Physical property analysis method of flexible integrated cable for spacecraft

Abstract

The invention discloses a spacecraft flexible integrated cable physical property analysis method comprising the following steps: dividing different operation areas in a spacecraft, and determining an application scene corresponding to each operation area; aiming at each application scene, obtaining an application logic characteristic file of the cable; key physical performance parameters of the cable are obtained; integrating the key physical performance parameters of the cable according to the application logic characteristic file of the cable to obtain an integration analysis result; and generating a comprehensive physical property file and an analysis report according to the integrated analysis result. According to the invention, the overall evaluation capability of the applicability of the flexible integrated cable is improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of flexible integrated cables for spacecrafts, and particularly relates to a method for physical property analysis of flexible integrated cables for spacecrafts. Background Art

[0002] With the gradual development of spacecrafts towards the trends of integration, miniaturization, and lightweight, new requirements for overall satellite weight reduction and cost reduction have been put forward. The overall satellite cable network is one of the important products that connect each subsystem and realize the functions of the overall satellite, occupying a relatively large weight ratio of the overall satellite. Therefore, the traditional complex cable network urgently needs to seek new ways of lightweight and cost reduction to meet the application requirements of spacecrafts.

[0003] Flexible integrated cables are highly integrated new cables that meet the development requirements of spacecrafts. Based on polyimide films, they are small in volume and light in weight, which can greatly reduce the weight of spacecrafts and meet the requirements of integration. They are an important direction for the future development of spacecrafts.

[0004] With the increasing complexity of space missions, the number and integration degree of electronic devices carried on spacecrafts continue to increase, resulting in an increasingly crowded and complex wiring environment inside the spacecrafts. Flexible integrated cables need to be laid in a very limited space, which not only increases the installation difficulty, but also puts more stringent requirements on the flexibility, bending radius, and mechanical strength of the cables themselves.

[0005] However, there are many limitations in the current physical property analysis and selection methods for flexible integrated cables for spacecrafts. Traditional practices often rely on single parameter data sheets provided by material suppliers, experience from past projects, or isolated component-level tests for specific physical properties. This approach lacks a comprehensive consideration of the multi-physical field coupling effects of cables in specific application environments. Existing cable analysis and management methods are often fragmented, focusing on solving problems in a specific link, rather than providing an integrated, multi-physical field comprehensive analysis systematic framework based on the specific "application logic" inside the spacecraft.

[0006] The environmental differences in different regions inside the spacecraft are huge. Existing analysis methods generally lack a standardized and systematic methodology to convert the "specific application logic" of cable deployment inside the spacecraft into a set of weighted and integrated physical property index requirements, and conduct in-depth analysis based on this. If the analysis is insufficient, it may lead to improper cable selection, damage caused by insufficient consideration of physical property changes under actual working conditions during the laying process, increased risk of on-orbit failures, or unnecessary increase in the weight and cost of the spacecraft system due to over-design. Summary of the Invention

[0007] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a method for analyzing the physical properties of flexible integrated cables for spacecraft, thereby improving the overall evaluation capability of the suitability of flexible integrated cables.

[0008] The objective of this invention is achieved through the following technical solution: a method for analyzing the physical properties of flexible integrated cables for spacecraft, comprising: dividing the spacecraft into different operating areas and determining the application scenario corresponding to each operating area; obtaining an application logic characteristic profile of the cable for each application scenario; obtaining the key physical performance parameters of the cable; integrating the key physical performance parameters of the cable based on the application logic characteristic profile to obtain an integrated analysis result; and generating a comprehensive physical property profile and analysis report based on the integrated analysis result.

[0009] In the aforementioned method for analyzing the physical properties of flexible integrated cables for spacecraft, the different operating areas inside the spacecraft include the external exposed area, the propulsion section, the payload compartment, and the avionics compartment.

[0010] In the aforementioned analysis method for the physical properties of flexible integrated cables for spacecraft, the application scenarios corresponding to the externally exposed areas are: facing severe temperature cycling, high vacuum, strong ultraviolet radiation, charged particle radiation, and atomic oxygen erosion; the application scenarios corresponding to the propulsion section are: withstanding high temperatures, strong vibrations, and shocks; the application scenarios corresponding to the payload compartment are: having strict pre-set requirements for gas release to avoid contaminating sensitive surfaces; and simultaneously meeting high pre-set requirements for micro-vibration and electromagnetic compatibility; the application scenarios corresponding to the avionics equipment compartment are: a temperature-controlled environment, but with high equipment density and a complex electromagnetic environment, requiring pre-set requirements for the electromagnetic shielding performance and heat dissipation performance of the cables.

[0011] In the aforementioned method for analyzing the physical properties of flexible integrated cables for spacecraft, the application logic characteristic profile of the cable includes: thermal environment characteristics, mechanical environment characteristics, radiation environment characteristics, electromagnetic environment characteristics, vacuum environment characteristics, and functional criticality level.

[0012] The aforementioned methods for analyzing the physical properties of flexible integrated cables for spacecraft include the following: thermal environment characteristics: maximum operating temperature, minimum operating temperature, rate of temperature change, number of thermal cycles, duration of sustained high / low temperatures, primary heat source being solar radiation, equipment heat generation, or external heat flow; mechanical environment characteristics: vibration spectrum, shock spectrum, acceleration overload, amplitude and frequency of sustained bending / torsional loads, and allowable tensile force during installation; radiation environment characteristics: total ionization dose, displacement damage dose, risk assessment of single-event effects, and types and energy spectra of radiated particles; among which, radiated particle types include protons, electrons, and heavy ions; electromagnetic environment characteristics: frequency and intensity of electromagnetic interference sources, and sensitivity thresholds of the cable itself or connected equipment to electromagnetic interference; vacuum environment characteristics: vacuum level and specific limits on material gas release; and functional criticality level: assessing the potential impact of cable failure on spacecraft mission, safety, or lifespan.

[0013] In the aforementioned method for analyzing the physical properties of flexible integrated cables for spacecraft, the key physical performance parameters of the cable include mechanical performance parameters, thermal performance parameters, electrical performance parameters, and environmental adaptability parameters.

[0014] The aforementioned methods for analyzing the physical properties of flexible integrated cables used in spacecraft include the following parameters: mechanical properties, tensile strength, elongation at break, minimum bending radius, material flexibility, bending fatigue life, vibration fatigue life, abrasion resistance, and compressive strength; thermal properties, upper and lower operating temperature limits, thermal conductivity, coefficient of thermal expansion, flame retardancy rating, and performance retention after rapid or repeated thermal cycling; electrical properties, rated current carrying capacity, rated voltage, insulation resistance, dielectric strength, signal transmission integrity parameters, electromagnetic compatibility, and electromagnetic interference shielding effectiveness; and environmental adaptability parameters, including vacuum release characteristics, radiation resistance, antigenic oxygen ablation resistance, and high and low temperature resistance.

[0015] In the aforementioned method for analyzing the physical properties of flexible integrated cables for spacecraft, the key physical performance parameters of the cable are integrated based on the cable's application logic characteristic profile to obtain the integrated analysis results. Each key physical performance parameter is assigned a weighting factor based on the cable's application logic characteristic profile. The overall score of the cable is obtained based on the values ​​of each key physical performance parameter and the corresponding weighting factor.

[0016] The aforementioned method for analyzing the physical properties of flexible integrated cables for spacecraft includes a comprehensive physical property profile and analysis report comprising an input application logic property profile summary, a list of key physical performance parameters and their quantitative results, a comprehensive physical property profile, risk assessment and trade-off analysis, and conclusions and recommendations. The input application logic property profile summary clearly describes the target application scenario, the main environmental stresses faced, and functional requirements of the analyzed cable. The list of key physical performance parameters and their quantitative results lists all key physical performance parameters selected as evaluation criteria, their specific values, test conditions, or reference standards. The comprehensive physical property profile is presented as a series of comprehensive scores, risk level assessments, and achievement rates of key performance indicators, visually displayed in chart form. The risk assessment and trade-off analysis assesses potential performance risks of the cable and considers trade-offs between different performance indicators. The conclusions and recommendations provide conclusions regarding the cable's suitability and offer specific suggestions for subsequent design optimization, laying precautions, or further specialized testing.

[0017] A physical property analysis system for flexible integrated cables used in spacecraft includes: a first module for dividing different operating areas inside the spacecraft and determining the application scenario corresponding to each operating area; for each application scenario, obtaining an application logic characteristic profile of the cable; a second module for obtaining the key physical performance parameters of the cable; a third module for integrating the key physical performance parameters of the cable based on the application logic characteristic profile of the cable to obtain integrated analysis results; and a fourth module for generating a comprehensive physical property profile and analysis report based on the integrated analysis results.

[0018] Compared with the prior art, the present invention has the following advantages:

[0019] (1) This invention makes the design and selection of flexible integrated cables more targeted, and can be optimized according to the specific application requirements on spacecraft, effectively avoiding on-orbit risks caused by insufficient performance, or cost and weight waste caused by excessive performance.

[0020] (2) This invention provides a scientific basis for cable laying process (such as bending radius control, fixing method selection, etc.) by providing physical property analysis data based on actual working conditions, thereby minimizing the damage that may be caused during installation and ensuring the long-term stable operation of the cable;

[0021] (3) By establishing a systematic and scientific physical property analysis and evaluation system, this invention enhances the confidence of engineers in using flexible integrated cables in complex and harsh aerospace environments, and helps to promote their popularization and in-depth application in more types of aerospace missions with higher requirements.

[0022] (4) By more accurately evaluating and selecting cables in the early stages of design, this invention can effectively identify potential risk points, reduce later design changes, repeated testing and verification work, thereby potentially shortening the overall R&D cycle and controlling project costs.

[0023] (5) This invention ensures that the cable system, which serves as the “nerves” and “blood vessels” of a spacecraft, can work reliably within its expected service environment and lifespan, which is an important guarantee for improving the success rate of the entire space mission. Attached Figure Description

[0024] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

[0025] Figure 1 This is a cross-sectional view of the flexible integrated cable provided in an embodiment of the present invention. Detailed Implementation

[0026] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the disclosure to those skilled in the art. It should be noted that, unless otherwise specified, the embodiments and features described herein can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0027] There is an urgent need for a systematic and comprehensive method to analyze the physical properties of flexible integrated cables used in spacecraft. This method should: fully consider the "specific application logic" of the cable in different operating areas of the spacecraft; integrate multiple key physical parameters, including mechanical, thermal, electrical, and environmental adaptability; provide a solid theoretical basis and data support for the cable's optimized design, material selection, reliable laying process, and high-fidelity simulation analysis; and ultimately aim to improve the reliability and applicability of flexible integrated cables in spacecraft applications, promoting their widespread and in-depth application in various space missions.

[0028] This embodiment provides a method for analyzing the physical properties of flexible integrated cables used in spacecraft, the method comprising:

[0029] The spacecraft's internal operating areas are divided, and the application scenarios corresponding to each operating area are determined. For each application scenario, the application logic characteristic profile of the cable is obtained. The key physical performance parameters of the cable are obtained. Based on the application logic characteristic profile of the cable, the key physical performance parameters of the cable are integrated to obtain the integrated analysis results. Based on the integrated analysis results, a comprehensive physical property profile and analysis report are generated.

[0030] The different operating areas inside a spacecraft include the externally exposed area, the propulsion section, the payload compartment, and the avionics compartment.

[0031] The application scenarios corresponding to the external exposure area are: facing severe temperature cycling, high vacuum, strong ultraviolet radiation, charged particle radiation, and atomic oxygen erosion; the application scenarios corresponding to the propulsion section are: withstanding high temperatures, strong vibrations, and shocks; the application scenarios corresponding to the payload compartment are: having strict preset requirements for gas release to avoid contaminating sensitive surfaces; and at the same time, having preset high requirements for micro-vibration and electromagnetic compatibility; the application scenarios corresponding to the avionics equipment compartment are: a temperature-controlled environment, but with high equipment density and a complex electromagnetic environment, and preset requirements for the electromagnetic shielding performance and heat dissipation performance of cables.

[0032] The application logic characteristic profile of a cable includes: thermal environment characteristics, mechanical environment characteristics, radiation environment characteristics, electromagnetic environment characteristics, vacuum environment characteristics, and functional criticality level.

[0033] Thermal environment characteristics include: maximum operating temperature, minimum operating temperature, rate of temperature change, number of thermal cycles, duration of sustained high / low temperatures, primary heat source being solar radiation, equipment heat generation, or external heat flow; mechanical environment characteristics include: vibration spectrum, shock spectrum, acceleration overload, amplitude and frequency of sustained bending / torsional loads, and permissible tensile force during installation during launch and on-orbit operation; radiation environment characteristics include: total ionization dose, displacement damage dose, risk assessment of single-event effects, and radiation particle type and energy spectrum; among which, radiation particle types include protons, electrons, and heavy ions; electromagnetic environment characteristics include: frequency and intensity of electromagnetic interference sources, and sensitivity thresholds of the cable itself or connected equipment to electromagnetic interference; vacuum environment characteristics include: vacuum level and specific limits on material venting; functional criticality level includes: assessing the potential impact of cable failure on spacecraft mission, safety, or lifespan.

[0034] The key physical performance parameters of cables include mechanical performance parameters, thermal performance parameters, electrical performance parameters, and environmental adaptability parameters.

[0035] Mechanical performance parameters include tensile strength, elongation at break, minimum bending radius, material flexibility, flexural fatigue life, vibration fatigue life, wear resistance, and compressive strength; thermal performance parameters include upper and lower operating temperature limits, thermal conductivity, coefficient of thermal expansion, flame retardancy rating, and performance retention after rapid or repeated thermal cycling; electrical performance parameters include rated current carrying capacity, rated voltage, insulation resistance, dielectric strength, signal transmission integrity parameters, electromagnetic compatibility, and electromagnetic interference shielding effectiveness; environmental adaptability parameters include vacuum release characteristics, radiation resistance, antigenic oxygen ablation resistance, and high and low temperature resistance.

[0036] In the integrated analysis results obtained by integrating the key physical performance parameters of the cable based on the cable's application logic characteristic file, a weighting factor is assigned to each key physical performance parameter according to the cable's application logic characteristic file; and the comprehensive score of the cable is obtained based on the values ​​of each key physical performance parameter and the corresponding weighting factor.

[0037] The comprehensive physical property profile and analysis report includes a summary of the input application logic property profile, a list of key physical performance parameters and their quantitative results, the comprehensive physical property profile, risk assessment and trade-off analysis, and conclusions and recommendations. The input application logic property profile summary includes: a clear description of the target application scenario, the main environmental stresses faced, and functional requirements of the analyzed cable; the list of key physical performance parameters and their quantitative results includes: a list of all key physical performance parameters selected as the evaluation basis, their specific values, test conditions, or reference standards; the comprehensive physical property profile is presented as a series of comprehensive scores, risk level assessments, and achievement rates of key performance indicators, visually displayed in chart form; the risk assessment and trade-off analysis includes: an assessment of potential performance risks of the cable, and considerations for trade-offs between different performance indicators; the conclusions and recommendations include: conclusions regarding the cable's suitability, and specific suggestions for subsequent design optimization, laying precautions, or further specialized testing.

[0038] This embodiment aims to address the current lack of an analytical framework that fully considers the "application-specific logic" of cables deployed within spacecraft and integrates a comprehensive evaluation of their physical properties across multiple aspects, including mechanical, thermal, electrical, and space environment parameters. This leads to challenges in cable optimization design, efficient and reliable laying, and accurate performance simulation. This embodiment improves the overall evaluation capability of the suitability of flexible integrated cables by systematically integrating various physical parameters closely related to specific application scenarios, rather than evaluating single indicators in isolation.

[0039] The method includes the following steps:

[0040] (1) Define the spacecraft application environment and cable application logic

[0041] The core of this step lies in gaining a deep understanding of the specific operating scenarios of the cable within the spacecraft. First, it's necessary to identify different operating areas within the spacecraft, such as externally exposed areas, propulsion modules, payload bays, potential crew compartments, and avionics bays. Then, for each target application area, a detailed description of the environmental stresses and operating conditions the cable will face in that area must be provided, including but not limited to: temperature range and variation gradients, thermal cycling characteristics, vibration spectrum and amplitude, impact loads, radiation type and dose, vacuum level, atomic oxygen concentration, and electromagnetic interference level. Simultaneously, the criticality level of the function carried by the cable must be determined, such as whether it's a main power supply line crucial to mission success or redundant sensor signal lines. The output of this step is a structured "application logic characteristic profile" for each type of cable specific to its application.

[0042] (2) Identify and quantify key physical parameters

[0043] Based on the "application logic characteristic profile" determined in step (1), a series of key physical performance parameters that must be considered are selected for a specific cable. The selection of these parameters directly serves the performance requirements of the cable under this application logic. For example... Figure 1 As shown, the flexible integrated cable 1 is typically a double-conductor layer flexible board structure, consisting of a substrate layer 1-1, a conductor layer 1-2, an adhesive layer 1-3, and a cover film 1-4. Key physical performance parameters need to be identified based on the raw materials of the flexible integrated cable. These parameters include, but are not limited to:

[0044] Mechanical properties: such as tensile strength, elongation at break, minimum bending radius (especially bending performance at extreme temperatures), material flexibility, bending fatigue life, vibration fatigue life, wear resistance, compressive strength, etc.

[0045] Thermal properties: such as the upper and lower limits of the material's long-term operating temperature, thermal conductivity, coefficient of thermal expansion, flame retardancy rating, and performance retention after rapid or multiple thermal cycles.

[0046] Electrical performance: such as rated current carrying capacity (ampere capacity), rated voltage, insulation resistance, dielectric strength, signal transmission integrity parameters (such as attenuation and crosstalk), electromagnetic compatibility (EMC), and electromagnetic interference (EMI) shielding effectiveness.

[0047] Environmental adaptability: such as vacuum release characteristics, radiation resistance, antigen oxygen ablation resistance, and high and low temperature resistance.

[0048] (3) Integrating physical parameters based on application logic

[0049] This step involves constructing an analytical framework to integrate the key physical parameters quantified in step (2). This integration is not a simple listing of parameters, but rather assigning appropriate weights to different parameters or using specific coupling models for comprehensive evaluation based on the "application logic characteristic profile" defined in step one. For example, for cables installed in locations subject to frequent mechanical movement (such as solar panel deployment mechanisms), parameters such as bending fatigue life and low-temperature flexibility will receive higher weights; while for cables near highly sensitive electronic devices, their electromagnetic shielding effectiveness and vacuum degassing characteristics may become priority considerations.

[0050] (4) Generate a comprehensive physical property profile and analysis report

[0051] The integrated analysis results of step (3) will form a comprehensive physical property profile of the cable for a specific application logic. This profile can be presented as a series of comprehensive scores, risk level assessments, achievement of key performance indicators, or visually displayed in chart form. Simultaneously, a detailed analysis report will be generated, outlining the analysis process, methods used, key findings, and targeted recommendations.

[0052] Furthermore, the method also includes the following steps:

[0053] (5) Application analysis output guides design, laying and simulation

[0054] The comprehensive physical property profile and analysis report generated in step (4) will serve as an important technical basis for subsequent engineering activities of flexible integrated cables.

[0055] Guiding cable design and material selection: For example, selecting appropriate conductor materials, insulation materials, shielding materials, etc., based on analysis results.

[0056] Optimize cable laying processes: For example, based on the analysis results of the cable's bending performance under specific temperatures and stresses, determine a safe minimum bending radius and installation torque; based on vibration analysis results, determine reasonable fixing point spacing and methods.

[0057] Provide high-confidence input for simulation analysis: Physical property parameters calibrated and integrated by "application logic" are used as input data in more advanced simulation models, such as thermal stress simulation models, electromagnetic field simulation models, and mechanical dynamics simulation models, thereby improving the accuracy of simulation predictions.

[0058] Specifically, the method includes the following steps:

[0059] Step 1: Define the spacecraft application environment and cable application logic

[0060] First, the spacecraft needs to be divided into regions to identify typical application scenarios with different environmental characteristics and functional requirements. For example: (11) External exposed areas: such as connecting cables for solar arrays, feed lines for external antennas, and external connection lines for scientific instruments. These areas usually face severe temperature cycles (alternating between sunlight and shadow), high vacuum, strong ultraviolet radiation, charged particle radiation, and atomic oxygen erosion. (12) Propulsion system area: such as cables connecting engine sensors and actuators. These areas may be subjected to high temperatures, strong vibrations, and shocks. (13) Payload compartment: such as cables connecting precision optical instruments, communication transponders, and other equipment. There are strict requirements for gas release (especially condensable volatile matter, CVCM) to avoid contaminating sensitive surfaces; at the same time, there may be high requirements for micro-vibration and electromagnetic compatibility. (14) Avionics compartment / instrument compartment: usually a temperature-controlled environment, but with high equipment density and complex electromagnetic environment, there are certain requirements for the electromagnetic shielding performance and heat dissipation performance of cables. (15) Deployable / movable parts: such as cables in deployable antennas, solar wings, robotic arms, etc. These cables need to withstand repeated bending and twisting, and have high requirements for dynamic bending life and abrasion resistance.

[0061] For each specific application scenario, its "application logic" needs to be described in detail, that is, the specific mission of the cable in that scenario and the challenges it faces. This includes:

[0062] Thermal environment characteristics: Define the maximum / minimum operating temperature, rate of temperature change, number of thermal cycles, duration of continuous high / low temperature, and main heat sources (solar radiation, equipment heat generation, external heat flow, etc.).

[0063] Mechanical environmental characteristics: Define the vibration spectrum (random vibration, sinusoidal vibration), impact spectrum, acceleration overload, amplitude and frequency of continuous bending / torsional loads, and allowable tensile force during the launch and on-orbit operation phases.

[0064] Radiation environment characteristics: Determine the risk assessment of total ionizing dose (TID), displacement damage dose (DDD), single event effect (SEE), and the main types of radiating particles (such as protons, electrons, and heavy ions) and their energy spectra.

[0065] Electromagnetic environment characteristics: Identify the main electromagnetic interference source frequencies and intensities in the area, as well as the sensitivity thresholds of the cable itself or the connected equipment to electromagnetic interference.

[0066] Vacuum environment characteristics: Define the vacuum level and specific limits for material release (TML, CVCM, WVR - water vapor recovery rate), especially in cases where there are optical or sensitive surfaces nearby.

[0067] Functional Criticality Level: Assess the potential impact of cable failure on spacecraft mission, safety, or lifespan, and classify it into different levels such as "mission critical", "safety critical", and "functionally degradeable".

[0068] The final output of this step is one or more structured "application logic profiles" that clearly record the environmental and functional requirements that each specific cable application needs to address.

[0069] Step 2: Identify and quantify key physical parameters

[0070] Based on the "application logic characteristic profile," the most relevant key physical parameters are selected for each type of cable application. The selection of these parameters must closely align with the core requirements of that application logic.

[0071] For example, cables used for deployable solar panels require high levels of flexibility at low temperatures, fatigue life against repeated bending, and resistance to space ultraviolet and particle radiation. Cables used to power high-power equipment, on the other hand, are more concerned with their current carrying capacity (ampere capacity), voltage rating, and heat dissipation capabilities in high vacuum environments.

[0072] The quantification of parameters should be based on recognized testing standards as much as possible. Data sources may include: detailed material performance data sheets provided by qualified suppliers (note the applicable conditions and testing methods); targeted internal testing or testing commissioned to authoritative third-party institutions; and relevant experimental data from published academic literature or technical reports.

[0073] When quantifying parameters, the coupling effects between parameters and the influence of environmental factors on parameter values ​​must be considered. For example, the mechanical strength and flexibility of materials may change significantly after exposure to low or high temperatures; the cumulative effect of radiation may lead to the degradation of the mechanical properties and the decline of the electrical properties of insulating materials.

[0074] The output of this step is a quantified and verified list of key physical parameters and their corresponding values ​​or acceptable ranges for a specific application logic.

[0075] Step 3: Integrate physical parameters based on application logic

[0076] The aim is to integrate isolated physical parameters into a holistic assessment that reflects the overall performance of a cable under specific application logic.

[0077] Example of an integration framework:

[0078] Weighted scoring model:

[0079] (31) Based on the “Application Logic Characteristic Profile”, assign a weight factor (Wi) to each key physical parameter to reflect its relative importance in the application scenario. For example, for cables that need to be bent frequently, the weight factor of “bending fatigue life” will be very high.

[0080] (32) Standardize the physical parameter values ​​(Pi) of each candidate cable (e.g., convert them to dimensionless values ​​between 0 and 1, or compare them with the benchmark requirements to obtain a score).

[0081] (33) Calculate the composite score S = ∑(Wi × Pi). Theoretically, the higher the score, the more suitable the cable is for the application scenario.

[0082] The Analytic Hierarchy Process (AHP) constructs a judgment matrix to compare the importance of each physical parameter pairwise, thereby determining the weights. Then, it evaluates the performance of each candidate solution under each parameter, ultimately obtaining a comprehensive ranking.

[0083] The Technique for Order Preference by Similarity to Ideal Solution (TOPSIS) ranks the candidate solutions by calculating the distances between each candidate solution and the "positive ideal solution" (where all parameters are optimal) and the "negative ideal solution" (where all parameters are worst).

[0084] Example of an integration rule driven by "application logic":

[0085] Example 1: Signal transmission cables for scientific instruments deployed outside spacecraft that need to withstand significant temperature changes and space radiation environments.

[0086] The application logic emphasizes: flexibility at low temperatures, resistance to thermal cycling fatigue, resistance to radiation aging, low gas release (to avoid contaminating optical lenses), and signal transmission stability.

[0087] Integration rules: In the weighted scoring model, the above parameters are given extremely high weights. At the same time, strict "rejection" thresholds may be set, such as directly eliminating the model if the vacuum release performance value exceeds a certain limit.

[0088] Example 2: Flexible waveguide cable for connecting a high-power traveling wave tube amplifier.

[0089] The application logic emphasizes: high power carrying capacity, low insertion loss, good electromagnetic shielding effectiveness, and phase stability at operating temperature.

[0090] Integration criteria: Focus on evaluating parameters related to electrical performance and thermal management. Preliminary electro-thermal coupling analysis may be required to predict operating temperature rise and the resulting performance changes.

[0091] This step emphasizes iterative processes. During integration, it may be discovered that some parameters were initially insufficiently quantified, or that there are potential conflicts between different parameters (for example, a material with excellent radiation resistance may have a large gas release). In such cases, it may be necessary to return to step two to re-evaluate or supplement the parameters, or even, in extreme cases, re-examine whether some constraints in the "application logic" in step one are too idealistic or whether there are unidentified key factors.

[0092] Step 4: Generate a comprehensive physical property profile and analysis report

[0093] This step is to document the analysis process and results. This report will serve as an important technical document to support subsequent decision-making. The generated report should include at least the following: (41) Summary of the input “Application Logic Characteristic Profile”: Clearly describe the target application scenario, main environmental stresses, and functional requirements of the analyzed cable. (42) List of key physical parameters and their quantitative results: List all physical parameters selected as the basis for evaluation and their specific values, test conditions, or reference standards. (43) Description of the integration method used: Detail the specific techniques used, such as weighted scoring, MCDA, or model-based evaluation, and explain the basis for determining the weighting factors or evaluation rules. (44) Comprehensive physical property profile: This is the core output, which can be a series of tables, charts, comprehensive scores, ranking results, etc. (45) Risk assessment and trade-off analysis: Point out the potential performance risks of the evaluated cable under the current application logic, and the trade-offs between different performance indicators. (46) Conclusions and recommendations: Clearly state the conclusions on the suitability of the cable and provide specific recommendations for subsequent design optimization, laying precautions, or further special tests.

[0094] Optionally, the method also includes step five: applying the analysis output to guide design, laying, and simulation analysis results. The value of these results ultimately lies in their guiding role in actual engineering activities.

[0095] Guidance on cable design and material selection: Based on comprehensive physical property data, scientifically select materials, including copper layer thickness, insulation material and thickness, whether a shielding layer structure and material are required, and outer coating or protective materials. Scientifically design flexible integrated cable structures, optimizing the number of cable layers, copper layer routing, shielding or outer protective layer placement, overall diameter, and weight.

[0096] Optimize cable laying process: Based on the analysis results of cable bending performance under specific temperature and stress conditions, formulate detailed installation operation specifications, such as minimum allowable bending radius, maximum allowable installation tension, recommended fixing point type and spacing, wiring path planning to avoid stress concentration, and special protective measures in specific areas (such as near vibration sources).

[0097] Provides high-confidence input for simulation analysis: provides validated material constitutive model parameters relevant to specific application scenarios for cable thermal stress analysis, mechanical stress-strain analysis, vibration response analysis, etc.; provides accurate thermophysical parameters (such as thermal conductivity, specific heat capacity, emissivity, etc.) for cable Joule heat calculation, heat conduction and heat radiation analysis; and provides more reliable electromagnetic characteristic parameters for cable crosstalk analysis, shielding effectiveness evaluation, etc.

[0098] The implementation of this method is not a static, linear process. In practical applications, feedback and iteration may occur between the steps. For example, in step three, "integrating physical parameters," if it is found that none of the candidate cables meet a certain key application logic requirement, it may be necessary to return to step two to consider introducing new materials or modifying existing materials to obtain better parameter values; or, in extreme cases, it may even be necessary to consult with the system designer to adjust some overly stringent or unrealistic indicators in the "application logic characteristic profile" of step one. This iteration ensures the flexibility of the analysis process and the applicability of the final results.

[0099] Meanwhile, this method's framework exhibits excellent scalability. For non-critical applications or the initial screening stage, a relatively simplified integration model (such as a basic weighted scoring method) can be used. However, for mission-critical cables or applications facing extremely complex environments, more sophisticated coupled multiphysics modeling and simulation analysis techniques can be introduced in step three to obtain deeper performance insights. This scalability allows the method to adapt to different levels of analysis needs and resource allocation. This method not only addresses the current pain points in cable analysis but also provides fundamental data support and methodological guidance for future more intelligent spacecraft design and verification systems.

[0100] This embodiment also provides a physical property analysis system for flexible integrated cables used in spacecraft. The system includes: a first module for dividing different operating areas inside the spacecraft and determining the application scenario corresponding to each operating area; for each application scenario, obtaining an application logic characteristic profile of the cable; a second module for obtaining the key physical performance parameters of the cable; a third module for integrating the key physical performance parameters of the cable according to the application logic characteristic profile of the cable to obtain an integrated analysis result; and a fourth module for generating a comprehensive physical property profile and analysis report based on the integrated analysis result.

[0101] This embodiment improves the accuracy of design and selection: making the design and selection of flexible integrated cables more targeted, and can be optimized according to the specific application requirements on spacecraft, effectively avoiding on-orbit risks caused by insufficient performance, or cost and weight waste caused by excessive performance.

[0102] This embodiment enhances the reliability of the laying process: by providing physical property analysis data based on actual working conditions, it provides a scientific basis for cable laying processes (such as bending radius control, fixing method selection, etc.), thereby minimizing potential damage during installation and ensuring long-term stable operation of the cable.

[0103] This embodiment improves the fidelity of simulation analysis by providing various simulation software (such as finite element analysis, thermal analysis, electromagnetic analysis, etc.) with input parameters that are closer to actual application scenarios and have undergone comprehensive evaluation, thereby significantly improving the accuracy and predictive ability of simulation results.

[0104] This embodiment promotes the widespread application of flexible integrated cables: by establishing a systematic and scientific physical property analysis and evaluation system, it enhances the confidence of engineers in using flexible integrated cables in complex and harsh aerospace environments, and helps to promote their popularization and in-depth application in more types of aerospace missions with higher requirements.

[0105] This embodiment offers the potential for shortening the R&D cycle and controlling costs: By more accurately evaluating and selecting cables in the early stages of design, potential risk points can be effectively identified, reducing later design changes, repeated testing, and verification work, thereby potentially shortening the overall R&D cycle and controlling project costs.

[0106] This embodiment enhances the overall reliability of space missions: ensuring that the cable system, which serves as the "nerves" and "blood vessels" of a spacecraft, can operate reliably within its expected service environment and lifespan is an important guarantee for improving the success rate of the entire space mission.

[0107] The core of this embodiment lies in its systematic integration capability. It is not merely a simple set of physical parameters, but rather forms a decision support framework. Through parameter integration based on "application logic" in step three, engineers can make scientific trade-offs among numerous performance indicators, thereby making optimal decisions. This structured decision-making process transforms what might have relied on experience-based judgment into a quantifiable and traceable analytical process.

[0108] Furthermore, the output of this embodiment is not isolated, but closely linked to and serves the entire lifecycle of the cable from conceptual design to on-orbit application. Accurate physical property analysis results in the early stages will directly improve the quality and efficiency of subsequent design, laying, and simulation verification processes, demonstrating its integrated and value-adding capabilities throughout the entire engineering process.

[0109] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A method of analyzing physical properties of a flexible integrated cable for a spacecraft, characterized by The application relates to a method for analyzing the application logic of cables in spacecrafts. The method comprises the following steps: dividing different operation areas in the spacecraft to determine the application scenarios of each operation area; obtaining the application logic characteristic files of the cables for each application scenario; obtaining the key physical performance parameters of the cables; integrating the key physical performance parameters of the cables according to the application logic characteristic files of the cables to obtain integration analysis results; 2. The method of claim 1, wherein: generating comprehensive physical property characteristic files and analysis reports according to the integration analysis results.

3. The method according to claim 2, wherein: The different operation areas in the spacecraft include an external exposure area, a propulsion cabin section, a payload cabin and an avionics cabin. The application scenario of the external exposure area is facing severe temperature cycles, high vacuum, strong ultraviolet radiation, charged particle radiation and atomic oxygen erosion; The application scenario of the propulsion cabin section is bearing high temperature, strong vibration and impact; The application scenario of the payload cabin is having strict requirements on outgassing to avoid polluting sensitive surfaces, and the micro-vibration and electromagnetic compatibility must meet preset high requirements; 4. The method according to claim 3, wherein: The application scenario of the avionics cabin is a temperature-controlled environment, but the device density is high, the electromagnetic environment is complex, and the electromagnetic shielding performance and heat dissipation performance of the cable have preset requirements.

5. The method according to claim 4, wherein: The application logic characteristic files of the cables include thermal environment characteristics, mechanical environment characteristics, radiation environment characteristics, electromagnetic environment characteristics, vacuum environment characteristics and function criticality levels. The thermal environment characteristics include the maximum working temperature, the minimum working temperature, the temperature change rate, the thermal cycle number, the continuous high / low temperature time, the main heat source is solar radiation, device heat or external heat flow; The mechanical environment characteristics include the vibration frequency spectrum, the impact spectrum, the acceleration overload, the amplitude and frequency of the continuous bending / twisting load during the launch stage and the on-orbit operation stage, and the allowable tensile force during the installation process; The radiation environment characteristics include the total ionizing dose, the displacement damage dose, the risk assessment of single particle effect, and the radiation particle type and radiation particle spectrum; wherein the radiation particle type includes protons, electrons and heavy ions; The electromagnetic environment characteristics include the electromagnetic interference source frequency and intensity, and the sensitivity threshold of the cable itself or the connected device to electromagnetic interference; The vacuum environment characteristics include the vacuum degree and the specific limit requirement of material outgassing; 6. The method of claim 1, wherein: The function criticality level includes the potential impact of cable failure on the spacecraft mission, safety or service life.

7. The method according to claim 6, wherein: The key physical performance parameters of the cables include mechanical performance parameters, thermal performance parameters, electrical performance parameters and environmental adaptability parameters. The mechanical performance parameters include tensile strength, elongation at break, minimum bending radius, material flexibility, bending fatigue life, vibration fatigue life, wear resistance and compressive strength; The thermal performance parameters include the upper and lower limits of the working temperature, thermal conductivity, thermal expansion coefficient, material flame retardant grade and performance retention ability after experiencing rapid or multiple thermal cycles; The electrical performance parameters include rated current-carrying capacity, rated voltage, insulation resistance, dielectric strength, signal transmission integrity parameters, electromagnetic compatibility and electromagnetic interference shielding effectiveness; The environmental adaptability parameters include vacuum outgassing characteristics, radiation resistance, atomic oxygen erosion resistance and high / low temperature resistance.

8. The method of claim 1, wherein: In the integrated analysis result of the key physical performance parameters of the cable according to the application logic characteristic profile of the cable, a weight factor is given to each key physical performance parameter according to the application logic characteristic profile of the cable; a comprehensive score of the cable is obtained according to the value of each key physical performance parameter and the weight factor corresponding to each key physical performance parameter.

9. The method of claim 1, wherein: The comprehensive physical property characteristic profile and the analysis report include the input application logic characteristic profile abstract, the list of key physical performance parameters and the quantitative results thereof, the comprehensive physical property characteristic profile, the risk assessment and trade-off analysis, the conclusion and suggestion; wherein, The input application logic characteristic profile abstract includes: clearly describing the target application scene of the analyzed cable, the main environmental stress and the functional requirements; The list of key physical performance parameters and the quantitative results thereof include: listing all the selected key physical performance parameters and their specific values, test conditions or reference standards for evaluation; The comprehensive physical property characteristic profile is a series of comprehensive scores, risk level assessments and achievement degrees of key performance indicators, which are visually displayed in the form of charts; The risk assessment and trade-off analysis includes: evaluating the possible performance risk points of the cable, and considering the trade-off between different performance indicators; The conclusion and suggestion includes: giving the conclusion about the cable applicability, and giving specific suggestions for subsequent design optimization, laying considerations or special tests that need to be further carried out.

10. A flexible integrated cable property analysis system for spacecraft, characterized by including: The first module is used to divide different operation areas inside the spacecraft, and determine the application scene corresponding to each operation area; For each application scene, the application logic characteristic profile of the cable is obtained; The second module is used to obtain the key physical performance parameters of the cable; The third module is used to integrate the key physical performance parameters of the cable according to the application logic characteristic profile of the cable to obtain an integrated analysis result; The fourth module is used to generate a comprehensive physical property characteristic profile and an analysis report according to the integrated analysis result.

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