WO2024099010A1 - Procédé et système d'évaluation de risque de charge interne de diélectriques d'engin spatial sur orbite synchrone, et terminal - Google Patents

Procédé et système d'évaluation de risque de charge interne de diélectriques d'engin spatial sur orbite synchrone, et terminal Download PDF

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WO2024099010A1
WO2024099010A1 PCT/CN2023/123567 CN2023123567W WO2024099010A1 WO 2024099010 A1 WO2024099010 A1 WO 2024099010A1 CN 2023123567 W CN2023123567 W CN 2023123567W WO 2024099010 A1 WO2024099010 A1 WO 2024099010A1
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medium
electric field
sample
model
electron
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PCT/CN2023/123567
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Chinese (zh)
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尚鹏辉
马雪娟
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电子科技大学长三角研究院(湖州)
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Publication of WO2024099010A1 publication Critical patent/WO2024099010A1/fr

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  • the present invention belongs to the technical field of spacecraft dielectric internal charging protection, and in particular relates to a method, system and terminal for assessing the risk of dielectric internal charging in a synchronous orbit spacecraft.
  • dielectric internal charging will cause the insulation of polymer dielectrics to deteriorate or even fail.
  • electrostatic discharge pulses generated by the dielectric internal charging will also cause abnormal operation or damage of sensitive electronic devices in the spacecraft, seriously threatening the operation safety of the spacecraft.
  • higher requirements are placed on the anti-internal charging performance of dielectric materials.
  • the research on the deep charge and discharge problem of dielectrics mainly adopts the method of numerical calculation.
  • the interaction process between high-energy electrons and dielectrics in a set radiation environment is simulated to obtain data such as charge deposition rate and dose rate in the dielectric; then, the equation group is solved based on the charge transport model inside the dielectric to calculate the distribution of electric field intensity in the dielectric under the corresponding radiation time; finally, by comparing the maximum value of the electric field intensity in the dielectric with the dielectric electrostatic discharge breakdown threshold, it is evaluated whether the sample will have electrostatic discharge problems under the set radiation conditions. This will further guide the shielding design of spacecraft and select the optimal shielding thickness according to the calculation results to protect the deep charge and discharge of the dielectric.
  • the existing technology lacks a solution for analyzing the deep charge and discharge mechanism of dielectrics under the combined effects of high-energy electron radiation and high working voltage.
  • the corresponding charge and discharge mechanism and characteristics are unclear, and the effectiveness and applicability of traditional dielectric doping and modification methods are unknown, and there is no feasible calculation method.
  • it is necessary to comprehensively consider the actual working conditions such as spacecraft shielding factors, dielectric grounding methods, and working voltage to comprehensively evaluate the anti-internal charging performance of spacecraft dielectrics under electron radiation, which is lacking in current research.
  • the present invention provides a method for assessing the risk of internal electrification in a synchronous orbit spacecraft medium, and in particular, relates to a method for assessing the risk of internal electrification in a geosynchronous orbit spacecraft medium.
  • the present invention is implemented as follows: a method for assessing the risk of internal electrification of a medium in a synchronous orbit spacecraft, the method comprising:
  • a geosynchronous orbit (GEO) environmental electron flux model is constructed; then, the GEO electron flux calculated by the geosynchronous orbit environmental electron flux model is introduced into the Monte Carlo simulation software Geant4 to simulate the dielectric electron radiation process; the shielding factor is comprehensively considered to obtain the two key factors of the internal charge deposition rate and dose rate of the dielectric under different shielding under GEO environmental electron radiation; then, the dielectric parameters of the dielectric are measured, a three-dimensional charge transport model is constructed, and then the corresponding three-dimensional charge transport model equation group is constructed in combination with the working voltage and the grounding method of the sample; then, the finite element method is used to solve the corresponding three-dimensional charge transport equation group to obtain the internal electric field strength distribution of the dielectric under the corresponding working condition; by comparing the maximum value of the internal electric field strength with the breakdown strength field of the dielectric measured by the experiment, it can be judged whether there is an electrostatic discharge risk under the corresponding working condition; finally, according to the judgment result, the shielding layer material or thickness is adjusted and the calculation
  • the method for assessing the risk of internal electrification of a geostationary orbit spacecraft medium includes the following steps:
  • Step 1 Construction of the geosynchronous orbit environment electron flux model
  • Step 2 constructing a calculation model of the electric field in the medium under electron radiation
  • Step 3 Risk assessment of dielectric electrostatic discharge under electronic radiation.
  • step 1 Furthermore, the construction of the geosynchronous orbit environment electron flux model in step 1 includes:
  • the FLUMIC3 (Flux Model for Internal Charging) model is used to construct the electron flux environment of the synchronous orbit:
  • the outer radiation belt model in the FLUMIC3 energy spectrum model is as follows: taking into account the solar cycle and annual variations, the outer radiation belt L > 2.5, and the electron flux will be a function of fsc , foy , L and E ;
  • fsc represents the normalized value of the solar activity cycle, which is 0 in the year of minimum solar activity.
  • foy represents the normalized value of the date in a year, with January 1 as the starting point.
  • L is the distance to the center of the Earth.
  • step 2 Furthermore, the construction of the calculation model of the electric field in the medium under electron radiation in step 2 includes:
  • the simulation of the electron radiation process in step (1) includes:
  • the result calculated by the FLUMIC3 model is the integrated flux of electrons in the GEO environment.
  • the electron integrated flux is converted to the vertical direction.
  • the electrons are set to be incident perpendicular to the sample plane.
  • the electron source is set to a circular plane source with a radius of 6 cm, which is placed 20 cm to the left of the sample and incident perpendicular to the sample surface from left to right.
  • the electrons are set to be emitted in the energy spectrum sampling mode.
  • the number of simulated incident electrons is 3 ⁇ 106 .
  • the virtual radiation time T is: s;
  • e q is the electron charge, which is set to 1.6 ⁇ 10 -19 C; the charge deposition rate in the medium under the actual beam current is: C/m 3 ⁇ s;
  • the dose rate in the medium is: rad/s;
  • step (2) Furthermore, the process of calculating the electric field in the medium under electron radiation in step (2) includes:
  • the charge transport equations are Poisson's equation, current continuity equation and Ohm's law from top to bottom.
  • E is the electric field strength, V/m; is the net charge density in the medium, C/m 3 ; ⁇ is the dielectric constant of the medium, F/m; J is the net current density, A/m 2 ; is the charge deposition rate in the medium, C/m 3 ⁇ s; is the conductivity related to the electric field, S/m.
  • the conductivity of the sample is segmented and fitted according to the size of the electric field strength. From the test data, when the electric field strength is less than 1kV/mm, the conductivity does not change significantly with the electric field, and it is set as a low field area. In the low field area, the intrinsic conductivity of the sample is used; when the field strength is greater than 1kV/mm, the conductivity will increase with the increase of the electric field strength.
  • the area is divided into two parts with the nonlinear conductivity threshold as the dividing point, where the electric field from 1kV/mm to the mutation point threshold is set as a low growth rate area, and after the mutation point is set as a nonlinear growth area.
  • the overall design is as follows: .
  • the electric field calculation model adopts the charge transport model, and the conductivity of the sample is processed by segmented fitting based on the test data.
  • the charge transport model is solved by COMSOL software based on the finite element method, and the partial differential equation interface in the mathematical module is used to customize the equations to be solved.
  • the coefficients of this partial differential equation and Poisson's equation are modified according to the charge transport model equations; the partial differential equation is: ; .
  • the specific working conditions are analyzed, including the grounding state, grounding position, amplitude of the working voltage and the applied position factors of the sample, corresponding to the initial state and boundary conditions of the partial differential equation group.
  • various initial states are set by modifying the initial conditions of the custom equations and adding Dirichlet boundary conditions.
  • Geant4 programming is used to simulate the electron radiation process according to the set radiation parameters, and then the charge deposition rate and dose rate at each position in the sample are introduced into the calculation model, and then imported into COMSOL using the interpolation method; the grounding conditions and working voltage are set according to the actual working conditions of the sample, and then the sample model is meshed and the radiation time is set; the MUMPS type solver based on LU decomposition is selected for solution calculation, and finally the internal electric field distribution of the sample within the set radiation time under the actual working conditions is obtained.
  • the risk assessment of dielectric electrostatic discharge under electronic radiation in step 3 includes:
  • the modified sample was subjected to a DC withstand voltage test using a breakdown test platform.
  • the test electrode was a ball-ball electrode placed in insulating oil.
  • the test data was processed using the Weibull distribution method, and the formula is as follows: ;
  • P ( E ) is the probability of cumulative failure
  • E is the breakdown strength
  • ⁇ is the shape parameter, which is used to evaluate the dispersion of the breakdown voltage
  • Eb is the breakdown field strength when the breakdown probability is 63.28%, which is called the characteristic breakdown field strength.
  • the shielding layer design is readjusted; in step 1, the shielding layer material or thickness is adjusted for simulation calculation, and then the electric field inside the medium is calculated, and finally the electrostatic discharge risk of the medium is evaluated; through multiple adjustments and repeated calculations until the maximum value of the internal electric field strength of the medium under the set electron radiation conditions is less than the breakdown field strength of the medium, the shielding design is taken as the safe shielding threshold, and the shielding layer thickness or shielding material density is taken as the minimum requirement.
  • Another object of the present invention is to provide a synchronous orbit spacecraft medium electrification risk assessment system using the synchronous orbit spacecraft medium electrification risk assessment method, the synchronous orbit spacecraft medium electrification risk assessment system comprising:
  • the dielectric electron radiation module simulation is used to build the geosynchronous orbit environment electron flux model.
  • the calculated GEO electron flux is introduced into Geant4 to simulate the dielectric electron radiation process.
  • the electric field intensity distribution determination module is used to construct a three-dimensional charge transport model equation group, and use the finite element method to solve the corresponding three-dimensional charge transport equation group to obtain the electric field intensity distribution in the medium under the corresponding working conditions;
  • the electrostatic discharge risk assessment module is used to compare the maximum internal electric field strength with the breakdown strength field of the medium to determine whether there is an electrostatic discharge risk under the corresponding working conditions.
  • Another object of the present invention is to provide a computer device, which includes a memory and a processor, wherein the memory stores a computer program, and when the computer program is executed by the processor, the processor executes the steps of the method for assessing the risk of electrical charges in a synchronous orbit spacecraft medium.
  • Another object of the present invention is to provide a computer-readable storage medium storing a computer program.
  • the processor executes the steps of the method for assessing the risk of electrical charges in a synchronous orbit spacecraft medium.
  • Another object of the present invention is to provide an information data processing terminal, which is used to implement the above-mentioned risk assessment system for the charged medium in a synchronous orbit spacecraft.
  • the present invention proposes a dielectric internal charge risk assessment method suitable for geosynchronous orbit spacecraft.
  • This method comprehensively considers the actual working conditions such as the synchronous orbit electron radiation environment, spacecraft shielding factors, and operating voltage to comprehensively evaluate the electrostatic discharge risk of spacecraft dielectrics and the modification effect of the doping modification scheme for its anti-internal charge performance, thereby providing a feasible calculation verification method for spacecraft shielding design and optimization and doping modification of spacecraft dielectrics.
  • the present invention aims at the problem of internal charge risk assessment of spacecraft media, especially spacecraft media operating in geosynchronous orbit, and comprehensively considers the current development needs of high-voltage and high-power spacecraft, and proposes a dielectric internal electric field calculation scheme and internal charge risk assessment scheme under the combined effect of working voltage and spacecraft electronic radiation environment.
  • this scheme takes into account the research needs of spacecraft dielectric doping modification, and provides a comparative evaluation calculation method for the modified dielectric's anti-internal charge performance.
  • This patent provides a feasible solution for the internal charge risk assessment and shielding design of high-voltage and high-power spacecraft on geosynchronous orbit, and is also suitable for providing a feasible calculation verification scheme for the design of improving the dielectric's anti-internal charge performance from the perspective of dielectric material modification, which is technologically advanced.
  • FIG1 is a flow chart of a method for assessing the risk of internal electrification in a geostationary orbit spacecraft medium provided by an embodiment of the present invention
  • FIG2 is a schematic diagram of an overall technical solution of a method for assessing the risk of internal electrification in a synchronous orbit spacecraft medium provided by an embodiment of the present invention
  • FIG. 3 is a schematic diagram showing the variation of GEO electron integrated flux with fo y and fsc according to an embodiment of the present invention
  • FIG4 is a schematic diagram showing a comparison between the calculated value of the GEO orbit electron integrated flux calculated by the FLUMIC3 model provided in an embodiment of the present invention and the “worst case recommended by NASA”;
  • FIG. 5 is a schematic diagram of a simulation of dielectric electron radiation in a GEO environment and a simulation diagram of an electron radiation process in Geant4 provided by an embodiment of the present invention
  • FIG7 is a fitting diagram of segmented conductivity test results of two polyimide (PI) samples provided in an embodiment of the present invention
  • FIG. 8 is a schematic diagram of the DC breakdown field strength test results (Weibull distribution) of micro- and nano-zinc oxide-modified polyimide samples provided in an embodiment of the present invention
  • FIG. 9 is a schematic diagram of a method for applying a working voltage to a polyimide (PI) sample provided in an embodiment of the present invention.
  • FIG. 10 is a calculation result of the maximum value of the internal electric field strength of a polyimide sample under a GEO electron radiation environment at different aluminum shielding layer thicknesses and different operating voltages provided by an embodiment of the present invention.
  • the present invention provides a method, system and terminal for assessing the risk of internal charging in a synchronous orbit spacecraft medium.
  • the present invention is described in detail below with reference to the accompanying drawings.
  • the method for assessing the risk of internal electrification of a medium in a synchronous orbit spacecraft comprises the following steps:
  • S102 comprehensively analyze shielding factors and find out the key factors of internal charge deposition rate and dose rate of the medium under different shielding conditions under GEO environmental electron radiation;
  • the method for assessing the risk of internal electrification in a synchronous orbit spacecraft medium specifically includes the following steps:
  • a sufficiently accurate GEO environment electron flux model is first required. Since the occurrence of electrostatic discharge is usually related to the enhancement of the electron flux in the space environment, the standard average flux model AE8 is no longer applicable, and a model that takes flux enhancement into account is needed.
  • the FLUMIC model was built to meet this demand. It is an empirical model built based on actual observational data and has been updated to the third generation, FLUMIC3. It updates the outer belt model based on observational data from satellites such as GEOS/SEM and STRV-1b/REM and models the electron flux in the inner radiation belt. It takes into account the seasonal and annual changes in the high-energy electron flux and constructs high-energy electron flux enhancement events. It is currently the most accurate model for describing the electron flux in the GEO environment.
  • the outer radiation belt model in the FLUMIC energy spectrum model is as follows:
  • the electron flux will be a function of fsc , foy , L and E :
  • fsc represents the normalized value of the solar activity cycle, which is 0 in the year of solar minimum activity.
  • foy represents the normalized value of the date in a year, with January 1 as the starting point.
  • L is the distance to the center of the Earth.
  • the present invention calculates the variation of electron flux greater than 2 MeV with foy and fsc in the GEO environment, and the results are shown in FIG3 .
  • This scheme uses an electron radiation program developed based on Geant4 to simulate the interaction process between high-energy electrons and samples.
  • the overall model is shown in Figure 5.
  • Step 1 Construct the sample model and shielding layer model
  • a disc sample model with a diameter of 10 cm and a thickness of 1 mm is constructed based on the actual size of the polyimide (PI) sample. The whole is placed in a vacuum environment. Considering the actual situation, a shielding layer is constructed 10 cm to the left of the sample.
  • the shielding layer material is aluminum, with a size of 15 cm ⁇ 15 cm, and the thickness can be parameterized and adjusted according to the actual situation.
  • Step 2 Construct an electron radiation source model and calculate relevant radiation parameters
  • the result calculated by the FLUMIC3 model introduced in Scheme 1 is the integrated flux of electrons in the GEO environment.
  • the electrons are set to be incident perpendicular to the sample plane, so the integrated flux of electrons needs to be converted to the vertical direction first.
  • the electron source is set to a circular plane source with a radius of 6 cm, placed 20 cm to the left of the sample, and incident perpendicular to the sample surface from left to right.
  • the electrons are set to be emitted in an energy spectrum sampling mode; the number of simulated incident electrons is 3 ⁇ 10 6.
  • the circular lines in Figure 5 represent the trajectory of the incident electrons, and the square lines represent the trajectory of the photons excited during the collision process.
  • the sample model is set as a detector and divided into 100*100*10 volume elements to collect and record the charge deposition and energy deposition data at each position during the radiation process.
  • Step 3 Calculation result processing
  • the calculation result needs to be converted to a specific beam current density to obtain the corresponding charge deposition rate in the sample under the corresponding radiation conditions ( ) and dose rate ( )distributed.
  • the conversion method is as follows:
  • e q is the electron charge (1.6 ⁇ 10 -19 C), which corresponds to the charge deposition rate in the medium under the actual beam current: (C/m 3 ⁇ s)
  • the dose rate in the medium is: (rad/s)
  • the charge deposition characteristics of the medium in the actual space radiation environment are quite different from the monoenergetic electron incidence results. It is no longer deposited at a specific depth, but is dispersed at different depths inside the medium. This is because the initial energy and beam density of the electrons contained in the actual environment are different. Electrons of different energies experience energy loss and transfer during the interaction with the dielectric material, and will eventually be deposited at different depths of the sample. In this way, the distribution of electrons in the sample appears to be more dispersed and random, and the charge accumulation may be more concentrated in some areas.
  • Step 1 Constructing the charge transport equation in the medium
  • E is the electric field strength, V/m (the quantity to be determined); is the net charge density in the medium, C/m 3 , (to be determined); ⁇ is the dielectric constant of the medium, F/m, (using the test result in step 1); J is the net current density, A/m 2 , (to be determined); is the charge deposition rate in the medium, C/m 3 ⁇ s; is the conductivity related to the electric field, S/m.
  • this scheme proposes a segmented conductivity calculation method based on the measured data of the dielectric, mainly based on the nonlinear conductivity characteristics measurement data of the modified sample.
  • This scheme will perform segmented fitting of the conductivity of the sample according to the measured conductivity data and the size of the electric field strength. From the experimental data, it is found that when the electric field strength is less than 1kV/mm, the conductivity does not change significantly with the electric field, which is set as the "low field zone” here.
  • the intrinsic conductivity of the sample measured is used in the low field zone; when the field strength is greater than 1kV/mm, the conductivity will increase with the increase of the electric field strength.
  • This area is divided into two parts with the nonlinear conductivity threshold as the dividing point, where the electric field from 1kV/mm to the mutation point threshold is set as the "low growth rate zone", and the area after the mutation point is set as the "nonlinear growth zone".
  • the conductivity related to the electric field is divided into three sections.
  • the overall design is as follows:
  • Step 2 Calculation process of the electric field inside the medium
  • the electric field calculation model adopts the charge transport model given in step 1, in which the conductivity of the sample is processed by segmented fitting based on the test data.
  • the charge transport model is solved by COMSOL software based on the finite element method. Since the transport equation needs to be modified and reconstructed according to the fitting parameters, the present invention does not use the inherent module given in COMSOL to calculate the electric field, but uses the partial differential equation interface in the mathematical module to define the set of equations to be solved.
  • the present invention uses a general form of partial differential equations, and its specific structure is as follows:
  • the specific working conditions that need to be considered in the simulation calculation process of the present invention mainly include the grounding state and grounding position of the sample, the amplitude of the working voltage, the applied position and other factors, which correspond to the initial state and boundary conditions of the partial differential equation group.
  • various initial states can be set by modifying the initial conditions of the custom equations and adding Dirichlet boundary conditions.
  • Geant4 programming it is necessary to first use Geant4 programming to simulate the electron radiation process according to the set radiation parameters, and then introduce the two key parameters of charge deposition rate and dose rate at each position in the sample into the calculation model.
  • the present invention uses the interpolation method to import them into COMSOL. Then, the grounding conditions and working voltage are set according to the actual working conditions of the sample, and then the sample model is meshed, the radiation time is set, and the MUMPS type solver based on LU decomposition is selected for solution calculation, and finally the internal electric field distribution of the sample within the set radiation time under the actual working conditions can be obtained.
  • Step 1 Calculate the maximum electric field intensity in the medium under the corresponding electron radiation scenario through schemes 1 and 2.
  • Step 2 Determine the DC breakdown field strength of the sample.
  • This scheme uses a breakdown test platform to carry out a DC withstand voltage test on the modified sample.
  • the test electrode is a ball-to-ball electrode, which is placed in insulating oil to prevent surface flashover.
  • test data was processed using the Weibull distribution method, and the formula is as follows:
  • P ( E ) is the probability of cumulative failure
  • E is the breakdown strength
  • ⁇ is the shape parameter, which can be used to evaluate the dispersion of the breakdown voltage
  • E b is the breakdown field strength when the breakdown probability is 63.28%, called the characteristic breakdown field strength.
  • the shielding layer design needs to be readjusted.
  • the shielding layer material or thickness can be adjusted in Scheme 1 for simulation calculation, and then the electric field inside the medium is calculated by the method in Scheme 2, and finally the electrostatic discharge risk of the medium is evaluated by the method in Scheme 3. Multiple adjustments and repeated calculations can be performed until the maximum value of the internal electric field strength of the medium is less than the breakdown field strength of the medium under the set electron radiation conditions.
  • the shielding design at this time is taken as the safe shielding threshold, that is, the shielding layer thickness or shielding material density at this time is the minimum requirement.
  • the dielectric electron radiation module simulation is used to build the geosynchronous orbit environment electron flux model.
  • the calculated GEO electron flux is introduced into Geant4 to simulate the dielectric electron radiation process.
  • the electric field intensity distribution determination module is used to construct a three-dimensional charge transport model equation group, and use the finite element method to solve the corresponding three-dimensional charge transport equation group to obtain the electric field intensity distribution in the medium under the corresponding working conditions;
  • the electrostatic discharge risk assessment module is used to compare the maximum internal electric field strength with the breakdown strength field of the medium to determine whether there is an electrostatic discharge risk under the corresponding working conditions.
  • the scheme of the present invention is used to calculate the maximum value of the electric field in the polyimide sample under the geosynchronous orbit electron radiation environment when the aluminum shielding thickness is 0 to 5 mm and the working voltage is 100 V, 500 V, 1000 V, 2000 V, 3000 V, and 5000 V, wherein the voltage application method is shown in FIG9 .
  • the electrostatic discharge threshold is set to 2 ⁇ 10 7 V/m
  • the minimum required aluminum shielding thickness should be 2 mm; for more demanding environments, if 1 ⁇ 10 7 V/m is used as the assessment threshold, the minimum required aluminum shielding thickness should be 4 to 5 mm.
  • the embodiments of the present invention can be implemented by hardware, software, or a combination of software and hardware.
  • the hardware part can be implemented using dedicated logic; the software part can be stored in a memory and executed by an appropriate instruction execution system, such as a microprocessor or dedicated design hardware.
  • an appropriate instruction execution system such as a microprocessor or dedicated design hardware.
  • the above-mentioned devices and methods can be implemented using computer executable instructions and/or contained in a processor control code, such as a carrier medium such as a disk, CD or DVD-ROM, a programmable memory such as a read-only memory (firmware), or a data carrier such as an optical or electronic signal carrier.
  • a processor control code such as a carrier medium such as a disk, CD or DVD-ROM, a programmable memory such as a read-only memory (firmware), or a data carrier such as an optical or electronic signal carrier.
  • a carrier medium such as a disk, CD or DVD-ROM
  • a programmable memory such as a read
  • the device and its modules of the present invention can be implemented by hardware circuits such as very large-scale integrated circuits or gate arrays, semiconductors such as logic chips, transistors, etc., or programmable hardware devices such as field programmable gate arrays, programmable logic devices, etc., can also be implemented by software executed by various types of processors, and can also be implemented by a combination of the above-mentioned hardware circuits and software, such as firmware.

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Abstract

La présente invention appartient au domaine technique de la prévention de la charge interne de diélectriques d'engins spatiaux. L'invention divulgue un procédé et un système d'évaluation de risque de charge interne de diélectriques d'engin spatial sur orbite synchrone, et un terminal. Le procédé consiste à : construire un modèle de flux d'électrons d'environnement d'orbite géosynchrone (GEO) ; simuler un processus de rayonnement d'électrons pour un diélectrique ; calculer les deux facteurs clés taux de dépôt de charges internes et débit de dose du diélectrique sous le rayonnement d'électrons d'environnement de GEO par rapport à différents blindages ; construire un modèle de transport de charges tridimensionnel, et, sur la base d'une tension de travail et du mode de mise à la masse d'un échantillon, construire un système d'équations de modèle de transport de charges tridimensionnel correspondant ; puis résoudre le système d'équations de transport de charges tridimensionnel correspondant en utilisant une méthode à éléments finis de façon à obtenir la distribution d'intensité de champ électrique interne du diélectrique sous la condition de travail correspondante ; estimer s'il existe un risque de décharge électrostatique sous la condition de travail correspondante ; et obtenir une solution de conception de blindage optimale n'ayant aucun risque de décharge électrostatique. Par conséquent, un procédé de calcul et de vérification faisable est fourni pour la conception et l'optimisation d'un blindage de véhicule spatial et la modification de dopage de diélectriques d'un engin spatial.
PCT/CN2023/123567 2022-11-11 2023-10-09 Procédé et système d'évaluation de risque de charge interne de diélectriques d'engin spatial sur orbite synchrone, et terminal WO2024099010A1 (fr)

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