Intelligent pre-tightening device for satellite locking mechanism and hot coating winding system and method

Abstract

The invention relates to the technical field of thermal control of spacecrafts, in particular to an intelligent pre-tightening device for a satellite locking mechanism and a thermal coating winding system and method. The intelligent pre-tightening device is made of an intelligent polymer composite material, can generate compressive plastic deformation through controlled heating softening and pressurization during assembly, and locks deformation after cooling, so that pre-tightening force for resisting emission vibration is actively generated and permanently kept. The intelligent pre-tightening device solves the problem that traditional mechanical locking is prone to loosening under vibration, and high-reliability locking is achieved. The system comprises the pre-tightening device, and an intelligent locking device and an intelligent furling device which are both made of intelligent materials and can be thermally recovered. The locking device is used for locking or releasing the furling device, and the furling device is used for furling or unfolding the hot coating; the system is driven by a heating system. The method comprises the steps that during ground assembling, heat-force coupling is conducted on the pre-tightening device to set the pre-tightening force, the locking device is firstly heated and unlocked during on-orbit assembling, and then the winding device is heated to conduct winding and hot wrapping.

Description

Technical Field

[0001] This invention relates to the field of spacecraft thermal control technology, and in particular to an intelligent pre-tightening device, a thermal wrapping and winding system and method for satellite locking mechanisms. Background Technology

[0002] While in orbit, a satellite radiates waste heat into space through its exposed heat dissipation surfaces. During the launch phase, as the satellite passes through the atmosphere, to prevent the extremely high heat flux generated by aerodynamic heating from entering the satellite through the heat dissipation surfaces, a deployable thermal envelope must be used to temporarily insulate the heat dissipation surfaces. This requires the thermal envelope system to be securely locked in place during the launch phase.

[0003] Currently, most locking mechanisms rely on mechanical pre-tightening methods such as bolts, clips, and ropes. Under the extreme vibration and impact loads experienced during launch vehicle launches, these mechanical connections have inherent drawbacks: the pre-tightening force is set once during assembly and cannot be compensated for or enhanced during vibration, leading to loosening and slippage at the connection points, causing pre-tightening force attenuation or even complete failure. If locking fails, the thermal insulation layer may accidentally detach during launch, resulting in loss of thermal insulation and endangering satellite safety. Therefore, ensuring that the locking mechanism can stably maintain the preset pre-tightening force under dynamic loads throughout the launch process is a long-standing challenge in the design of highly reliable aerospace structures. Summary of the Invention

[0004] The purpose of this invention is to overcome the shortcomings of the prior art and provide an intelligent pretensioning device that can actively set and stably maintain pretensioning force under vibration environment, a satellite thermal wrapping and winding system including the intelligent pretensioning device, and a control method thereof.

[0005] To achieve the above objectives, in a first aspect, the present invention provides an intelligent pre-tightening device for a satellite locking mechanism, which is made of intelligent polymer composite material; The device is configured to soften during assembly by a controlled first thermal excitation and to produce a preset compressive plastic deformation under applied pressure along its thickness direction. When the initial thermal excitation is removed, the compressive plastic deformation is locked by the material, thereby providing a continuous active preload to the locking mechanism assembled with it to resist the vibration loads during the satellite launch phase.

[0006] Optionally, the intelligent pre-tightening device includes an upper platform, a lower platform, and a support structure connecting the upper platform and the lower platform; The upper platform and the lower platform are arranged at intervals along the thickness direction of the intelligent pre-tightening device, and the thickness direction is parallel to the direction of the pre-tightening force. The support structure is configured to bear pressure in the thickness direction and transmit the pressure to the lower platform, and the support structure is designed such that its lateral deformation rate is less than a preset threshold when it is compressed in the thickness direction. The upper platform is used to support the base of the locking mechanism, and the lower platform is used to install it on the satellite structure.

[0007] Optionally, the support structure includes two spaced-apart and mirror-symmetrically arranged support plates; Each support plate has at least one bend in its height direction, and at the bend of each support plate, there is a through hole for weight reduction and stress relief in a direction parallel to the upper and lower platforms. The upper ends of both support plates are integrally connected to the upper platform, and the lower ends are integrally connected to the lower platform, together forming a support frame with low lateral deformation characteristics under vertical load.

[0008] Optionally, the smart polymer composite material is a fiber-reinforced shape memory resin-based composite material.

[0009] Secondly, the present invention also provides a satellite thermal wrapping and winding system, comprising: an intelligent pre-tightening device, an intelligent winding device, an intelligent locking device, a heating system, and thermal wrapping; The intelligent pretensioning device is the intelligent pretensioning device described in any one of the first aspects; Both the intelligent winding device and the intelligent locking device are made of intelligent polymer composite material and have an initial shape that can be restored by thermal excitation; the intelligent locking device is configured to lock or release the intelligent winding device, and the intelligent winding device is configured to wind up or unwind the thermal coating. The thermal wrapping is configured to wrap the satellite's heat dissipation surface and include an intelligent winding device, an intelligent locking device, and an intelligent pre-tightening device, and can be wound up by the intelligent winding device to expose the satellite's heat dissipation surface. The heating system is used to heat the intelligent winding device and the intelligent locking device independently or sequentially to trigger their shape recovery function.

[0010] Optionally, the two sets of intelligent pre-tightening devices are respectively installed at two corners on one side of the satellite's heat dissipation surface; The roots of the two intelligent winding devices are attached to the two corners on the other side of the satellite's heat dissipation surface, with the ends of the intelligent winding devices facing the intelligent pre-tightening device. The roots of the two sets of intelligent locking devices are mounted on top of the intelligent pre-tightening device, and the ends of the intelligent locking devices are provided with locking components. The ends of the intelligent winding device are provided with locking holes that match the locking components. The locking components and locking holes cooperate to achieve locking. The heat-wrapping system uses Velcro to connect and wrap the intelligent winding device, intelligent locking device, intelligent pre-tightening device, and satellite heat dissipation surface.

[0011] Optionally, the locking component is a protruding locking portion, and the lock hole is a recess that matches the protruding locking portion.

[0012] Optionally, the pre-tightening force generated by the intelligent pre-tightening device through thermal deformation is perpendicular to the plane of the satellite's heat dissipation surface.

[0013] Optionally, the intelligent winding device is rod-shaped or plate-shaped, with one end fixed to the satellite heat dissipation surface and the other end locked by an intelligent locking device along its length; and along the length of the intelligent winding device, the intelligent winding device is divided into multiple heating sections, each of which is heated sequentially by the heating system.

[0014] Optionally, the initial shape of the intelligent locking device is an L-shaped plate with rounded corners, which is composed of two plate segments arranged vertically or nearly vertically connected by a rounded transition section. The temporary shape of the intelligent locking device is flat; In the locked state, the smart locking device is maintained in a temporary shape; when unlocked, the smart locking device is heated to return it to its initial shape.

[0015] Optionally, the heat coating includes a fixed section fixedly connected to the intelligent locking device, and a take-up section bonded to the intelligent take-up device and capable of being wound up with it.

[0016] Thirdly, the present invention also provides a control method for a satellite thermal wrapping and winding system, applied to the satellite thermal wrapping and winding system described in any one of the second aspects, the method comprising: System assembly and preload setting steps: The intelligent pre-tightening device, the intelligent locking device in a temporary flat state, and the intelligent winding device in a temporary flat state are assembled at predetermined positions on the satellite's heat dissipation surface. The intelligent pre-tightening device is subjected to a first thermal excitation to soften it; Pressure is applied along the thickness direction to the softened intelligent pre-tightening device to induce compressive plastic deformation. Stop the first thermal excitation to allow the intelligent pre-tightening device to cool down and lock the compression plastic deformation, thereby providing active pre-tightening force for the intelligent locking device; The heat-shrink wrapping is unfolded and secured to the assembled devices and satellite heat dissipation surfaces using Velcro. On-orbit unlocking and rewinding steps: After the satellite enters orbit, the heating system heats the intelligent locking device, causing it to return to its initial shape, thereby releasing the locking of the intelligent winding device; The intelligent winding device is heated by a heating system, causing it to return to its initial curled shape, thereby winding up the heat-covered surface and exposing the satellite's heat dissipation surface.

[0017] Optionally, during the system assembly and preload setting steps, the operation of applying pressure to the intelligent preload device continues until the intelligent preload device cools down below its glass transition temperature.

[0018] The above-described technical solution of the present invention has the following advantages: The intelligent pre-tightening device provided by this invention utilizes the thermo-mechanical coupling characteristics of intelligent polymer composite materials. Through a one-time "heating softening-pressurization deformation-cooling locking" process during ground assembly, a preset compression deformation is permanently "programmed" and stored within the material, thereby transforming it into a continuous and stable active pre-tightening force. This pre-tightening force does not rely on the static friction of traditional threaded connections. Therefore, when subjected to extreme vibration and impact loads during satellite launch, there will be no pre-tightening force attenuation or failure due to fretting or loosening. This fundamentally solves the long-standing technical problem of insufficient reliability of mechanical locking mechanisms under high dynamic load environments, providing reliable locking assurance for critical satellite mechanisms.

[0019] The satellite thermal wrapping and rewinding system provided by this invention includes intelligent pre-tightening, intelligent locking, and intelligent winding devices with shape memory function, combined with a rewindable thermal wrapping and heating control system. This achieves fully intelligent and programmed operation of the entire process from "launch thermal insulation" to "on-orbit heat dissipation." The system eliminates traditional moving parts such as motors, gears, and complex linkages, greatly simplifying the structure, significantly reducing weight, and improving inherent reliability. Through coordinated thermal excitation, each intelligent component completes a complex task chain from reliable locking to non-destructive unlocking, and then to smooth and orderly winding, providing satellites with a lightweight, highly reliable, and shock-free novel thermal control solution.

[0020] The control method for a satellite thermal wrapping and winding system provided by this invention sets an anti-vibration preload through key "heating-pressurization-cooling and locking" steps during the ground phase. During the on-orbit phase, the reliability and stability of the operation are ensured through sequential control of unlocking followed by winding. This method transforms the characteristics of smart materials into controllable system behavior, making the entire thermal wrapping and winding process predictable and controllable. It avoids the uncontrollable impacts and potential jamming risks associated with traditional mechanisms during deployment, and represents a necessary and optimized operational logic for achieving the system's intended functions. Attached Figure Description

[0021] The accompanying drawings are provided for illustrative purposes only, and the proportions and quantities of the components in the drawings may not be consistent with the actual product.

[0022] Figure 1 This is a schematic diagram of the unfolded state of a satellite thermal wrapping and winding device according to an embodiment of the present invention; Figure 2 yes Figure 1 A schematic diagram of the exploded state of the satellite thermal wrapping and winding device; Figure 3 yes Figure 2 Enlarged diagram of part A in the diagram; Figure 4 This is a schematic diagram of the structure of an intelligent winding device according to an embodiment of the present invention; Figure 5 yes Figure 4 Schematic diagram of the winding state structure of the intelligent winding device; Figure 6 This is a schematic diagram of the structure of an intelligent pre-tightening device according to an embodiment of the present invention; Figure 7 yes Figure 6 A front view structural diagram of the intelligent pre-tightening device; Figure 8 yes Figure 1 Schematic diagram of the winding state of the Zhongweixing thermal coating winding device; Figure 9 This is a schematic diagram of the unlocking state of an intelligent locking device according to an embodiment of the present invention.

[0023] In the picture: 100: Satellite; 101: Heat dissipation surface; 200: Satellite thermal wrapping and winding system; 210: Intelligent pre-tightening device; 211: Upper platform; 212: Lower platform; 213: Support structure; 2131: Support plate; 2132: Through hole; 214: Connection hole; 220: Intelligent winding device; 221: Locking hole; 230: Intelligent locking device; 231: Locking component; 240: Heating film; 250: Velcro; 260: Heat-coating; 261: Fixed section; 262: Rewinding section. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, 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, 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.

[0025] Example 1 This embodiment provides an intelligent pre-tensioning device for a satellite locking mechanism, which is configured as follows: During the ground assembly of the satellite thermal control system, operators use tools such as hot air guns to heat the device (first thermal excitation), raising its temperature to approximately 150°C (exceeding its glass transition temperature), softening the material. Subsequently, a locking mechanism (such as the intelligent locking device in this application) is placed above the intelligent pre-tightening device, and the connecting screws are tightened, applying pressure along its thickness direction (perpendicular to the heat dissipation surface) to the intelligent pre-tightening device. Under this pressure, the intelligent pre-tightening device as a whole generates a preset compression amount (compressive plastic deformation), for example, 0.5 mm, 0.8 mm, or 1 mm. The pressure is maintained, heating is stopped, and the device is allowed to cool naturally to room temperature (approximately 25°C). After cooling, the material shape is fixed, and the compressive deformation is permanently locked within the material. This locked deformation continuously pushes the locking mechanism upwards, thus providing the locking mechanism with a constant active pre-tightening force to resist vibration loads perpendicular to the heat dissipation surface during satellite launch.

[0026] The preload force originates from the deformation locked within the material, rather than relying on the friction of the bolt. Therefore, it will not loosen or decay when encountering strong vibrations during launch, fundamentally solving the problem of unreliable traditional mechanical preload.

[0027] In one embodiment, see Figure 6 and Figure 7 The intelligent pre-tightening device 210 includes a square upper platform 211, a lower platform 212 of the same size, and a support structure 213 connecting the two. The upper platform 211 and lower platform 212 are spaced apart along the thickness direction of the intelligent pre-tightening device 210, which is parallel to the direction of the pre-tightening force. The upper platform 211 supports the intelligent locking device 230, and the lower platform 212 contacts the satellite's heat dissipation surface. The intelligent pre-tightening device 210 can be installed on the satellite's heat dissipation surface using conventional fixing methods such as screws, or it can be fixed to the satellite's heat dissipation surface by the clamping of the intelligent locking device 230. For example, the intelligent pre-tightening device 210 has a connecting hole that passes through the upper platform 211 and the lower platform 212. During installation, it and the intelligent locking device 230 share a fixing screw; that is, the fixing screw passes through the intelligent locking device 230 and then through the connecting hole 214 to connect with the satellite's heat dissipation surface via a threaded connection.

[0028] In this embodiment, the support structure 213 is specifically designed to have a lateral deformation rate less than a preset threshold when the device is compressed in the thickness direction. For example, a zero Poisson's ratio structure. When the structure is compressed vertically, its lateral (horizontal) dimensional change is small; for example, when the structure is compressed vertically, its lateral (horizontal) dimensional change rate (Poisson's ratio) is less than 0.1. The upper and lower platforms of the intelligent pretensioning device 210 provide standard installation interfaces. The zero Poisson's ratio support structure 213 ensures that the device hardly expands outwards when generating vertical pretensioning force, guaranteeing the purity and directional stability of the pretensioning force transmission.

[0029] See one example. Figure 6 and Figure 7 The support structure 213 consists of two thin, plate-like support plates 2131, which are spaced apart, parallel, and mirror-symmetrical. Each support plate 2131 has a horizontally bent structure in its height direction. At this bend, a through hole 2132 is opened in the horizontal direction to reduce weight and release stress. The upper edges of the two support plates 2131 are integrally connected to the upper platform 211, and the lower edges are integrally connected to the lower platform 212. These two mirror-symmetrical support plates together form a support frame with low lateral deformation characteristics under vertical load. The support structure 213 is simple, lightweight, and easy to manufacture. The mirror-symmetrical design of the two support plates 2131 mutually restricts their lateral deformation under compression, effectively achieving the mechanical characteristics of low lateral deformation (close to zero Poisson's ratio). The through hole reduces weight and releases stress concentration at the bend, improving fatigue life. This specific structure is an efficient and reliable solution for achieving zero Poisson's ratio functionality.

[0030] Of course, in some implementations, each support plate 2131 has multiple consecutive bends in its height direction.

[0031] In this embodiment, the smart polymer composite material is a fiber-reinforced shape memory resin matrix composite. This material uses epoxy shape memory resin as the matrix and exhibits high stiffness below its glass transition temperature (e.g., 140°C), while softening and plastically deforming above it. Fiber reinforcement endows the composite material with extremely high specific strength and specific modulus, meeting the requirements of aerospace load-bearing structures. The shape memory resin matrix provides crucial thermotropic softening and shape locking / recovery properties. This material combination enables the smart preload device to simultaneously meet the stringent requirements of load-bearing capacity, intelligent deformation, and space environment tolerance. This type of smart polymer composite material is a relatively mature technology and will not be described in detail here.

[0032] Example 2 See Figures 1 to 3 and Figure 8This invention provides a complete satellite thermal wrapping and rewinding system. The system includes: two sets of intelligent pre-tensioning devices 210 as described in Embodiment 1, two intelligent winding devices 220, two intelligent locking devices 230, a heating system, and a flexible thermal wrapping sheet 260. The intelligent locking devices 230 are configured to lock or release the intelligent winding devices 220, while the intelligent winding devices 220 are configured to wind up or unwind the thermal wrapping sheet 260. The thermal wrapping sheet 260 is configured to completely cover the satellite's heat dissipation surface 101 and all the aforementioned devices, and can be wound up by the intelligent winding devices 220 to expose the heat dissipation surface 101. The heating system (including a power supply, controller, and heating film 240) is used to independently heat the intelligent winding devices 220 and the intelligent locking devices 230 to trigger their shape recovery. The system achieves coordinated operation through unified heating control, realizing an intelligent switch from "launch locking" to "on-orbit deployment." The system structure is simplified, eliminating complex motors and transmission mechanisms, and has high reliability.

[0033] In one embodiment, see Figures 2 to 4 and Figure 8 Two sets of intelligent pre-tightening devices 210 are respectively installed at two corners of one side edge of the heat dissipation surface 101 of the satellite 100, and the roots of two intelligent winding devices 220 are fixed at two corners of the opposite side edge of the heat dissipation surface 101. The roots of two intelligent locking devices 230 are respectively installed on the upper platform 211 of the corresponding intelligent pre-tightening device 210, and the locking end of the intelligent locking device 230 is provided with a locking component 231 (see...). Figure 9 The free end of the intelligent winding device 220 is provided with a matching locking hole 221 (see...). Figure 3 and Figure 4 This achieves a locking mechanism. Finally, the entire heat-shrink wrap 260 is tightly wrapped and adhered to all devices and the heat dissipation surface 101 via the Velcro 250 on its back.

[0034] In this embodiment, the number of each group of intelligent pre-tightening devices 210 can be one or more, such as two, three or four (see [link to documentation]). Figure 3 ).

[0035] In one example, the locking component 231 is embodied as a stainless steel hemisphere (metal locking hemisphere), and the keyhole 221 is machined into a hemispherical recess that matches its curvature (hemispherical keyhole). When locked, the hemisphere is embedded in the recess; when unlocked, the intelligent locking device 230 returns to an L-shape, causing the hemisphere to slide smoothly out of the recess in any direction.

[0036] In this embodiment, the pre-tightening force generated by the intelligent pre-tightening device 210 through thermal deformation is perpendicular to the plane where the satellite heat dissipation surface 101 is located.

[0037] In this embodiment, both the intelligent winding device 220 and the intelligent locking device 230 are made of fiber-reinforced shape memory resin-based composite material.

[0038] See Figures 2 to 5 The intelligent winding device 220 is a retractable rod / plate whose initial shape is a tight spiral (see...). Figure 5 During assembly, the material is heated above its glass transition temperature, softening it. External force is applied to unfold it into a flat state, and then heating is stopped to allow it to regain its stiffness and lock into its shape. One end of the intelligent retraction device 220 is fixed to the satellite's heat dissipation surface 101 with screws, while the other end is free and locked by the intelligent locking device 230 during launch. Its shape remains flat (see [link to product details]). Figure 2 and Figure 3 This keeps the heat-coated 260 in an expanded state.

[0039] See Figure 3 and Figure 9 The intelligent locking device 230 is initially shaped as an L-shaped plate with rounded corners, and is composed of two vertically or nearly vertically arranged plate segments connected by an arc transition section. During assembly, it is heated above its glass transition temperature, softening the material. An external force is applied to unfold it into a flat state, and then heating is stopped to allow its rigidity to be restored and locked in that shape. One end of the intelligent locking device 230 is located above the intelligent pre-tightening device 210 and is fixed to the satellite heat dissipation surface 101 with screws. The other end is the locking end, which presses against the free end of the intelligent retraction device 220 during the launch phase to lock it in place. The intelligent locking device 230 maintains a flat shape (see [reference]). Figure 2 and Figure 3 The intelligent locking device 230 has a simple structure and reliable operation. The rounded transition avoids stress concentration at right-angle bends, improving material fatigue life and operational reliability.

[0040] When the heat-coated 260 needs to be wound up, the intelligent locking device 230 is heated by the heating system to raise its temperature above the glass transition temperature, causing the intelligent locking device 230 to return to its initial shape (see...). Figure 8 and Figure 9 The locking of the intelligent winding device 220 is released. The intelligent winding device 220 is heated by the heating system, causing it to return to its initial shape, which in turn drives the heat-coating 260 to wind up (see...). Figure 8 ).

[0041] See Figure 4 The intelligent winding device 220 is divided into multiple independent heating sections along its length, for example, three sections. The heating part of the heating system consists of multiple heating films 240, which are attached to each heating section of the intelligent winding device 220 and the area to be heated in the intelligent locking device 230 (see [reference]). Figure 9Through program control, the intelligent locking device 230 and the intelligent winding device 220 are heated sequentially at their ends, middle, and root, allowing the winding rod to be wound up segment by segment, starting from the free end. This segmented sequential heating strategy ensures a smooth and orderly winding process, completely eliminating the risks of internal stress conflicts, motion interference, or jamming that may result from simultaneous overall winding.

[0042] In some other embodiments, the heating part of the heating system can be other commonly used heating components, such as alloy heating wire.

[0043] To achieve a more complete wrapping, see one example. Figure 2 and Figure 8 The heat-coating 260 is divided into two functional sections: a fixing section 261, which covers the intelligent locking device 230 and is fixed to it with Velcro 250, without participating in the winding process; and a winding section 262, which covers the intelligent winding device 220, with Velcro 250 on its inner side along the length of the intelligent winding device 220 for bonding. The fixing section 261 ensures that the area of ​​the intelligent locking device 230 is always covered and insulated, and its material does not interfere with the winding action. The winding section 262, on the other hand, can be wound up with the winding rod without interference. This functional zoning design greatly improves the certainty and reliability of the system's operation.

[0044] Example 3 This embodiment describes a control method for a satellite thermal wrapping and rewinding system. First, the intelligent pre-tightening device, the intelligent locking device in a temporarily flat state, and the intelligent rewinding device in a temporarily flat state are assembled at predetermined positions on the satellite's heat dissipation surface. Then, the pre-tightening force is set: the intelligent pre-tightening device 210 is heated with a hot air gun, the screws are tightened to the specified torque and held, and the pre-tightening force is set after cooling. Next, the thermal wrapping 260 is laid out and secured with Velcro 250. After the satellite 100 enters orbit, the following commands are sent: 1) The intelligent locking device 230 is energized and heated through the heating system, causing it to return to an L-shape and unlock; 2) After a 2-second delay, the heating system sequentially energizes and heats each heating segment of the intelligent rewinding device 220, causing the intelligent rewinding device 220 to roll up sequentially, completely rolling up the rewinding segment 262 of the thermal wrapping 260, exposing the heat dissipation surface 101.

[0045] In the preload setting step, after heating and pressurizing the intelligent preload device 210, the pressure is maintained until the surface temperature of the device drops below its glass transition temperature. Only then is the pressure released and the assembly completed. This ensures that the compressive plastic deformation of the intelligent polymer material is fully locked, avoiding material springback due to insufficient cooling, thereby guaranteeing the accuracy and long-term stability of the preload setting.

[0046] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that not every embodiment contains only one independent technical solution, and in the absence of conflict between solutions, the various technical features mentioned in each embodiment can be combined in any way to form other implementation methods that can be understood by those skilled in the art.

[0047] Furthermore, without departing from the scope of the present invention, modifications to the technical solutions described in the foregoing embodiments, or equivalent substitutions of some of the technical features, shall not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A smart pre-tightening device for a satellite locking mechanism, made of a smart polymer composite material, characterized in that: The device is configured to soften during assembly by a controlled first thermal excitation and to produce a preset compressive plastic deformation under applied pressure along its thickness direction. When the first thermal excitation is removed, the compressive plastic deformation is locked by the material, thereby providing a continuous active preload to the locking mechanism assembled therewith to resist vibration loads during the satellite launch phase.

2. The intelligent pre-tightening device according to claim 1, characterized in that: It includes an upper platform, a lower platform, and a support structure connecting the upper platform and the lower platform; The upper platform and the lower platform are arranged at intervals along the thickness direction of the intelligent pre-tightening device, and the thickness direction is parallel to the direction of the pre-tightening force. The support structure is configured to bear pressure in the thickness direction and transmit the pressure to the lower platform, and the support structure is designed such that its lateral deformation rate is less than a preset threshold when it is compressed in the thickness direction. The upper platform is used to support the base of the locking mechanism, and the lower platform is used to be installed on the satellite structure.

3. The intelligent pre-tightening device according to claim 2, characterized in that: The support structure includes two spaced and mirror-symmetrically arranged support plates. Each of the support plates has at least one bend in its height direction, and each of the support plates has a through hole at the bend, which is parallel to the upper and lower platforms, for weight reduction and stress relief. The upper ends of both support plates are integrally connected to the upper platform, and the lower ends are integrally connected to the lower platform, together forming a support frame with low lateral deformation characteristics under vertical load.

4. The intelligent pre-tightening device according to any one of claims 1 to 3, characterized in that: The intelligent polymer composite material is a fiber-reinforced shape memory resin-based composite material.

5. A satellite thermal wrapping and rewinding system, characterized in that, include: Intelligent pretensioning device, intelligent winding device, intelligent locking device, heating system and heat wrapping; The intelligent pretensioning device is the intelligent pretensioning device according to any one of claims 1 to 4; Both the intelligent winding device and the intelligent locking device are made of intelligent polymer composite material and have an initial shape that can be restored by thermal excitation; the intelligent locking device is configured to lock or release the intelligent winding device, and the intelligent winding device is configured to wind or unwind the thermal coating. The thermal wrapping is configured to wrap the satellite heat dissipation surface and the intelligent winding device, intelligent locking device and intelligent pre-tightening device, and can be wound up by the intelligent winding device to expose the satellite heat dissipation surface; The heating system is used to heat the intelligent winding device and the intelligent locking device independently or sequentially to trigger their shape recovery function.

6. The satellite thermal wrapping and rewinding system according to claim 5, characterized in that: The two sets of intelligent pre-tightening devices are respectively installed at two corners on one side of the satellite's heat dissipation surface; The roots of the two intelligent winding devices are assembled to the two corners on the other side of the satellite heat dissipation surface, with the ends of the intelligent winding devices facing the intelligent pre-tightening device; The roots of the two sets of intelligent locking devices are assembled above the intelligent pre-tightening device, and the ends of the intelligent locking devices are provided with locking components. The ends of the intelligent winding device are provided with locking holes that match the locking components. The locking components cooperate with the locking holes to achieve locking. The heat wrapping is connected and wrapped around the intelligent winding device, intelligent locking device, intelligent pre-tightening device, and satellite heat dissipation surface via Velcro.

7. The satellite thermal wrapping and winding system according to claim 6, characterized in that: The locking component is a protruding locking part, and the lock hole is a recess that matches the protruding locking part.

8. The satellite thermal wrapping and rewinding system according to claim 5, characterized in that: The intelligent winding device is rod-shaped or plate-shaped. One end of it is fixed to the satellite heat dissipation surface along its length, and the other end is locked by the intelligent locking device. Along the length of the intelligent winding device, the intelligent winding device is divided into multiple heating sections, and each heating section is heated sequentially by the heating system. The heat coating includes a fixed section fixedly connected to the intelligent locking device, and a take-up section bonded to the intelligent take-up device and capable of being taken up with it.

9. The satellite thermal wrapping and rewinding system according to claim 5, characterized in that: The initial shape of the intelligent locking device is an L-shaped plate with rounded corners, and its whole is composed of two plate segments arranged vertically or nearly vertically connected by a rounded transition section. The temporary shape of the intelligent locking device is straight; In the locked state, the intelligent locking device is maintained in the temporary shape; when unlocked, the intelligent locking device is heated to return it to the initial shape.

10. A control method for a satellite thermal wrapping and winding system, characterized in that, The method, applied to the system according to any one of claims 5 to 9, comprises: System assembly and preload setting steps: The intelligent pre-tightening device, the intelligent locking device in a temporary flat state, and the intelligent winding device in a temporary flat state are assembled at predetermined positions on the satellite heat dissipation surface; The intelligent pre-tightening device is subjected to a first thermal excitation to soften it; Pressure is applied along the thickness direction to the softened intelligent pre-tightening device, causing it to undergo compressive plastic deformation; Stop the first thermal excitation, allow the intelligent pre-tightening device to cool down, lock the compression plastic deformation, thereby providing active pre-tightening force to the intelligent locking device; The heat-shrink wrapping is unfolded and secured to the assembled devices and satellite heat dissipation surfaces using Velcro. On-orbit unlocking and rewinding steps: After the satellite enters orbit, the heating system heats the intelligent locking device, causing it to return to its initial shape, thereby releasing the locking of the intelligent winding device. The intelligent winding device is heated by the heating system, causing it to return to its initial curled shape, thereby winding up the heat-shrinking coating and exposing the satellite's heat dissipation surface. During the system assembly and preload setting steps, the operation of applying pressure to the intelligent preload device continues until the intelligent preload device cools down below its glass transition temperature.

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