Spaceship defense material and preparation method thereof

Abstract

The invention relates to the technical field of spacecrafts, in particular to a spacecraft defense material and a preparation method thereof, and designs a structure capable of effectively absorbing and dispersing impact energy on microscopic and macroscopic scales by utilizing computer simulation and an advanced material modeling technology. A base material with high strength, high toughness, light weight and corrosion resistance is selected, nanofibers, nanoparticles or nanosheet layers are embedded into the base material by utilizing a nanotechnology so as to enhance the mechanical property and the impact resistance of the base material, and the shape, the structure and the performance of the material are accurately controlled by adopting an advanced manufacturing technology. The prepared materials are stacked, bonded or mechanically connected together to form a final defense structure, and the structure is strictly tested. By combining a nanotechnology, composite material engineering and an additive manufacturing defense material, the deep requirement of a space exploration task is met, and the safety of astronauts and the smooth completion of the task are ensured.

Description

Technical Field

[0001] This invention relates to the field of spacecraft technology, and in particular to a spacecraft defense material and its preparation method. Background Technology

[0002] A spacecraft is a space vehicle that transports astronauts and cargo to space and returns them safely. During flight, spacecraft encounter various challenges and risks, such as cosmic radiation, solar wind, meteoroid impacts, and asteroid collisions. These factors necessitate that the spacecraft be designed and manufactured with high reliability and durability to ensure the safety of astronauts and the successful completion of the mission.

[0003] Existing materials used in spacecraft manufacturing mainly include metallic and non-metallic materials. In terms of metallic materials, aluminum, titanium, and stainless steel are commonly used in the manufacture of spacecraft. In terms of non-metallic materials, graphene and composite ceramics have advantages such as lightweight, high strength, good thermal stability, and radiation resistance.

[0004] However, while existing spacecraft materials already possess considerable protection against radiation and extreme temperatures, the demands on material protection performance are constantly increasing as space exploration missions progress. Especially when traveling to more distant destinations such as the Moon and Mars, spacecraft may face even harsher radiation and temperature environments. Summary of the Invention

[0005] The purpose of this invention is to provide a spacecraft defense material and its preparation method, which solves the problem that the requirements for the protective performance of materials are constantly increasing as space exploration missions deepen.

[0006] To achieve the above objectives, the present invention provides a method for preparing spacecraft defense materials, comprising the following steps: Design of material structure; Select basic materials; Nanotechnology is used to embed nanofibers, nanoparticles, or nanosheets into basic materials. Manufacturing materials; The prepared materials are layered, bonded, or mechanically connected to form the final defensive structure; Test the defensive structure.

[0007] The step of designing the material structure further includes: Identify the type and energy level of the impact that needs to be protected against, and define the main performance indicators of the structure; Collect information about potential impact sources and compile performance data of existing materials; Use numerical methods to establish a physical model of the structure; Based on the design objectives and collected data, several preliminary structural design schemes are proposed, and preliminary structural modeling is carried out using computer-aided design software. The preliminary structural model is imported into finite element analysis software for impact simulation. The simulation results are analyzed to evaluate the deformation, stress distribution, energy absorption and failure behavior of the structure under impact. Based on the simulation results, adjust the structural parameters to optimize performance; To verify the accuracy of simulation results, prototypes are manufactured or small-scale experiments are conducted. Based on the experimental results, iterative designs are carried out to correct model parameters or improve structural designs. The design is refined and improved by taking into account the constraints and limitations in the actual manufacturing and assembly process.

[0008] Among these steps, the selection of basic materials also includes: The basic materials include carbon fiber, ceramics, metal alloys and polymers, while the materials for parts that need to withstand extreme temperatures include graphene and silicon carbide.

[0009] The step of embedding nanofibers, nanoparticles, or nanosheets into a base material using nanotechnology further includes: The nanomaterials are dispersed in a suitable solvent to form a uniform nano suspension. The nano suspension is then subjected to ultrasonic treatment or mechanical stirring to ensure uniform dispersion of the nanomaterials in the solvent. Pre-treatment of the base materials; The well-dispersed nano suspension is mixed with the base material; Post-treatment of the mixture includes heat treatment, chemical treatment, and irradiation; The nano-reinforced material was characterized in detail to evaluate the dispersion of the nanomaterial, its binding with the matrix, and the reinforcement effect. Based on the test results, the preparation process parameters were adjusted to optimize the dispersion and embedding effect of the nanomaterial. Conduct mass production and application testing.

[0010] The manufacturing process further includes: Manufacturing technologies such as additive manufacturing, automated fiber placement, or autoclave curing are employed to precisely control the shape, structure, and properties of materials. During the manufacturing process, high temperature, high pressure, or special chemical treatments are used to ensure tight bonding between materials and optimize performance.

[0011] A spacecraft defense material, prepared using the aforementioned spacecraft defense material preparation method.

[0012] This invention discloses a spacecraft defense material and its preparation method. Utilizing computer simulation and advanced material modeling techniques, it designs a structure capable of effectively absorbing and dispersing impact energy at both microscopic and macroscopic scales. It selects base materials with high strength, high toughness, lightweight, and corrosion resistance, such as carbon fiber, ceramics, metal alloys, and polymers. For parts requiring resistance to extreme temperatures, materials with excellent thermal stability, such as graphene and silicon carbide, are chosen. Nanotechnology is used to embed nanofibers, nanoparticles, or nanosheets into the base materials to enhance their mechanical properties and impact resistance. Advanced manufacturing techniques, such as additive manufacturing (3D printing), automated fiber placement, or autoclave curing, are employed to precisely control the material's shape, structure, and properties. The prepared materials are then layered, bonded, or mechanically connected to form the final defense structure. This structure undergoes rigorous testing to ensure its effective operation in actual space environments. Combining nanotechnology, composite material engineering, and additive manufacturing of defense materials meets the needs of in-depth space exploration missions, ensuring astronaut safety and mission success. Attached Figure Description

[0013] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the accompanying drawings used in the description of the embodiments or the prior art will be briefly introduced below.

[0014] Figure 1 This is a flowchart illustrating the steps of a method for preparing spacecraft defense materials according to the first embodiment of the present invention.

[0015] Figure 2 This is a step diagram of the design material structure of the first embodiment of the present invention.

[0016] Figure 3 This is a flowchart illustrating the steps of embedding nanofibers, nanoparticles, or nanosheets into a base material using nanotechnology, according to the first embodiment of the present invention. Detailed Implementation

[0018] The embodiments of the present invention are described in detail below. Examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, but should not be construed as limiting the present invention.

[0019] The first embodiment of this application is as follows: Please see Figures 1 to 3 ,in, Figure 1 This is a flowchart illustrating the steps of a method for preparing spacecraft defense materials according to the first embodiment of the present invention. Figure 2 This is a step diagram of the design material structure of the first embodiment of the present invention. Figure 3This is a step diagram illustrating the first embodiment of the present invention, which utilizes nanotechnology to embed nanofibers, nanoparticles, or nanosheets into a base material. The present invention also provides a method for preparing a spacecraft defense material, comprising the following steps: S100: Design of material structure; S101: Specify the type and energy level of the impact that needs to be protected against, and define the main performance indicators of the structure; S102: Collect information on potential impact sources and compile performance data of existing materials; S103: Use numerical methods to establish a physical model of the structure; S104: Based on the design objectives and collected data, several preliminary structural design schemes are proposed, and preliminary structural modeling is performed using computer-aided design software; S105: Import the preliminary structural model into the finite element analysis software to perform impact simulation, analyze the simulation results, and evaluate the deformation, stress distribution, energy absorption and failure behavior of the structure under impact. S106: Adjust the structural parameters based on the simulation results to optimize performance; S107: Create a prototype or conduct small-scale experiments to verify the accuracy of the simulation results, and iterate the design based on the experimental results to correct the model parameters or improve the structural design. S108: Refine and improve the design by taking into account the constraints and limitations in the actual manufacturing and assembly process.

[0020] Specifically, the process involves: clearly defining the type and energy level of the impact to be protected against; defining the main performance indicators of the structure, such as energy absorption efficiency, weight, size, and cost; collecting information on potential impact sources (such as micrometeoroids, debris, etc.), including their size, velocity, density, and impact angle; compiling existing material performance data, such as elastic modulus, yield strength, fracture toughness, and coefficient of thermal expansion; using numerical methods such as finite element analysis (FEA) or discrete element method (DEM) to establish a physical model of the structure, considering the nonlinear behavior, failure modes, and interactions of materials in the model; based on the design objectives and collected data, proposing several preliminary structural design schemes; and using computer-aided design software (CAD) for preliminary structural modeling; and importing the preliminary structural model into finite element analysis software for impact simulation. Analyze simulation results to evaluate the structure's deformation, stress distribution, energy absorption, and failure behavior under impact; adjust structural parameters (such as thickness, shape, and materials) to optimize performance based on simulation results, using multi-objective optimization algorithms or heuristic algorithms (such as genetic algorithms and particle swarm optimization) to automatically search for the optimal design; manufacture prototypes or conduct small-scale experiments to verify the accuracy of simulation results, and iteratively design based on experimental results, correcting model parameters or improving the structural design; refine the design considering constraints and limitations in actual manufacturing and assembly processes, and conduct complete system-level simulations, including the integration and interaction of the structure with other spacecraft components; write detailed design reports, including the design process, simulation results, optimization history, and verification data, and organize an expert team to review the design to ensure that all requirements and standards are met.

[0021] S200: Selecting basic materials; Specifically, based on the specific operating environment and functional requirements of the spacecraft, the required material performance indicators, such as high strength, high toughness, lightweight, and corrosion resistance, are determined. These indicators serve as the basis for subsequent material screening and evaluation. Relevant literature, databases, and online resources are consulted to understand the types of materials currently available and their performance characteristics, with particular attention paid to materials known to possess high strength, high toughness, lightweight, and corrosion resistance. Communication with materials science experts, suppliers, and industry professionals is conducted to obtain the latest material information and market dynamics. Based on the collected information, materials are initially screened, excluding those that clearly do not meet performance requirements. The screened materials are then classified and ranked according to their performance characteristics for further evaluation. Laboratory tests are conducted on the initially screened materials to verify whether their performance meets the requirements. These tests may include tensile testing. Laboratory tests, including impact and corrosion tests, are conducted to quantitatively evaluate the material's performance and compare it with other candidate materials. While considering material performance, a cost-benefit analysis is performed to assess procurement, processing, and maintenance costs, ensuring the selected material is economically feasible. A comprehensive evaluation is conducted, taking into account performance, cost, and availability, using decision analysis methods such as Multi-Attribute Decision Analysis (MADM) or Analytic Hierarchy Process (AHP) to aid in decision-making. Based on the comprehensive evaluation results, the most suitable material is selected as the base material for the spacecraft. During practical application, the selected material undergoes continuous verification and monitoring to ensure its performance in the actual environment matches expectations. If performance problems or non-compliance are found, timely adjustments and replacements are necessary. Base materials with high strength, high toughness, lightweight, and corrosion resistance are selected, such as carbon fiber, ceramics, metal alloys, and polymers. For parts requiring resistance to extreme temperatures, materials with excellent thermal stability, such as graphene and silicon carbide, are chosen.

[0022] S300: Utilizing nanotechnology, nanofibers, nanoparticles, or nanosheets are embedded in basic materials; S301: Disperse nanomaterials in a suitable solvent to form a uniform nano suspension, and subject the nano suspension to ultrasonic treatment or mechanical stirring to ensure uniform dispersion of nanomaterials in the solvent. S302: Pretreatment of base materials; S303: Mix the well-dispersed nano-suspension with the base material; S304: Post-treatment of mixtures, including heat treatment, chemical treatment and irradiation; S305: Perform detailed characterization of the nano-reinforced material, evaluate the dispersion of the nanomaterial, its binding with the matrix, and the reinforcement effect, and adjust the preparation process parameters based on the test results to optimize the dispersion and embedding effect of the nanomaterial. S306: Conduct mass production and application testing.

[0023] Specifically, the required nanofibers, nanoparticles, or nanosheets are prepared. These nanomaterials are prepared through chemical synthesis, physical vapor deposition (PVD), solution methods, etc. The nanomaterials are dispersed in a suitable solvent to form a uniform nanosuspension. Different dispersants and dispersion techniques are required for different nanomaterials and matrices. The nanosuspension is subjected to ultrasonic treatment or mechanical stirring to ensure uniform dispersion of the nanomaterials in the solvent and prevent agglomeration. The base material is pretreated, such as by cleaning the surface, removing impurities, and increasing surface activity, to promote good bonding between the nanomaterials and the matrix. Functional groups or coatings are introduced onto the matrix surface as needed to improve compatibility with the nanomaterials. The well-dispersed nanosuspension is then mixed with the base material through methods such as impregnation, spraying, spin coating, and blending. For polymer matrices, nanomaterials are added during the polymerization process to allow them to grow in situ during polymerization. The nanomaterials are formed and dispersed in the matrix. For metal and ceramic matrices, powder metallurgy is used to mix the nanomaterials with the matrix powder, then press and sinter them. Depending on the matrix and nanomaterials used, appropriate post-treatments, such as heat treatment, chemical treatment, and irradiation, are performed to promote chemical bonding or physical cross-linking between the nanomaterials and the matrix. For systems requiring curing (such as polymers), curing treatment is performed to firmly embed the nanomaterials in the matrix. The nano-reinforced materials are characterized in detail, including morphological observation (SEM, TEM), structural analysis (XRD, FTIR), and mechanical property testing, to evaluate the dispersion of the nanomaterials, their bonding with the matrix, and the reinforcing effect. Based on the test results, the preparation process parameters are adjusted to optimize the dispersion and embedding effect of the nanomaterials. After successful verification in the laboratory stage, the preparation process is scaled up to pilot or industrial production scale for mass production and application testing.

[0024] S400: Manufacturing materials; Specifically, advanced manufacturing technologies, such as additive manufacturing (3D printing), automated fiber placement, or autoclave curing, are employed to precisely control the shape, structure, and properties of materials. During the manufacturing process, high temperatures, high pressures, or special chemical treatments are used to ensure tight bonding between materials and optimize performance. Additive manufacturing (3D printing): Based on the selected material and design requirements, parameters such as layer thickness, infill density, and support structure are set for the printer. The material is loaded into the 3D printer, the printing program is started, and material is deposited layer by layer to build the object. The support structure is then removed, and the printed part undergoes necessary cleaning, sanding, and surface treatment. Automated fiber placement: Specialized software plans the fiber placement path to maximize structural strength and performance. Pre-impregnated or unimpregnated fiber bundles are automatically placed onto a mold or substrate according to the planned path. The placed fiber layers are then thermo-pressed or chemically cured to ensure tight bonding between fibers. Autoclave Curing: Molds are fabricated according to design requirements and preheated. Prepreg or other forms of composite materials are laid on the mold according to design requirements. The laid-up material, along with the mold, is placed in a vacuum bag, air is removed, and the bag is sealed. The vacuum-sealed material is then placed in an autoclave and cured under high temperature and pressure. After cooling, the material is removed from the autoclave and demolded. Special Chemical Treatment: Appropriate chemical treatment methods, such as surface activation and impregnation, are selected based on the material properties and performance requirements. The material is placed in a specific chemical environment to improve its surface properties or enhance the bonding strength between materials. After treatment, the material is cleaned and dried to remove residual chemicals. Finally, quality inspection and testing: The appearance of the manufactured parts is checked to ensure it meets design requirements. Non-destructive testing of the internal structure is performed using X-rays, ultrasound, etc. Mechanical and thermal performance tests are conducted to ensure they meet usage requirements. Necessary surface treatments, such as painting and polishing, are applied. The manufactured parts are then assembled and integrated to form the final product or structure.

[0025] S500: The prepared materials are layered, bonded or mechanically connected together to form the final defensive structure; Specifically, ensure all prepared materials meet design specifications and quality requirements. Clean all material surfaces to remove any contaminants that may affect adhesion or bonding. Determine the stacking order of different material layers according to design requirements. Use clamps, locating pins, or other auxiliary tools to ensure precise alignment of each layer. Select a suitable adhesive based on material properties and the application environment. Apply the adhesive evenly to the material contact surfaces, ensuring a moderate and uniform application. Stack the adhesive-coated material layers together, applying appropriate pressure to promote adhesive diffusion and wetting. Perform curing treatment according to adhesive requirements, such as room temperature curing, heat curing, or UV curing. Mechanical bonding: according to design requirements. The process involves selecting appropriate mechanical connection methods, such as bolting, riveting, and welding. Pre-processing of the parts requiring mechanical connection includes drilling, grooving, and deburring. Using suitable tools and equipment, materials are securely connected according to the predetermined connection method. Finally, the appearance of the stacked or connected structure is checked for flatness and defects. The dimensions of the structure are verified to meet design requirements. Necessary performance tests, such as tensile tests, impact tests, and sealing tests, are conducted to ensure the structure meets predetermined usage requirements. Excess adhesives and scraps are removed. Surface treatments, such as painting and electroplating, are applied as needed. Necessary markings are added to the structure, and key information from the manufacturing process is recorded.

[0026] S600: Testing the defensive structure.

[0027] Specifically, the defensive structure undergoes rigorous testing, including impact testing, thermal testing, radiation testing, and durability testing, to ensure it can function effectively in real-world space environments. Among these, impact testing... Objectives: To simulate extreme conditions such as impacts from small meteorites and debris in space and test the structure's impact resistance. Thermal testing aims to simulate extreme temperature changes in space and test the structure's performance in terms of thermal expansion and contraction, thermal stress, etc. Radiation testing aims to simulate the high-energy radiation environment in space and test the structure's radiation resistance. Durability testing aims to simulate long-term service in the space environment and test the structure's durability and reliability.

[0028] By combining nanotechnology, composite materials engineering, and additive manufacturing of defense materials, we can meet the in-depth needs of space exploration missions and ensure the safety of astronauts and the successful completion of missions.

[0029] The second embodiment of this application is as follows: Based on the first embodiment, this embodiment provides a spacecraft defense material prepared using the aforementioned spacecraft defense material preparation method.

[0030] Defense materials combining nanotechnology, composite materials engineering, and additive manufacturing meet the in-depth needs of space exploration missions, ensuring the safety of astronauts and the successful completion of missions.

[0031] The above-disclosed embodiments are merely one or more preferred embodiments of this application and should not be construed as limiting the scope of this application. Those skilled in the art can understand that all or part of the processes for implementing the above embodiments and equivalent changes made in accordance with the claims of this application still fall within the scope of this application.

Claims

1. A method for preparing a spacecraft defense material, characterized in that, Includes the following steps: Design materials and structure; Select basic materials; Nanotechnology is used to embed nanofibers, nanoparticles, or nanosheets into basic materials. Manufacturing materials; The prepared materials are layered, bonded, or mechanically connected to form the final defensive structure; Test the defensive structure.

2. The method for preparing spacecraft defense materials as described in claim 1, characterized in that, The step of designing the material structure further includes: Identify the type and energy level of the impact that needs to be protected against, and define the main performance indicators of the structure; Collect information about potential impact sources and compile performance data of existing materials; Use numerical methods to establish a physical model of the structure; Based on the design objectives and collected data, several preliminary structural design schemes are proposed, and preliminary structural modeling is carried out using computer-aided design software. The preliminary structural model is imported into finite element analysis software for impact simulation. The simulation results are analyzed to evaluate the deformation, stress distribution, energy absorption and failure behavior of the structure under impact. Based on the simulation results, adjust the structural parameters to optimize performance; To verify the accuracy of simulation results, prototypes are manufactured or small-scale experiments are conducted. Based on the experimental results, iterative designs are carried out to correct model parameters or improve structural designs. The design is refined and improved by taking into account the constraints and limitations in the actual manufacturing and assembly process.

3. The method for preparing spacecraft defense materials as described in claim 2, characterized in that, The steps of selecting basic materials also include: The basic materials include carbon fiber, ceramics, metal alloys and polymers, while the materials for parts that need to withstand extreme temperatures include graphene and silicon carbide.

4. The method for preparing spacecraft defense materials as described in claim 3, characterized in that, Using nanotechnology, nanofibers, nanoparticles, or nanosheets are embedded in a base material, the steps of which further include: The nanomaterials are dispersed in a suitable solvent to form a uniform nano suspension. The nano suspension is then subjected to ultrasonic treatment or mechanical stirring to ensure uniform dispersion of the nanomaterials in the solvent. Pre-treatment of the base materials; The well-dispersed nano suspension is mixed with the base material; Post-treatment of the mixture includes heat treatment, chemical treatment, and irradiation; The nano-reinforced material was characterized in detail to evaluate the dispersion of the nanomaterial, its binding with the matrix, and the reinforcement effect. Based on the test results, the preparation process parameters were adjusted to optimize the dispersion and embedding effect of the nanomaterial. Conduct mass production and application testing.

5. The method for preparing spacecraft defense materials as described in claim 4, characterized in that, The manufacturing process further includes: Manufacturing technologies such as additive manufacturing, automated fiber placement, or autoclave curing are employed to precisely control the shape, structure, and properties of materials. During the manufacturing process, high temperature, high pressure, or special chemical treatments are used to ensure tight bonding between materials and optimize performance.

6. A spacecraft defense material, prepared by the spacecraft defense material preparation method as described in any one of claims 1 to 5.

Images