Spacecraft-oriented shield-thermal control integrated structure

Abstract

The application belongs to the technical field of spacecraft, and particularly relates to a protective-thermal control integrated structure for spacecraft. The integrated structure is composed of a protected object and an inner shield, a protected object and an outer shield, or a protected object and an inner shield and an outer shield. The inner shield is a multifunctional filling layer structure, which is composed of an outer atomic oxygen protection layer, a reflection layer, a heat insulation layer, a crushing layer, a diffusion layer and an inner atomic oxygen protection layer from outside to inside. The atomic oxygen protection layers on the inner and outer surfaces completely cover each surface of the multifunctional filling layer. The outer shield is made of metal and includes a protective outer shield, a plurality of groups of array-distributed connecting ribs and fluid pipelines. The fluid pipelines are arranged along the direction of the cabin body and are welded to the inner side of the protective outer shield through the connecting ribs. The integrated structure can have both protective and thermal control functions, and the mechanical interfaces in the assembly and disassembly processes can be independent of each other, which greatly improves the structural efficiency and simplifies the complexity of the structure.

Description

Technical Field

[0001] This invention belongs to the field of spacecraft technology, specifically relating to an integrated protection-thermal control structure for spacecraft. Background Technology

[0002] During spacecraft operation, due to the unique and complex space environment, adaptive design is required, including space debris protection and spacecraft temperature control. For space debris protection, simple single-layer or filled protective structures are typically used: a single-layer structure adds a thin metal plate at a certain distance from the spacecraft's main structure to improve its protection against space debris; a filled protective structure is a composite structure consisting of one or more layers of high-strength woven fabric placed between the outermost aluminum shield and the rear wall, generally used in high-risk areas. For spacecraft thermal control, a multi-layered design combining radiators is generally used to effectively ensure that the spacecraft temperature is controlled within specified ranges.

[0003] However, for spacecraft, existing debris protection structures and temperature control devices are usually designed independently and perform their respective functions independently. They do not have the ability to directly combine and install these two structures and functions together. They require additional independent installation structures, such as the device for installing a large-diameter thin-walled structure on a spacecraft described in patent application CN201020624487.8, in order to achieve the two functions of space debris or micrometeorite protection and temperature control. At the same time, the layout of the two structural forms overlaps to some extent, which puts high demands on mechanical interfaces and installation space, and causes great difficulties in structural assembly and disassembly. Summary of the Invention

[0004] In view of this, the present invention provides an integrated protection-thermal control structure for spacecraft. The integrated structure can perform both protection and thermal control functions (at least one of insulation and heat dissipation functions), and the mechanical interfaces can be independent of each other during assembly and disassembly, which greatly improves the structural efficiency and simplifies the complexity of the structure.

[0005] This invention is achieved through the following technical solution:

[0006] An integrated protection-thermal control structure for spacecraft, the integrated structure consisting of a protected object and an inner screen, a protected object and an outer screen, or a protected object, an inner screen, and an outer screen; the protected object is the spacecraft cabin.

[0007] With the side closer to the protected object as the inner side and the side farther from the protected object as the outer side: when the integrated structure consists of the protected object and an inner screen or an outer screen, the inner screen or outer screen can be detachably installed on the outer surface of the spacecraft cabin.

[0008] When the integrated structure consists of the protected object, an inner screen, and an outer screen, the inner screen is detachably mounted on the outer surface of the spacecraft cabin, and the outer screen is detachably mounted on the outer surface of the inner screen.

[0009] The inner screen is a multi-functional filling layer structure, consisting of an atomic oxygen shield, a reflective layer, a heat insulation layer, a fragmentation layer, a diffusion layer, and an atomic oxygen shield, arranged sequentially from the outside to the inside. The atomic oxygen shields on the inner and outer surfaces completely cover each surface of the multi-functional filling layer, achieving fragment protection and heat insulation functions.

[0010] The outer screen is made of metal and includes a protective outer screen, several arrayed connecting ribs and fluid pipelines. The fluid pipelines are arranged along the direction of the cabin and are welded to the inside of the protective outer screen by welding ribs to achieve fragment protection and heat dissipation functions.

[0011] Preferably, in the multifunctional filling layer structure, the atomic oxygen shielding layer material is an atomic oxygen shielding cloth, which is a fiber woven fabric with an atomic oxygen shielding coating on its surface; the reflective layer material is an aluminized polyester film with a surface emissivity of <0.05; the heat insulation layer material is polyester or nylon with a thermal conductivity of <0.05W / (mK); the breakage layer is a fiber fabric with an elastic modulus of >70GPa; and the diffusion layer is a fiber fabric with a strength of >3GPa.

[0012] More preferably, the inner screen fragmentation layer material is ceramic fiber, carbon fiber, or basalt fiber; the diffusion layer fiber fabric is aramid fiber or carbon fiber cloth; according to the space debris protection requirements and weight requirements, the fragmentation layer fiber fabric has 2 to 5 layers, and the diffusion layer fiber fabric has 2 to 5 layers; the outer screen is made of aluminum alloy; aluminum alloy has low density, high strength, rigidity, and good thermal conductivity, which can carry heat away from the heat source.

[0013] Preferably, when the integrated structure consists of the protected object and the inner screen, the inner screen is directly installed on the outer surface of the spacecraft cabin via Velcro or hook-and-loop fasteners.

[0014] Specifically, the outer surface of the spacecraft cabin is bonded with several arrays of first Velcro fasteners or first hooks; the inner surface of the multifunctional filling layer structure is sewn with several arrays of second Velcro fasteners or second hooks. By connecting the first and second Velcro fasteners, or connecting the first and second hooks, the multifunctional filling layer structure can be directly wrapped and fixed to the outer surface of the cabin. When the protection requirements are relatively low or the overall enclosure is limited, the multifunctional filling layer can still achieve protection and thermal insulation functions using the simplified installation method described above. At the same time, the connection via Velcro fasteners or hooks facilitates installation and disassembly, and also reduces the requirements for processing precision.

[0015] Preferably, when the integrated structure consists of the protected object and the inner screen, the inner screen is mounted on the outer surface of the spacecraft cabin via an inner screen mounting base, and a rigid shaping strip for the inner screen is provided between the outer surface of the cabin and the inner screen to support and maintain the shape of the flexible multifunctional filling layer.

[0016] Specifically, several array-distributed mechanical interfaces are pre-reserved on the outer surface of the spacecraft cabin. The lower end of the inner screen mounting base is threaded to the mechanical interfaces. The upper end of the inner screen mounting base is machined with mechanical grooves, and countersunk screws pass through the rigid shaping strip of the inner screen and are threaded to the mechanical grooves. Several array-distributed third nylon fasteners or third nylon hooks are glued to the surface of the rigid shaping strip of the inner screen. Several array-distributed second nylon fasteners or second nylon hooks are sewn onto the inner surface of the multifunctional filling layer structure of the inner screen. By connecting the third nylon fasteners and second nylon fasteners, or connecting the third nylon hooks and second nylon hooks, the multifunctional filling layer structure of the inner screen can be directly covered and fixed to the outer surface of the cabin. Since the inner screen is a flexible structure, it is difficult to fix. The shape of the multifunctional filling layer is supported and maintained by the rigid shaping strip of the inner screen, which greatly reduces the number of connection points required for installation and also allows the inner screen to maintain a certain distance from the cabin, thereby achieving good protection and heat insulation effects.

[0017] Preferably, when the integrated structure consists of the protected object and the outer screen, the outer screen is mounted on the outer surface of the spacecraft cabin via an outer screen mounting base. Specifically, several array-distributed mechanical interfaces are pre-reserved on the outer surface of the spacecraft cabin, and the lower end of the outer screen mounting base is threadedly connected to the mechanical interfaces. The upper end of the outer screen mounting base is machined with mechanical grooves, and screws pass through the outer screen and are threadedly connected to the mechanical grooves, thus covering and fixing the outer screen to the outer surface of the cabin. The protective outer screen protects both the inner fluid pipelines and the outer surface of the spacecraft cabin, reducing the risk of failure due to impact from space debris. The fluid pipelines can transfer heat and radiate heat through the protective outer screen, thereby giving the outer screen both radiative heat dissipation and space debris protection functions.

[0018] Further preferably, the inner and outer surfaces of the outer screen are also provided with heat insulation pads, the heat insulation pads being made of heat insulation material with a thermal conductivity of <0.05W / (mK); due to the good heat insulation performance of the heat insulation pads, heat leakage of the structure is reduced, thereby improving the overall thermal insulation performance of the structure; washers are provided between the heat insulation pads and screws on the outer surface of the outer screen; vibration damping pads are provided between the heat insulation pads and the inner surface of the outer screen; the vibration damping pads are made of rubber material with a damping coefficient >0.1, effectively reducing the vibration and impact loads on the outer screen.

[0019] More preferably, the integrated structure comprises a protected object, an inner screen, and an outer screen, with the inner screen and outer screen connected by an outer screen mounting base. Specifically, the lower end of the outer screen mounting base passes through the inner screen and the rigid shaping strip of the inner screen in sequence, and is threadedly connected to the mechanical groove at the upper end of the outer screen mounting base. A washer is provided between the lower end of the countersunk screw and the outer surface of the inner screen. A mechanical groove is machined at the upper end of the outer screen mounting base, and the screw passes through the washer, the outer surface heat insulation pad of the outer screen, the vibration damping pad, and the inner surface heat insulation pad of the outer screen in sequence, and then connects to the outer screen. The upper end of the base is machined with a mechanical groove thread connection to achieve the installation of the outer screen and the inner screen; the surface of the rigid shaped strip of the inner screen is glued with several arrays of third nylon fasteners or third nylon hooks; the inner surface of the multifunctional filling layer structure of the inner screen is stitched with several arrays of second nylon fasteners or second nylon hooks; the third nylon fasteners and second nylon fasteners are connected, or the third nylon hooks and second nylon hooks are connected, to achieve the installation of the inner screen and the outer surface of the cabin, thus obtaining the integrated protection-thermal control structure.

[0020] Beneficial effects:

[0021] (1) The present invention provides an integrated protection-thermal control structure for spacecraft, which consists of a protected object and an inner screen, a protected object and an outer screen, or a protected object and an inner screen and an outer screen. The integrated structure can have both protection and thermal control functions (at least one of thermal insulation and heat dissipation functions), and the mechanical interfaces can be independent of each other during assembly and disassembly, which greatly improves the structural efficiency and simplifies the complexity of the structure. Compared with the separately designed protection structure and thermal control structure, the present invention reduces the structural weight required to meet the functions and performance, and effectively improves the structural efficiency.

[0022] (2) This invention provides an integrated protection-thermal control structure for spacecraft. The integrated structure consists of a protected object and an inner screen, a protected object and an outer screen, or a protected object, an inner screen, and an outer screen. The inner screen is a multi-functional filling layer structure. It adopts a mixed arrangement of multiple functional structures, which not only plays a role in heat insulation but also provides good protection against space debris. At the same time, the thickness, number of layers, and other parameters of each layer can be designed according to the needs of protection and thermal control, which is highly designable. In addition, the multi-functional filling layer can be used alone for space debris protection and heat insulation of spacecraft structures, or it can be used together with the outer screen to improve the protection performance of the integrated protection-thermal control structure, further increase the heat dissipation capacity, and improve the thermal control effect.

[0023] (3) The present invention provides an integrated protection-thermal control structure for spacecraft. The outer screen of the integrated structure not only serves as a space debris protection function, but also dissipates the heat on the cabin in the form of radiation heat dissipation. The protective outer screen protects the fluid pipelines by placing them on the inside through connecting ribs, thereby improving reliability. By using heat insulation pads and vibration damping pads, the heat leakage of the system is reduced, and the vibration, impact and other loads on the outer screen are also reduced.

[0024] (4) This invention provides an integrated protection-thermal control structure for spacecraft. The integrated protection-thermal control structure decouples the inner screen and the outer screen through the independent design of the lower base for the outer screen mounting, the inner screen mounting base, and the upper base for the outer screen mounting. The two have their own independent mechanical interfaces. When only the inner screen needs to be connected, the inner screen and the protected object are installed through the inner screen mounting base. When only the outer screen needs to be connected, the outer screen and the protected object are installed through the upper base for the outer screen mounting. When the inner screen and the outer screen need to be connected, the design of the lower base for the outer screen mounting, the inner screen mounting base, and the upper base for the outer screen mounting enables detachable installation. This solves the problems of layout conflict and operation difficulty, thereby realizing the serialization and universalization of the product.

[0025] (5) The present invention provides an integrated protection-thermal control structure for spacecraft. The structure integrates nylon hooks or nylon fasteners into the multi-functional filling layer structure of the inner screen, which facilitates engineering installation and disassembly and reduces the requirements for processing precision. At the same time, the inner screen can be directly covered and fixed to the outer surface of the cabin by gluing nylon hooks or nylon fasteners onto the outer surface of the cabin, which is simple to use.

[0026] (6) The present invention provides an integrated protection-thermal control structure for spacecraft. The inner screen of the integrated protection-thermal control structure is a flexible structure and the outer screen is a thin-walled structure, which makes the integrated structure of the present invention have good structural shape adaptability. It can select a planar or curved structure according to actual use needs. The corresponding installation connection points in the integrated structure can also be flexibly set to adapt to different envelope requirements and dynamically adjust the protection and thermal control performance, thereby realizing the serialization and generalization of products and having a wide range of adaptability. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the integrated protection-thermal control structure described in Embodiment 1 of the present invention;

[0028] Figure 2 for Figure 1 Schematic diagram of the inner and outer screen structure;

[0029] Figure 3 for Figure 1 Schematic diagram of the multi-functional filling layer structure of the inner screen;

[0030] Figure 4 This is a schematic diagram of the assembly of the structure described in Embodiment 1 of the present invention;

[0031] Among them, 1-protected object, 2-outer screen, 3-inner screen, 4-lower base for outer screen installation, 5-inner screen installation base, 6-second Velcro fastener, 7-third Velcro fastener, 8-countersunk screw, 9-inner screen shaping strip, 10-washer, 11-upper base for outer screen installation, 12-heat insulation pad, 13-vibration damping pad, 14-screw, 201-protective outer screen, 202-connecting rib, 203-fluid pipeline, 301-anti-atomic layer, 302-reflective layer, 303-heat insulation layer, 304-fracture layer, 305-diffusion layer. Detailed Implementation

[0032] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0033] Example 1

[0034] An integrated protection-thermal control structure for spacecraft as described in this embodiment, such as Figure 1 As shown, the integrated structure consists of the protected object 1, the inner screen 3 and the outer screen 2; with the side closer to the protected object 1 as the inner side and the side farther away from the protected object 1 as the outer side: the inner screen 3 is detachably installed on the outer surface of the spacecraft cabin, and the outer screen 2 is detachably installed on the outer surface of the inner screen 3.

[0035] The protected object 1 is the spacecraft cabin; the inner screen 3 is a multi-functional filling layer structure, as shown in Figure 3, consisting of an atomic oxygen shield 301, a reflective layer 302, a heat insulation layer 303, a fragmentation layer 304, a diffusion layer 305, and an atomic oxygen shield 301 from the outside to the inside; the atomic oxygen shield 301 on the inner and outer surfaces completely covers each surface of the multi-functional filling layer, preventing the inner and outer parts and edges of the multi-functional filling layer structure from being damaged by atomic oxygen;

[0036] In the multifunctional filling layer structure, the atomic oxygen shielding layer material 101 is an atomic oxygen shielding cloth, which is a fiber-woven fabric with an atomic oxygen shielding coating on its surface; the reflective layer 302 is an aluminized polyester film with a surface emissivity of <0.05; the heat insulation layer 303 is polyester or nylon with a thermal conductivity of <0.05W / (mK); the fragmentation layer 304 is 2 to 5 layers of ceramic fiber, carbon fiber, or basalt fiber with an elastic modulus >70GPa, which can generate stronger impact pressure within the incident particles, making them more thoroughly fragmented; the diffusion layer is 2 to 5 layers of aramid fiber or carbon fiber cloth with a strength >3GPa, which can effectively reduce the velocity of residual fragments and the expansion velocity of the fragment cloud.

[0037] The outer screen is made of aluminum alloy, such as Figure 2 As shown, it includes a protective outer screen 201, several sets of arrayed connecting ribs 202 and fluid pipelines 203. The fluid pipelines 203 are arranged along the direction of the cabin and are welded to the inner side of the protective outer screen 201 by welding ribs 202 to achieve fragment protection and heat dissipation functions.

[0038] The schematic diagram of the integrated protection-thermal control structure assembly is shown below. Figure 4 As shown, several array-distributed mechanical interfaces are pre-reserved on the outer surface of the protected object 1. The lower end of the outer screen mounting base 4 is threaded to the mechanical interfaces. The upper end of the outer screen mounting base 4 is machined with a mechanical groove. The lower end of the outer screen mounting upper base 11 passes through the inner screen 3 and the inner screen rigid shaping strip 9 in sequence, and is threaded to the mechanical groove at the upper end of the outer screen mounting base 4. A washer 10 is provided between the lower end of the outer screen mounting upper base 11 and the upper surface of the inner screen 3. The upper end of the outer screen mounting upper base 11 is machined with a mechanical groove, and screws... 14 passes sequentially through the gasket 10, the heat insulation gasket 12 on the outer surface of the outer screen, the vibration damping gasket 13, and the heat insulation gasket 12 on the inner surface of the outer screen, and is connected to the mechanical groove thread processed on the upper end of the mounting base 11 of the outer screen; several arrayed third nylon fasteners 7 are glued to the surface of the rigid shaping strip 9 of the inner screen; several arrayed second nylon fasteners 6 are sewn on the inner surface of the multifunctional filling layer structure of the inner screen; the third nylon fasteners 7 and the second nylon fasteners 6 are connected to achieve the installation of the inner screen 3 and the outer surface of the cabin, thus obtaining the integrated protection-thermal control structure.

[0039] Example 2

[0040] An integrated protection-thermal control structure for spacecraft as described in this embodiment, the integrated structure consists of a protected object 1 and an inner screen 3; with the side closer to the protected object 1 as the inner side and the side farther away from the protected object 1 as the outer side: the inner screen 3 is detachably installed on the outer surface of the spacecraft cabin, and a rigid shaping strip 9 of the inner screen is provided between the outer surface of the cabin and the inner screen 3 to support and maintain the shape of the flexible multifunctional filling layer;

[0041] The protected object 1 is the spacecraft cabin; the inner screen 3 is a multi-functional filling layer structure, as shown in Figure 3, consisting of an atomic oxygen shield 301, a reflective layer 302, a heat insulation layer 303, a fragmentation layer 304, a diffusion layer 305, and an atomic oxygen shield 301 from the outside to the inside; the atomic oxygen shield 301 on the inner and outer surfaces completely covers each surface of the multi-functional filling layer, preventing the inner and outer parts and edges of the multi-functional filling layer structure from being damaged by atomic oxygen;

[0042] Specifically, several array-distributed mechanical interfaces are pre-reserved on the outer surface of the spacecraft cabin. The lower end of the inner screen mounting base 5 is threaded to the mechanical interface. The upper end of the inner screen mounting base 5 is machined with a mechanical groove, and the countersunk screw 8 passes through the rigid shaping strip 9 of the inner screen and is threaded to the mechanical groove. Several array-distributed third nylon fasteners 7 are glued to the surface of the rigid shaping strip 9 of the inner screen. Several array-distributed second nylon fasteners 6 are sewn onto the inner surface of the multifunctional filling layer structure of the inner screen. By connecting the third nylon fasteners 7 and the second nylon fasteners 6, the multifunctional filling layer structure of the inner screen 3 can be directly covered and fixed to the outer surface of the cabin. Since the inner screen 3 is a flexible structure, it is difficult to fix. The shape of the multifunctional filling layer is supported and maintained by the rigid shaping strip 9 of the inner screen, which greatly reduces the number of connection points required for installation and also allows the inner screen 3 to maintain a certain distance from the cabin, thereby achieving good protection and heat insulation effects.

[0043] Example 3

[0044] An integrated protection-thermal control structure for spacecraft as described in this embodiment, the integrated structure consists of a protected object 1 and an inner screen 3; with the side closer to the protected object 1 as the inner side and the side farther from the protected object 1 as the outer side: the inner screen 3 is detachably installed on the outer surface of the spacecraft cabin.

[0045] The protected object 1 is the spacecraft cabin; the inner screen 3 is a multi-functional filling layer structure, as shown in Figure 3, consisting of an atomic oxygen shield 301, a reflective layer 302, a heat insulation layer 303, a fragmentation layer 304, a diffusion layer 305, and an atomic oxygen shield 301 from the outside to the inside; the atomic oxygen shield 301 on the inner and outer surfaces completely covers each surface of the multi-functional filling layer, preventing the inner and outer parts and edges of the multi-functional filling layer structure from being damaged by atomic oxygen;

[0046] The outer surface of the spacecraft cabin is bonded with several arrays of first Velcro fasteners; the inner surface of the multifunctional filling layer structure is sewn with several arrays of second Velcro fasteners 6; by connecting the first and second Velcro fasteners 6, the multifunctional filling layer structure can be directly wrapped and fixed to the outer surface of the cabin; when the protection requirements are relatively low or the overall enclosure is limited, the multifunctional filling layer can also achieve protection and thermal insulation functions by adopting the simplified installation method described above; at the same time, the Velcro fasteners facilitate installation and disassembly, and also reduce the requirements for processing precision.

[0047] Example 4

[0048] An integrated protection-thermal control structure for spacecraft as described in this embodiment, the integrated structure consists of a protected object 1 and an outer screen 2; with the side closer to the protected object 1 as the inner side and the side farther from the protected object 1 as the outer side: the outer screen 2 is detachably installed on the outer surface of the spacecraft cabin.

[0049] The outer screen 2 is made of aluminum alloy and includes a protective outer screen 201, several arrayed connecting ribs 202, and fluid pipes 203. The fluid pipes 203 are arranged along the direction of the cabin and are welded to the inner side of the protective outer screen 201 by the welding ribs 202 to achieve fragment protection and heat dissipation. The inner and outer surfaces of the outer screen 2 are also provided with heat insulation pads 12. The heat insulation pads 12 are made of heat insulation material with a thermal conductivity of <0.05W / (mK). Due to the good heat insulation performance of the heat insulation pads 12, the heat leakage of the structure is reduced, thereby improving the overall thermal insulation performance of the structure. A washer 10 is provided between the heat insulation pads 12 and screws 14 on the outer surface of the outer screen. A vibration damping pad 13 is provided between the heat insulation pads 12 on the inner surface of the outer screen 2 and the inner surface of the outer screen. The vibration damping pad 13 is made of rubber material with a damping coefficient >0.1, which effectively reduces the vibration and impact loads on the outer screen.

[0050] Specifically, several array-distributed mechanical interfaces are reserved on the outer surface of the spacecraft cabin. The lower end of the outer screen mounting base 11 is threaded to the mechanical interfaces. The upper end of the outer screen mounting base 11 is machined with mechanical grooves. Screws 14 pass through washers 10, heat insulation pads 12 on the outer surface of the outer screen, vibration damping pads 13, and heat insulation pads 12 on the inner surface of the outer screen in sequence, and connect to the several array-distributed mechanical interfaces reserved on the outer surface of the spacecraft cabin, thus covering and fixing the outer screen to the outer surface of the cabin. The protective outer screen 201 protects both the inner fluid pipeline 203 and the outer surface of the spacecraft cabin, reducing the risk of failure caused by space debris impact. The fluid pipeline 203 can transfer heat and radiate heat through the protective outer screen 201, so that the outer screen 2 has both radiative heat dissipation and space debris protection functions. The integrated structure provides good protection and heat dissipation.

[0051] Working principle:

[0052] When space debris or micrometeoroids impact, they first come into contact with the outer screen 2. After being fully broken up by the outer screen 201, the debris or micrometeoroids will come into contact with the inner screen 3. The inner screen 3 is a multi-functional filling layer structure. Through the layering design and material selection of the multi-functional filling layer, it not only has the function of debris protection, but also heat insulation, heat preservation, and isolation from atomic oxygen and other space environments. It can further break up, disperse, slow down, and even vaporize the broken debris, effectively protecting the spacecraft structure. All components of the outer screen are made of aluminum alloy, which has good thermal conductivity. The structural design of the fluid pipeline 203 can also transfer heat, which is then transmitted through the outer screen 201. The outer screen provides radiative heat dissipation, thus achieving a thermal control effect. Furthermore, the heat-insulating pads 12 on the inner and outer surfaces of the outer screen 2 have excellent heat insulation properties, reducing structural heat leakage. The outer screen also enhances the overall thermal insulation performance. Therefore, the combined use of the inner and outer screens further improves the protective and thermal control performance of the integrated protection-thermal control structure, providing both insulation and heat dissipation capabilities. Since the probability of being impacted twice at the same location is extremely low, repairs are unnecessary after an impact. Even if repairs are required, simply attaching an aluminum plate to the impacted area of ​​the protective outer screen 201 to fill the impact dent simplifies on-orbit maintenance of the integrated structure.

[0053] Furthermore, since the inner screen of the integrated protection-thermal control structure of the present invention is a flexible structure and the outer screen is a thin-walled structure, the integrated structure of the present invention has good structural shape adaptability and can select a planar or curved structure according to actual use needs. Correspondingly, the installation connection points in the integrated structure can also be flexibly set, which has a wide range of adaptability.

[0054] In summary, the above are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An integrated protection-thermal control structure for spacecraft, characterized in that: The integrated structure consists of the protected object and an inner screen, the protected object and an outer screen, or the protected object, an inner screen, and an outer screen; the protected object is the spacecraft cabin. With the side closer to the protected object as the inner side and the side farther from the protected object as the outer side: when the integrated structure consists of the protected object and an inner screen or an outer screen, the inner screen or outer screen can be detachably installed on the outer surface of the spacecraft cabin. When the integrated structure consists of the protected object, an inner screen, and an outer screen, the inner screen is detachably mounted on the outer surface of the spacecraft cabin, and the outer screen is detachably mounted on the outer surface of the inner screen. The inner screen is a multi-functional filling layer structure, consisting of an atomic oxygen shield, a reflective layer, a heat insulation layer, a fragmentation layer, a diffusion layer, and an atomic oxygen shield, arranged sequentially from the outside to the inside. The atomic oxygen shields on the inner and outer surfaces completely cover each surface of the multi-functional filling layer, achieving fragment protection and heat insulation functions. The outer screen is made of metal and includes a protective outer screen, several sets of arrayed connecting ribs and fluid pipelines. The fluid pipelines are arranged along the direction of the cabin and are welded to the inside of the protective outer screen by welding ribs to achieve fragment protection and heat dissipation functions. In the multifunctional filling layer structure, the atomic oxygen shielding layer material is atomic oxygen shielding cloth, which is a fiber woven fabric with an atomic oxygen shielding coating on its surface; the reflective layer material is an aluminum-coated polyester film with a surface emissivity of <0.05; the heat insulation layer material is polyester or nylon with a thermal conductivity of <0.05W / (mK); the breakage layer is a fiber fabric with an elastic modulus of >70GPa; and the diffusion layer is a fiber fabric with a strength of >3GPa.

2. The integrated protection-thermal control structure for spacecraft according to claim 1, characterized in that: The inner screen fragmentation layer material is ceramic fiber, carbon fiber, or basalt fiber; the diffusion layer fiber fabric is aramid fiber or carbon fiber cloth; depending on the space debris protection requirements and weight requirements, the fragmentation layer fiber fabric has 2 to 5 layers, and the diffusion layer fiber fabric has 2 to 5 layers; the outer screen is made of aluminum alloy. Aluminum alloys have low density, high strength, rigidity and good thermal conductivity, which can carry heat away from the heat source.

3. The integrated protection-thermal control structure for spacecraft according to claim 1, characterized in that: When the integrated structure consists of the protected object and the inner screen, the inner screen is directly installed on the outer surface of the spacecraft cabin via Velcro or hook-and-loop fasteners. The outer surface of the spacecraft cabin is bonded with several arrays of first Velcro fasteners or first Velcro hooks; the inner surface of the multifunctional filling layer structure of the inner screen is sewn with several arrays of second Velcro fasteners or second Velcro hooks; the first Velcro fasteners and second Velcro fasteners are connected, or the first Velcro hooks and second Velcro hooks are connected, so that the multifunctional filling layer structure is directly covered and fixed to the outer surface of the cabin.

4. The integrated protection-thermal control structure for spacecraft according to claim 1, characterized in that: When the integrated structure consists of the protected object and the inner screen, the inner screen is mounted on the outer surface of the spacecraft cabin via the inner screen mounting base, and a rigid shaping strip for the inner screen is set between the outer surface of the cabin and the inner screen. Several array-distributed mechanical interfaces are pre-reserved on the outer surface of the spacecraft cabin. The lower end of the inner screen mounting base is threaded to the mechanical interfaces. The upper end of the inner screen mounting base is machined with mechanical grooves. Countersunk screws pass through the rigid shaping strip of the inner screen and are threaded to the mechanical grooves. Several array-distributed third nylon fasteners or third nylon hooks are glued to the surface of the rigid shaping strip of the inner screen. Several array-distributed second nylon fasteners or second nylon hooks are sewn onto the inner surface of the multifunctional filling layer structure of the inner screen. The third nylon fasteners and second nylon fasteners are connected, or the third nylon hooks and second nylon hooks are connected, so that the multifunctional filling layer structure of the inner screen is directly covered and fixed to the outer surface of the cabin.

5. The integrated protection-thermal control structure for spacecraft according to claim 1, characterized in that: When the integrated structure consists of the protected object and the outer screen, the outer screen is mounted on the outer surface of the spacecraft cabin via an outer screen mounting base; Several array-distributed mechanical interfaces are reserved on the outer surface of the spacecraft cabin. The lower end of the outer screen mounting base is threaded to the mechanical interface. The upper end of the outer screen mounting base is machined with a mechanical groove. Screws pass through the outer screen and are threaded to the mechanical groove to cover and fix the outer screen to the outer surface of the cabin.

6. The integrated protection-thermal control structure for spacecraft according to claim 5, characterized in that: The inner and outer surfaces of the outer screen are also provided with heat insulation pads, the heat insulation pads are made of heat insulation material with a thermal conductivity of <0.05W / (mK); a washer is provided between the heat insulation pad and the screw on the outer surface of the outer screen; a vibration damping pad is provided between the heat insulation pad and the inner surface of the outer screen; the vibration damping pad is made of rubber material with a damping coefficient >0.

1.

7. The integrated protection-thermal control structure for spacecraft according to claim 1, characterized in that: The integrated structure consists of the protected object, an inner screen, and an outer screen. The inner screen and the outer screen are connected by an outer screen mounting base. The lower end of the outer screen mounting base passes through the inner screen and its rigid shaping strip, and is threaded into a mechanical groove on the upper end of the outer screen mounting base. A washer is provided between the lower end of the countersunk screw and the outer surface of the inner screen. The upper end of the outer screen mounting base has a machined mechanical groove, and the screw passes through the washer, the outer surface heat insulation pad of the outer screen, the vibration damping pad, and the inner surface heat insulation pad of the outer screen, and is connected to the outer screen mounting base. The upper end of the seat is machined with a mechanical groove thread connection to realize the installation of the outer screen and the inner screen; the surface of the rigid shaped strip of the inner screen is glued with several arrays of third nylon fasteners or third nylon hooks; the inner surface of the multifunctional filling layer structure of the inner screen is stitched with several arrays of second nylon fasteners or second nylon hooks; the third nylon fasteners and second nylon fasteners are connected, or the third nylon hooks and second nylon hooks are connected, to realize the installation of the inner screen and the outer surface of the cabin, thus obtaining the integrated protection-thermal control structure.

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