide film, the treated Kevlar fiber woven mesh, and the airtight polymer material layer are then laid out sequentially. Resin transfer molding is recommended during lamination. Vacuum bagging technology is used to remove air bubbles at the joints to ensure interlayer uniformity. Epoxy resin is injected to fill the tiny gaps at the joints and improve overall strength. After the aluminized polyimide film, the treated Kevlar fiber woven mesh, and the airtight polymer material layer are bonded, heat treatment is performed. The preferred heat treatment parameters are 120°C for 2 hours to enhance interlayer adhesion. During interlayer treatment, a thin layer of silicone can be coated on the outside of the airtight polymer material layer to improve airtightness. Finally, a graphene-based phase change material layer is deposited on the inside of the airtight polymer material layer using a chemical vapor deposition process.

[0038] The working process of the deformable spacecraft structure in this embodiment is as follows: (1) Rocket launch phase: The cabin module 1 folds into a compact form, and the telescopic ladder is in a compressed state; The liquefied nitrogen tank 41 is pre-filled with liquid nitrogen (-196℃), and the nitrogen nozzle 42 is closed.

[0039] (2) On-orbit deployment phase: S1. Extendable ladder unfolds: The servo motor operates, driving each power pulley 24 to rotate in an orderly manner, and ultimately causing the two ends of the cabin module 1 to move away from each other; based on the data transmitted by the laser sensor, the telescopic ladder extends to the specified length and proceeds to the next step; S2. Inflate cabin module 1: The liquefied nitrogen tank 41 delivers vaporized nitrogen to the nitrogen nozzle 42 through a pipeline; the nitrogen nozzle 42 injects nitrogen into the cabin module 1 (i.e., inside the composite membrane), causing the pressure inside the cabin module 1 to gradually rise to the specified pressure; after the composite membrane has expanded to a certain extent, when the pressure sensor detects that the internal air pressure has reached the specified pressure, the air pressure is locked and the inflation stops. S3. Position Adjustment: The data obtained by the internal multi-function sensor 43 and the external multi-function sensor 33 are calculated by AI and then the position adjustment nozzle 31 is activated to inject nitrogen gas to adjust the attitude of the cabin module 1 to a horizontal position; the position adjustment nozzle 31 continues to work to maintain the stable position of the cabin. (3) Integration and Usage Phase: When other spacecraft to be docked approach, data is obtained from the internal multi-functional sensor 43 and external functional sensors. The attitude of the stabilizing module 1 is then adjusted through AI calculations. The docking module 3 captures the target and establishes a preliminary connection. The distance data between the docking module 3 and other spacecraft to be docked is obtained through the laser rangefinder 32. The docking module 3 automatically locks, forming an airtight connection. The docking hatch is sealed, the air pressure inside the module 1 is maintained at 0.1 MPa, and the docking hatch opens automatically, allowing astronauts to enter.

[0040] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. A deformable spacecraft structure, characterized in that: It includes a telescopic module, a cabin module, and several docking modules. The telescopic module is connected to the cabin module and can drive the cabin module to unfold and fold. The cabin module can be inflated to form an active cabin with a closed space. The docking module is located at the end of the cabin module and can dock with other spacecraft, enabling the cabin module to communicate with the interior of other spacecraft.

2. The deformable spacecraft structure according to claim 1, characterized in that: The telescopic module is a telescopic ladder, and there are two sets of telescopic ladders. The two sets of telescopic ladders are symmetrically arranged, and the two sets of telescopic ladders are used to drive the two ends of the telescopic module to move towards each other or away from each other.

3. The deformable spacecraft structure according to claim 2, characterized in that: The telescopic ladder includes a central slide rail and multiple extension slide rails, which are sequentially arranged inside and outside each other. The innermost extension slide rail is fitted around the outer periphery of the central slide rail. Adjacent extension slide rails and the innermost extension slide rail is slidably connected to the central slide rail by pulleys. The first end of the central slide rail is connected to the end of the cabin module. The central slide rail and the extension slide rails other than the outermost one can move towards or away from the center of the cabin module. The first end of the outermost extension slide rail is connected to the center of the cabin module. The central slide rail and each extension slide rail inside the outermost extension slide rail can move away from the center of the cabin module, thereby unfolding the cabin module, or move towards the center of the cabin module, thereby retracting the cabin module.

4. The deformable spacecraft structure according to claim 3, characterized in that: The outer periphery of the central slide rail and the outer periphery of the non-outermost extended slide rail are provided with a drive motor, a power pulley and several driven pulleys. The output shaft of the drive motor is connected to the power pulley. The drive motor is used to drive the power pulley to rotate, and the power pulley, with the assistance of the driven pulleys, drives the central slide rail or the extended slide rail to move.

5. The deformable spacecraft structure according to claim 4, characterized in that: Displacement sensors are provided on the outer periphery of the central slide rail and the outer periphery of the extension slide rails (not the outermost layer). The displacement sensors are used to detect the displacement of the central slide rail or the displacement of the extension slide rail. The displacement sensors and the drive motor are both electrically connected to the controller. The displacement information detected by the displacement sensors can be transmitted to the controller, enabling the controller to control the working state of the drive motor.

6. The deformable spacecraft structure according to claim 1, characterized in that: A liquefied nitrogen tank is located in the middle of the cabin module. The outlet of the liquefied nitrogen tank is connected to a jet pipe via a valve. The jet pipe is equipped with a nitrogen nozzle, which is used to spray nitrogen from the liquefied nitrogen tank into the cabin module, causing the cabin module to inflate. A pressure sensor is also installed in the cabin module to detect the air pressure inside the cabin module and control the opening and closing of the valve at the outlet of the liquefied nitrogen tank according to the air pressure via a controller.

7. The deformable spacecraft structure according to claim 1, characterized in that: Each end of the cabin module is equipped with a position adjustment component, which includes a high-pressure nitrogen tank, an external multi-functional sensor, and multiple position nozzles. An internal multi-functional sensor is located in the middle of the cabin module. The external and internal multi-functional sensors work together to detect the attitude of the cabin module and control the opening and closing of each position nozzle through a controller. Each position nozzle is connected to the outlet valve of the high-pressure nitrogen tank through a pipe, and the position nozzles on the same side face different directions. By spraying nitrogen from different position nozzles, the attitude of the cabin module can be adjusted.

8. The deformable spacecraft structure according to claim 7, characterized in that: Each end of the cabin module is provided with a docking module. A laser rangefinder is provided at each docking module. The laser rangefinder is used to detect the distance between the docking module and other spacecraft. The docking module is provided with a docking hatch. When the docking module docks with other spacecraft and forms an airtight connection, the docking hatch can be opened.

9. The deformable spacecraft structure according to claim 1, characterized in that: The cabin module is made of a composite membrane, and the composite membrane is deformable. The composite membrane consists of an aluminized polyimide film, a Kevlar fiber woven mesh, an airtight polymer material layer, and a graphene-based phase change material layer from the outside to the inside. A flexible solar panel is provided on the outer periphery of the composite membrane.

10. The deformable spacecraft structure according to claim 9, characterized in that: Before lamination, the interface between the aluminized polyimide film and the Kevlar fiber woven mesh is treated with plasma. The treated aluminized polyimide film, the treated Kevlar fiber woven mesh, and the airtight polymer material layer are then laid out sequentially. Vacuum bagging technology is used to remove air bubbles at the joints, and epoxy resin is injected to fill the tiny gaps at the joints. After the aluminized polyimide film, the treated Kevlar fiber woven mesh, and the airtight polymer material layer are bonded together, they are subjected to heat treatment. Finally, a graphene-based phase change material layer is deposited on the inner side of the airtight polymer material layer using a chemical vapor deposition process.

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