Carbon fiber thermal protection system and method suitable for spacecraft

Abstract

The invention discloses a carbon fiber thermal protection system and method suitable for a spacecraft, and belongs to the technical field of aerospace thermal protection, the carbon fiber thermal protection system is characterized in that the carbon fiber main body structure is unique, the mechanical property is enhanced, the thermal protection performance is outstanding through a heat reflection coating, the temperature can be controlled to guarantee equipment operation, the protection for cosmic radiation is good, and the shielding efficiency is not lower than 70%; the carbon fiber material is good in performance index, the thermal protection system is appropriate in size and weight and high in edge sealing performance, stability is guaranteed, the thermal protection system adapts to different spacecraft task environments and is high in reliability, the thermal protection performance can still reach the standard after repeated use, maintenance cost is reduced, safety and use efficiency are improved, and aerospace development is promoted. Related technical concepts can also provide references for aviation and other fields to promote technical progress.

Description

Technical Field

[0001] The present invention belongs to the technical field of aerospace thermal protection, and in particular relates to a carbon fiber thermal protection system and method suitable for spacecraft. Background Art

[0002] With the continuous development of aerospace technology, spacecraft are facing increasingly complex and severe flight environment challenges. During the flight of a spacecraft, it will experience a variety of extreme temperature changes. For example, when a spacecraft enters the atmosphere, due to air friction and other reasons, the outer surface of the spacecraft will heat up sharply. If effective thermal protection measures are not taken, excessive temperature will cause serious damage to the internal equipment and structure of the spacecraft, affecting its safety and normal operation. In the extremely low temperature environment of outer space, the spacecraft needs to prevent excessive internal heat loss to maintain a suitable internal temperature and ensure the normal operation of electronic equipment. At the same time, there is a large amount of radiation in the universe, such as cosmic rays. These radiations will cause harm to the electronic equipment inside the spacecraft and possible astronauts, requiring effective shielding measures. Moreover, the spacecraft has strict restrictions on its own weight and space. The thermal protection system must not only meet good thermal protection performance, but also control weight and thickness to ensure that the spacecraft can successfully complete its flight mission.

[0003] In the existing thermal protection technology, traditional thermal protection materials and methods may have deficiencies in certain performance aspects. For example, some materials may not be able to simultaneously meet the requirements of high strength, high heat resistance, good heat reflection, and adaptability to weight and space limitations. Therefore, it is crucial to develop a new type of thermal protection system suitable for spacecraft. The carbon fiber thermal protection system in this case came into being in this context, aiming to solve the thermal protection problem of spacecraft in different flight environments and ensure the safe and stable operation of spacecraft as well as the safety of internal equipment and personnel. Summary of the invention

[0004] The object of the present invention is to provide a carbon fiber thermal protection system and method suitable for spacecraft to solve the problems raised in the above background technology.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: A carbon fiber thermal protection system suitable for spacecraft, characterized in that it comprises a carbon fiber main structure, wherein the carbon fiber main structure is composited by multiple layers of carbon fiber materials, wherein the weaving directions of each layer of carbon fiber are staggered at a specific angle, and the structure can effectively enhance its mechanical properties and thermal protection performance.

[0006] Preferably, the innermost layer of the carbon fiber main structure is in direct contact with the outer surface of the spacecraft and is connected by a special adhesive with good high temperature resistance and bonding properties, and the adhesive can maintain a stable bonding state within the temperature range of -100 degrees Celsius to 500 degrees Celsius.

[0007] Preferably, it also includes a heat reflective coating arranged on the outer layer of the carbon fiber main structure, wherein the heat reflective coating is made of a material with high reflectivity and can reflect most of the external heat, and its reflectivity of thermal radiation in a specific wavelength range is not less than 80%.

[0008] Preferably, the carbon fiber material in the carbon fiber thermal protection system has a tensile strength of not less than 3500 MPa, an elastic modulus of 200 to 300 GPa, and a strength retention rate of not less than 80% at a temperature of up to 1500 degrees Celsius. The carbon fiber material has good thermal shock resistance, and after 50 rapid cooling and heating cycles from room temperature to 1200 degrees Celsius, the carbon fiber main structure has no obvious cracks or damage.

[0009] Preferably, the total thickness of the carbon fiber thermal protection system is between 5 and 15 mm, and its weight should be controlled within 5 kg per square meter to meet the weight and space restrictions of the spacecraft, while ensuring the stability of the thermal protection system during the flight of the spacecraft. The edge of the carbon fiber thermal protection system should be specially sealed, and the bonding strength between the sealing material and the carbon fiber main structure and the outer surface of the spacecraft should be no less than 50 Newtons / mm2 to prevent external gases and impurities from entering the thermal protection system during flight.

[0010] Preferably, first, according to the shape and size of the spacecraft, a suitable carbon fiber main structure (1) is designed and prepared to ensure that the weaving and composite processes of each layer of carbon fiber meet the requirements and the performance of the carbon fiber material is fully utilized.

[0011] 2. The prepared carbon fiber main structure is glued to the outer surface of the spacecraft with a special adhesive. During the gluing process, the adhesive must be evenly distributed and the pressure applied must be between 100 and 200 Pascals to ensure a firm bond.

[0012] 3. Spray heat-reflective coating on the outer layer of the carbon fiber main structure. The spraying process must ensure that the uniformity and thickness of the coating are within the specified range, and the coating thickness error does not exceed 5 microns.

[0013] 4. Carry out comprehensive inspection and debugging of the installed carbon fiber thermal protection system to ensure that its thermal protection performance and various indicators meet the design requirements.

[0014] Preferably, when the spacecraft enters the atmosphere, the carbon fiber thermal protection system can increase the temperature of the outer surface of the spacecraft by no more than 300 degrees Celsius within 3 minutes to ensure the safety and normal operation of the internal equipment and structures of the spacecraft. In the extremely low temperature environment of outer space, the carbon fiber thermal protection system can effectively prevent the loss of heat inside the spacecraft, so that the internal temperature of the spacecraft drops by no more than 10 degrees Celsius within 1 hour. The shielding efficiency of the carbon fiber thermal protection system against cosmic radiation is not less than 70%, so as to reduce the harm of cosmic radiation to the electronic equipment inside the spacecraft and astronauts (if any).

[0015] Preferably, the carbon fiber thermal protection system can adapt to the flight missions and environmental requirements of different types of spacecraft, and can play a normal thermal protection role regardless of low-Earth orbit flight or deep space exploration mission, and the difference in thermal protection performance in different missions does not exceed 10%. The reliability of the carbon fiber thermal protection system is not less than 95% during the entire service life of the spacecraft, and after 20 spacecraft launches, flights and returns, the thermal protection performance can still meet the design requirements without large-scale maintenance and replacement.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] First of all, in terms of mechanical properties and thermal protection performance, its carbon fiber main structure is made of multiple layers of carbon fiber materials woven and composited at a specific angle, which effectively enhances the mechanical properties and can better withstand various external forces that the spacecraft may encounter during flight. At the same time, the thermal protection performance is outstanding, and the heat reflective coating can reflect most of the external heat. When the spacecraft enters the atmosphere, the outer surface temperature can be increased by no more than 300 degrees Celsius within 3 minutes, ensuring the safe operation of internal equipment and structures. In the low temperature environment of the universe, it can also prevent internal heat loss, and the internal temperature drops by no more than 10 degrees within 1 hour. degrees Celsius, maintaining a suitable temperature environment inside the spacecraft to ensure the normal operation of electronic equipment, etc. Secondly, it has a good protection effect on cosmic radiation. The system's shielding efficiency for cosmic radiation is not less than 70%, which can effectively reduce the harm of cosmic radiation to electronic equipment and astronauts (if any) inside the spacecraft, providing an important guarantee for the safety inside the spacecraft. Furthermore, it performs well in adapting to the requirements of spacecraft. Its carbon fiber material has good performance indicators, with a tensile strength of not less than 3500 MPa and an elastic modulus of 200 to 300 GPa. It also has a high strength retention rate at high temperatures and good thermal shock resistance. At the same time, the thermal The total thickness of the protection system is between 5 and 15 mm, and the weight is controlled within 5 kg per square meter, which meets the strict restrictions on weight and space of the spacecraft, ensuring that the spacecraft can successfully complete the flight mission. Moreover, the edge sealing treatment makes the bonding strength between the sealing material and the carbon fiber main structure and the outer surface of the spacecraft not less than 50 Newtons / mm2, preventing external gases and impurities from entering the thermal protection system, and ensuring the stability and reliability of the system. Finally, from the perspective of overall application, the carbon fiber thermal protection system can adapt to the flight missions and environmental requirements of different types of spacecraft. Whether it is low-Earth orbit flight or deep space exploration mission, it can play a normal role in thermal protection, and the difference in thermal protection performance does not exceed 10%. During the entire service life of the spacecraft, the reliability is not less than 95%. After 20 spacecraft launches, flights and returns, the thermal protection performance can still meet the design requirements without large-scale maintenance and replacement, which greatly reduces the maintenance cost and improves the efficiency and safety of the spacecraft. It is of great significance to promote the development of the aerospace industry. In actual production and life, its related technologies and concepts may also provide reference and inspiration for other fields such as aviation and high-end manufacturing, and promote technological progress in related industries. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the present invention;

[0019] In the figure: 1. Carbon fiber main structure; 2. Spacecraft outer surface; 3. Special adhesive; 4. Heat reflective coating. DETAILED DESCRIPTION

[0020] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0021] See also Figure 1 The present invention provides a carbon fiber thermal protection system suitable for spacecraft, comprising a carbon fiber main structure 1, wherein the carbon fiber main structure 1 is composited with multiple layers of carbon fiber materials, wherein the weaving directions of the carbon fiber layers are staggered at a specific angle, and the structure can effectively enhance its mechanical properties and thermal protection properties.

[0022] Furthermore, the carbon fiber main structure is made of multiple layers of carbon fiber materials interlaced and woven at a specific angle. This design has significant advantages in mechanical properties. This interlaced woven structure is like a complex and strong spider web, with each layer of carbon fiber supporting and reinforcing each other. During the flight of the spacecraft, it will be subject to various external forces, such as aerodynamics and vibration. This structure can better disperse and withstand these external forces, and its mechanical properties have been greatly improved compared to traditional single structural materials. For example, when a spacecraft encounters the impact of airflow during high-speed flight, this enhanced mechanical property can ensure that the carbon fiber main structure will not be easily deformed or damaged, thereby protecting the overall structural integrity of the spacecraft. At the same time, this unique structure also plays an important role in thermal protection performance. The interlaced weaving of multiple layers of carbon fiber causes heat to pass through a complex path during conduction, increasing thermal resistance and effectively reducing the transfer of heat to the interior of the spacecraft. Just like in the cold winter, people wear multiple layers of clothing to keep warm, the multi-layer carbon fiber structure can better block the intrusion of external heat, providing a reliable thermal protection barrier for the internal equipment and structure of the spacecraft, and ensuring the safe operation of the spacecraft in a complex flight environment.

[0023] In this embodiment, the innermost layer of the carbon fiber main structure 1 is in direct contact with the outer surface 2 of the spacecraft, and is connected by a special adhesive 3 with good high temperature resistance and bonding properties. The adhesive 3 can maintain a stable bonding state within the temperature range of -100 degrees Celsius to 500 degrees Celsius.

[0024] Furthermore, the innermost layer of the carbon fiber main structure is connected to the outer surface of the spacecraft through a special adhesive with good high temperature resistance and bonding properties. This design has many important significances. First, from the perspective of bonding stability, the adhesive can maintain a stable bonding state in the range of -100 degrees Celsius to 500 degrees Celsius. During the flight of the spacecraft, it will experience extreme temperature changes, from the extremely low temperature in space to the high temperature generated by air friction when entering the atmosphere. This stable bonding performance in a wide temperature range ensures that the carbon fiber main structure is always firmly attached to the outer surface of the spacecraft. For example, when a spacecraft is flying in space, it may encounter an extremely low temperature environment. If the adhesive cannot maintain good bonding at low temperatures, the carbon fiber main structure may separate from the outer surface of the spacecraft, thereby losing its thermal protection effect. When the spacecraft enters the atmosphere, the adhesive can still maintain stable bonding in a high temperature environment, allowing the carbon fiber thermal protection system to continue to function and protect the internal equipment and structure of the spacecraft. Secondly, good bonding performance also helps to transfer and disperse heat. When the temperature of the outer surface of the spacecraft rises, the adhesive can help to evenly conduct the heat to the carbon fiber main structure to a certain extent, and further disperse the heat through its multi-layer staggered structure, reducing the risk of local overheating on the outer surface of the spacecraft. Moreover, the use of this special adhesive makes the installation of the carbon fiber main structure easier and more reliable, improving the overall assembly efficiency and quality of the spacecraft thermal protection system.

[0025] In this embodiment, a heat reflective coating 4 is also included on the outer layer of the carbon fiber main structure 1. The heat reflective coating 4 is made of a material with high reflectivity and can reflect most of the external heat. Its reflectivity for thermal radiation in a specific wavelength range is not less than 80%.

[0026] Furthermore, when the spacecraft enters the atmosphere or is exposed to external heat sources such as solar radiation, the heat reflective coating acts like a mirror, reflecting a large amount of heat back to the outside space. Taking the spacecraft entering the atmosphere as an example, when the air friction causes the temperature of the outer surface of the spacecraft to rise sharply, the heat reflective coating can quickly reflect most of the heat, effectively reducing the rate of heat transfer to the inside of the carbon fiber main structure and the inside of the spacecraft. This is like people wearing white clothes in the hot summer, because white has a higher reflectivity to sunlight, so it feels relatively cool. For spacecraft, this heat reflection function greatly reduces the burden of the internal thermal protection system, allowing the internal equipment and structure of the spacecraft to operate in a relatively low temperature environment. Moreover, the reflectivity of the heat reflective coating for thermal radiation in a specific wavelength range is not less than 80%, which means that it can efficiently reflect the main thermal radiation sources faced by the spacecraft during flight. For example, the specific wavelength thermal radiation in solar radiation is one of the main sources of heat for spacecraft in space. The heat reflective coating can effectively reflect these thermal radiations, reduce the heat absorbed by the spacecraft, and maintain the stability of the internal temperature. In addition, the heat reflective coating can also cooperate with the carbon fiber main structure to further improve the performance of the entire thermal protection system. The carbon fiber main structure itself has a certain thermal protection capability, while the heat-reflective coating forms the first line of defense on the outside, reflecting a large amount of heat. The two work synergistically to provide more comprehensive and reliable thermal protection for the spacecraft.

[0027] In this embodiment, the carbon fiber material in the carbon fiber thermal protection system has a tensile strength of not less than 3500 MPa, an elastic modulus of 200 to 300 GPa, and a strength retention rate of not less than 80% at a temperature of up to 1500 degrees Celsius. The carbon fiber material has good thermal shock resistance. After 50 rapid cooling and heating cycles from room temperature to 1200 degrees Celsius, the carbon fiber main structure 1 has no obvious cracks or damage.

[0028] Furthermore, firstly, the high tensile strength of not less than 3500 MPa enables carbon fiber materials to withstand huge tension and stress during the flight of spacecraft. For example, when the spacecraft is accelerating, turning or encountering airflow impact, the carbon fiber material will not be easily broken or damaged due to the action of external forces. This is like the steel bars in a building, which provide strong support for the entire structure. In the actual operation of the spacecraft, this high tensile strength can ensure that the carbon fiber thermal protection system maintains structural integrity under various complex mechanical environments. Secondly, the elastic modulus is in the range of 200 to 300 GPa, which means that the carbon fiber material has good stiffness and elastic properties. When the spacecraft is subjected to external pressure or vibration, the carbon fiber material can undergo elastic deformation to a certain extent, and then quickly return to its original state without permanent deformation. This characteristic helps to absorb and buffer external impact forces and protect the internal equipment and structures of the spacecraft from damage. At the same time, when the temperature is as high as 1500 degrees Celsius, the strength retention rate of carbon fiber materials is not less than 80%, and it has good thermal shock resistance. After experiencing 50 rapid cooling and heating cycles from room temperature to 1200 degrees Celsius, the main structure of the carbon fiber has no obvious cracks and damage. This is crucial for the operation of spacecraft in extreme temperature environments. When a spacecraft enters the atmosphere, the temperature of the outer surface will rise sharply, and when it returns to the low temperature environment of outer space, it will cool down rapidly. These characteristics of carbon fiber materials enable it to maintain high strength and stability in such drastic temperature changes, and will not crack due to thermal expansion and contraction, thereby continuously and effectively providing thermal protection for spacecraft and ensuring the safety of equipment and personnel inside the spacecraft.

[0029] In this embodiment, the total thickness of the carbon fiber thermal protection system is between 5 and 15 mm, and its weight should be controlled within 5 kg per square meter to meet the spacecraft's restrictions on weight and space, while ensuring the stability of the thermal protection system during the spacecraft's flight. The edge of the carbon fiber thermal protection system should be specially sealed, and the bonding strength between the sealing material and the carbon fiber main structure 1 and the outer surface 2 of the spacecraft should be no less than 50 Newtons / mm2 to prevent external gases and impurities from entering the thermal protection system during flight.

[0030] Furthermore, firstly, the total thickness of the thermal protection system is controlled between 5 and 15 mm, and the weight is controlled within 5 kg per square meter, which fully takes into account the strict restrictions on weight and space of the spacecraft. The launch and operation of the spacecraft requires a lot of energy. An overweight thermal protection system will increase the load of the spacecraft, resulting in an increase in the launch cost and affecting the flight performance and control flexibility of the spacecraft. By controlling the thickness and weight of the thermal protection system within a reasonable range, it is like "slimming down" the spacecraft, enabling it to complete the flight mission more efficiently. For example, during the orbit adjustment and attitude control of the spacecraft, a lighter thermal protection system can reduce the spacecraft's demand for propellant and improve the energy efficiency of the spacecraft. At the same time, the appropriate thickness can also ensure that the thermal protection system provides sufficient thermal protection for the spacecraft without taking up too much space. Secondly, the edge of the carbon fiber thermal protection system is specially sealed, and the bonding strength between the sealing material and the carbon fiber main structure and the outer surface of the spacecraft is not less than 50 Newtons / mm2, which is crucial to ensure the stability and reliability of the thermal protection system. During the flight of the spacecraft, it will face various harsh environments, such as cosmic dust, micro-meteorite particles, etc. If the edges of the thermal protection system are not tightly sealed, these external substances may enter the thermal protection system and damage its structure and performance. However, through high-strength sealing treatment, the invasion of external gases and impurities can be effectively prevented, and the cleanliness and stability of the thermal protection system can be kept. Just like installing well-sealed doors and windows in a house, it can block the entry of wind, rain and dust, ensuring the comfort and safety of the indoor environment. For spacecraft, this sealing treatment can ensure that the thermal protection system always maintains good performance throughout the flight, extend its service life, and provide solid protection for the safe flight of the spacecraft.

[0031] In this embodiment, a carbon fiber thermal protection method suitable for a spacecraft includes the following steps:

[0032] 1. According to the shape and size of the spacecraft, design and prepare a suitable carbon fiber main structure1, ensure that the weaving and composite process of each layer of carbon fiber meets the requirements, so that the performance of the carbon fiber material can be fully utilized.

[0033] 2. The prepared carbon fiber main structure 1 is pasted to the outer surface 2 of the spacecraft through a special adhesive 3. During the pasting process, the adhesive 3 must be evenly distributed and the pressure applied must be between 100 and 200 Pascals to ensure a firm pasting.

[0034] 3. Spraying a heat reflective coating 4 on the outer layer of the carbon fiber main structure 1. The spraying process must ensure that the uniformity and thickness of the coating are within a specified range, and the coating thickness error does not exceed 5 microns.

[0035] 4. Carry out comprehensive inspection and debugging of the installed carbon fiber thermal protection system to ensure that its thermal protection performance and various indicators meet the design requirements.

[0036] Furthermore, first of all, according to the shape and size of the spacecraft, a suitable carbon fiber main structure is designed and prepared. This step ensures that the thermal protection system can be perfectly adapted to the spacecraft. Different types of spacecraft have different appearances and structural characteristics. Through precise design and preparation, the carbon fiber main structure can fully fit the outer surface of the spacecraft and maximize the thermal protection performance. Just like tailoring a piece of clothing for a person, only the right size and style can make it comfortable and beautiful. During the flight of the spacecraft, the tightly fitted carbon fiber main structure can effectively block the intrusion of external heat and the loss of internal heat, providing comprehensive thermal protection for the spacecraft. At the same time, ensure that the weaving and composite process of each layer of carbon fiber meets the requirements so that the performance of the carbon fiber material can be fully utilized. This fine process control can ensure that the mechanical properties and thermal protection performance of the carbon fiber main structure are in the best state. For example, the layers of carbon fiber woven at a specific angle work together to enhance the overall strength and toughness, and can better withstand various stresses and impacts during the flight of the spacecraft. Secondly, when the prepared carbon fiber main structure is pasted to the outer surface of the spacecraft through a special adhesive, it is crucial to ensure that the adhesive is evenly distributed and a pressure of 100 to 200 Pascals is applied to ensure that the adhesion is firm. The evenly distributed adhesive can form a uniform bonding force between the carbon fiber main structure and the outer surface of the spacecraft to avoid the situation of local weak bonding. The appropriate pressure application helps the adhesive to fully fill the tiny gap between the two, further enhancing the bonding effect. Just like when pasting tiles, it is necessary to evenly apply glue and apply appropriate pressure to make the tiles firmly adhere to the ground. During the flight of the spacecraft, the firm adhesion can ensure that the carbon fiber main structure will not fall off easily under various mechanical and thermal environments, and always provide stable thermal protection for the spacecraft. Furthermore, when spraying the heat reflective coating on the outer layer of the carbon fiber main structure, ensure that the uniformity and thickness of the coating are within the specified range, and the coating thickness error does not exceed 5 microns. The uniform coating can ensure the consistency of the heat reflection effect, so that all parts of the outer surface of the spacecraft can effectively reflect external heat. And the precise control of the coating thickness within the specified range can ensure that the heat reflective coating achieves the best reflectivity. For example, if the coating is too thick, it may increase the weight and thickness of the thermal protection system and affect the performance of the spacecraft; if the coating is too thin, it may not achieve sufficient heat reflection effect. Finally, the installed carbon fiber thermal protection system is fully inspected and debugged. This step is the key to ensure that the performance and various indicators of the thermal protection system meet the design requirements. Through inspection, possible problems in the thermal protection system during installation, such as poor bonding of adhesives, uneven coating, etc., can be discovered in time, and corresponding adjustments and repairs can be made.Just like cars need to be thoroughly inspected and debugged before leaving the factory, only by ensuring that all performance indicators of the thermal protection system meet the requirements can the spacecraft operate safely and stably during flight, providing all-round guarantee for the spacecraft's thermal protection.

[0037] In this embodiment, when the spacecraft enters the atmosphere, the carbon fiber thermal protection system can increase the temperature of the outer surface 2 of the spacecraft by no more than 300 degrees Celsius within 3 minutes to ensure the safety and normal operation of the internal equipment and structures of the spacecraft. In the extremely low temperature environment of outer space, the carbon fiber thermal protection system can effectively prevent the loss of heat inside the spacecraft, so that the internal temperature of the spacecraft drops by no more than 10 degrees Celsius within 1 hour. The shielding efficiency of the carbon fiber thermal protection system against cosmic radiation is not less than 70%, so as to reduce the harm of cosmic radiation to the electronic equipment and astronauts inside the spacecraft.

[0038] Furthermore, firstly, when the spacecraft enters the atmosphere, the carbon fiber thermal protection system can make the temperature of the outer surface of the spacecraft rise by no more than 300 degrees Celsius within 3 minutes. This performance is crucial to protect the safety and normal operation of the internal equipment and structure of the spacecraft. In the process of the spacecraft entering the atmosphere, the outer surface temperature will rise sharply due to air friction and other reasons. If there are no effective thermal protection measures, the excessively high temperature will cause serious damage to the electronic equipment, instruments and structural materials inside the spacecraft. The carbon fiber thermal protection system can effectively block the rapid transfer of external heat through the synergistic effect of its multi-layer carbon fiber structure and heat-reflective coating, and control the increase in the outer surface temperature within a safe range. For example, the electronic components inside the spacecraft are very sensitive to temperature, and excessively high temperatures may cause their performance to degrade or even damage. This performance of the carbon fiber thermal protection system can ensure that the electronic components can still work normally when the spacecraft enters the atmosphere, and ensure the stable operation of the key systems such as navigation and communication of the spacecraft. Secondly, in the extremely low temperature environment of space, the thermal protection system can effectively prevent the loss of heat inside the spacecraft, so that the internal temperature of the spacecraft will not drop by more than 10 degrees Celsius within 1 hour. In outer space, the temperature is extremely low. If the spacecraft cannot effectively maintain the internal temperature, the electronic equipment and life support system inside it will not be able to operate normally. The carbon fiber thermal protection system is like a warm "protective cover". Through its good thermal insulation performance, it reduces the loss of internal heat to the outside. For example, for some scientific instruments that need to work within a specific temperature range, the thermal protection system can maintain the temperature stability of its surrounding environment and ensure the accuracy and reliability of scientific experiments and observations. In addition, the shielding efficiency of the carbon fiber thermal protection system for cosmic radiation is not less than 70%, which is of great significance for reducing the harm of cosmic radiation to electronic equipment inside the spacecraft and astronauts. Cosmic radiation contains various high-energy particles and rays. Long-term exposure to cosmic radiation will have an adverse effect on the performance and life of electronic equipment, and even threaten the health of astronauts. The high shielding efficiency of the thermal protection system can effectively block most of the cosmic radiation and provide a relatively safe environment inside the spacecraft. For example, for precision electronic equipment on spacecraft, such as computer control systems, communication equipment, etc., good radiation shielding can reduce failures and data errors caused by radiation and improve the overall reliability and safety of spacecraft.

[0039] In this embodiment, the carbon fiber thermal protection system can adapt to the flight missions and environmental requirements of different types of spacecraft. It can play a normal thermal protection role regardless of low-Earth orbit flight or deep space exploration mission, and the difference in thermal protection performance in different missions does not exceed 10%. The reliability of the carbon fiber thermal protection system is not less than 95% during the entire service life of the spacecraft, and after 20 spacecraft launches, flights and returns, the thermal protection performance can still meet the design requirements without large-scale maintenance and replacement.

[0040] Furthermore, first of all, the carbon fiber thermal protection system can adapt to the flight missions and environmental requirements of different types of spacecraft. Whether it is a low-Earth orbit flight or a deep space exploration mission, it can play a normal role in thermal protection, and the difference in thermal protection performance does not exceed 10%. This means that it has strong versatility and adaptability. For different types of spacecraft, their flight missions and environmental conditions may be very different. For example, spacecraft flying in low-Earth orbit are mainly affected by factors such as atmospheric resistance and solar radiation, while spacecraft for deep space exploration missions may face more extreme environmental challenges such as temperature changes and cosmic radiation. The carbon fiber thermal protection system can maintain good thermal protection performance in such different missions and environments, providing reliable protection for various spacecraft. This is like a multifunctional tool that can play a role in any work scenario. Secondly, during the entire service life of the spacecraft, its reliability is not less than 95%, and after 20 spacecraft launches, flights and returns, the thermal protection performance can still meet the design requirements without large-scale maintenance and replacement. High reliability means that the thermal protection system can work continuously and stably during the long-term use of the spacecraft, reducing spacecraft failures and safety hazards caused by thermal protection problems.

[0041] The working principle and use process of the present invention:

[0042] The first is the design and preparation stage. The carbon fiber main structure must be carefully designed according to the shape and size of the spacecraft. In this process, it is necessary to ensure that the weaving and composite process of each layer of carbon fiber meets the requirements, because the multi-layer carbon fiber material is woven and composited at a specific angle, which can effectively enhance the mechanical properties and better withstand the external force during flight. At the same time, the performance indicators of carbon fiber materials must be strictly controlled to ensure that the tensile strength is not less than 3500 MPa, the elastic modulus is between 200 and 300 GPa, and it has good thermal shock resistance. Then comes the pasting stage. The prepared carbon fiber main structure is pasted to the outer surface of the spacecraft with a special adhesive. During the pasting process, it is necessary to ensure that the adhesive is evenly distributed and a pressure of 100 to 200 Pascals is applied, just like a craftsman carefully fitting precious decorations to ensure a firm paste. This adhesive can maintain a stable bonding state in the range of -100 degrees Celsius to 500 degrees Celsius, providing a guarantee for the close integration of the carbon fiber main structure and the spacecraft. Then comes the spraying of heat-reflective coating, which is like putting on a special protective coat for the spacecraft. The heat-reflective coating is sprayed on the outer layer of the carbon fiber main structure. The spraying process must ensure that the uniformity and thickness of the coating are within the specified range, and the coating thickness error does not exceed 5 microns. It can reflect most of the external heat, and the thermal radiation reflectivity in a specific wavelength range is not less than 80%. Finally, it is the detection and debugging stage, during which the installed carbon fiber thermal protection system is comprehensively tested and debugged, just like a doctor conducts a comprehensive physical examination on a patient to ensure that its thermal protection performance and various indicators meet the design requirements. In the actual operation of the spacecraft, the system can increase the outer surface temperature by no more than 300 degrees Celsius within 3 minutes when entering the atmosphere, and the internal temperature can drop by no more than 10 degrees Celsius within 1 hour in the low temperature environment of the universe. The shielding efficiency of cosmic radiation is not less than 70%, and its edge sealing treatment makes the bonding strength between the sealing material and the carbon fiber main structure and the outer surface of the spacecraft not less than 50 Newtons / mm 2 , prevent external gases and impurities from entering, ensure the system is stable and reliable, adapt to different spacecraft missions and environmental requirements, and escort the safe flight of spacecraft. In actual production life, its related technologies and concepts may also bring reference and inspiration to other fields and promote industrial technological progress.

[0043] The electronic components and modules used in the invention can be parts commonly used in the market and can realize the specific functions in this case, and the specific models and sizes can be selected and adjusted according to actual needs.

[0044] The above shows and describes the basic principles, main features and advantages of the present invention. It should be understood by those skilled in the art that the present invention is not limited to the above embodiments. The above embodiments and descriptions are only for explaining the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention to be protected. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. A carbon fiber thermal protection system suitable for spacecraft, characterized in that: The invention comprises a carbon fiber main structure (1), wherein the carbon fiber main structure (1) is composited with multiple layers of carbon fiber materials, wherein the weaving directions of the carbon fiber layers are staggered at a specific angle, and the structure can effectively enhance its mechanical properties and thermal protection properties.

2. A carbon fiber thermal protection system suitable for spacecraft according to claim 1, characterized in that: The innermost layer of the carbon fiber main structure (1) is in direct contact with the outer surface (2) of the spacecraft and is connected via a special adhesive (3) having good high temperature resistance and bonding properties. The adhesive (3) can maintain a stable bonding state within a temperature range of -100 degrees Celsius to 500 degrees Celsius.

3. A carbon fiber thermal protection system suitable for spacecraft according to claim 2, characterized in that: It also includes a heat reflective coating (4) arranged on the outer layer of the carbon fiber main structure (1), wherein the heat reflective coating (4) is made of a material with high reflectivity and can reflect most of the external heat. Its reflectivity for thermal radiation in a specific wavelength range is not less than 80%.

4. A carbon fiber thermal protection system and method suitable for spacecraft according to claim 3, characterized in that: The carbon fiber material in the carbon fiber thermal protection system has a tensile strength of not less than 3500 MPa, an elastic modulus of 200 to 300 GPa, and a strength retention rate of not less than 80% at a temperature of up to 1500 degrees Celsius. The carbon fiber material has good thermal shock resistance. After 50 rapid cooling and heating cycles from room temperature to 1200 degrees Celsius, the carbon fiber main structure (1) has no obvious cracks or damage.

5. A carbon fiber thermal protection system and method suitable for spacecraft according to claim 4, characterized in that: The total thickness of the carbon fiber thermal protection system is between 5 and 15 mm, and its weight should be controlled within 5 kg per square meter to meet the weight and space restrictions of the spacecraft, while ensuring the stability of the thermal protection system during the flight of the spacecraft. The edge of the carbon fiber thermal protection system should be specially sealed, and the bonding strength between the sealing material and the carbon fiber main structure (1) and the outer surface of the spacecraft (2) should not be less than 50 Newtons / mm2 to prevent external gases and impurities from entering the thermal protection system during flight.

6. A carbon fiber thermal protection method suitable for spacecraft according to claim 5, characterized in that: The following steps are involved:

1. Design and prepare a suitable carbon fiber main structure (1) according to the shape and size of the spacecraft, ensure that the weaving and composite process of each layer of carbon fiber meets the requirements, and give full play to the performance of the carbon fiber material.

2. The prepared carbon fiber main structure (1) is adhered to the outer surface (2) of the spacecraft by means of a special adhesive (3). During the pasting process, the adhesive (3) must be evenly distributed and the pressure applied must be between 100 and 200 Pascals to ensure a firm adhesion.

3. Spraying a heat reflective coating (4) on the outer layer of the carbon fiber main structure (1). The spraying process must ensure that the uniformity and thickness of the coating are within a specified range, and the coating thickness error does not exceed 5 microns.

4. Carry out comprehensive inspection and debugging of the installed carbon fiber thermal protection system to ensure that its thermal protection performance and various indicators meet the design requirements.

7. A carbon fiber thermal protection system suitable for spacecraft according to claim 6, characterized in that: When the spacecraft enters the atmosphere, the carbon fiber thermal protection system can increase the temperature of the outer surface (2) of the spacecraft by no more than 300 degrees Celsius within 3 minutes, so as to ensure the safety and normal operation of the internal equipment and structure of the spacecraft. In the extremely low temperature environment of outer space, the carbon fiber thermal protection system can effectively prevent the heat loss inside the spacecraft, so that the internal temperature of the spacecraft drops by no more than 10 degrees Celsius within 1 hour. The shielding efficiency of the carbon fiber thermal protection system against cosmic radiation is not less than 70%, so as to reduce the harm of cosmic radiation to the electronic equipment inside the spacecraft and astronauts (if any).

8. The carbon fiber thermal protection system suitable for spacecraft according to claim 7, characterized in that: The carbon fiber thermal protection system can adapt to the flight missions and environmental requirements of different types of spacecraft. It can play a normal thermal protection role regardless of low-Earth orbit flight or deep space exploration mission, and the difference in thermal protection performance in different missions does not exceed 10%. The reliability of the carbon fiber thermal protection system is not less than 95% during the entire service life of the spacecraft, and after 20 spacecraft launches, flights and returns, the thermal protection performance can still meet the design requirements without the need for large-scale repairs and replacements.

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