237 results about "Space radiation" patented technology

The invention discloses a high-voltage cable partial discharge detection method and system, and the method comprises the steps: carrying out the simulation coupling of a cable and a radio frequency antenna in a target region, obtaining an output result of a coupled model, and enabling the output result to reflect the space radiation characteristics between the radio frequency antenna and the cable; the simulation operation result is extracted based on space radiation characteristics, and a coupling gap parameter and a radio frequency receiving coupling point set between a radio frequency antenna and a cable are obtained; according to a standard corresponding to the coupling gap parameter, screening the radio frequency receiving coupling point set to obtain a target radio frequency receiving coupling point so as to receive a partial discharge original signal; performing feature analysis on the partial discharge original signal by using a signal-to-noise stripping technology, and analyzing the constructed phase analysis partial discharge map to obtain a to-be-decomposed signal; and analyzing a to-be-decomposed signal through an empirical mode decomposition method, and inputting the trained partial discharge analysis model to obtain a partial discharge detection result so as to improve the accuracy of power equipment monitoring.

The invention provides a functional composite one-dimensional metal cavity slot array antenna, which belongs to the field of antennae, and comprises a feed cavity and a cover plate located at the top of the feed cavity, a plurality of groups of periodic intermediate-frequency anti-interference metal blocks and high-frequency anti-interference metal blocks are arranged in the feed cavity, and a radiation slot is formed in the cover plate. The polarization conversion structures are arranged on the two sides of the radiation slot in a stepped and open manner to form an undulating shape; an antenna array is also provided. An anti-interference periodic structure is embedded in the feed cavity, the antenna is endowed with anti-interference capacity in multiple different frequency bands, the polarization conversion structures are arranged on the two sides of the radiation slot in a stepped and open mode to form an undulating shape, an electromagnetic signal is input into the feed cavity, linearly polarized electromagnetic waves are radiated outwards through the radiation slot, and the antenna is formed. Linear polarization electromagnetic waves are decomposed into a group of orthogonal components with the same amplitude after passing through the polarization conversion structure, a 90-degree phase difference exists between the two components, circular polarization is formed to radiate towards the space, the polarization conversion structure is simple in structure and convenient to process, and the scattering characteristic of the antenna is improved.

The invention discloses a single event upset reinforced magnetic random access memory reading circuit, and belongs to the field of nonvolatile memories. Interlocked transistors are added on the basis of a traditional 6T reading circuit, meanwhile, a PMOS tube and an NMOS tube are introduced, and errors caused by the single event upset effect can be effectively corrected. The method has the following advantages that single event effect sensitive nodes are considered, zero upset nodes do not exist in the reinforcement method, meanwhile, 1 upset can be rapidly corrected, the single event upset resistance is higher, and the method can be used for reliable storage of data in the space radiation environment.

The invention relates to a method for the in-system calibration of gamma radiation detectors (15) of a positron emission tomograph (10), wherein the tomograph (10) has a receiving space (11) for introducing objects to be measured, around which the radiation detectors (15) are arranged, preferably in pairs opposite one another, with a defined position and orientation. According to the invention, the method comprises: introducing (103) an emission device (5) with a radioactive radiation source (7) into a reference position (R) within the receiving space (11), recording (105) coincidences between one or more pairs (15.1, 15.2) of the detectors (15), and - carrying out (107) virtual collimation, wherein determining (117) interaction positions (PI) comprises determining (119) an interaction depth (PI, T) within the detector (15.1) to be calibrated.

The invention discloses an earth space radiation zone environment modeling and calculating method based on a deep neural network, and belongs to the field of earth space radiation environment simulation modeling. Flux intensity training data and flux distribution training data are constructed based on the earth radiation band environment data; building a regression prediction network and a dichotomy network, optimizing the regression prediction network based on the flux intensity training data, and optimizing the dichotomy network based on the flux distribution training data to obtain a radiation band ion flux intensity model and a radiation band flux distribution model; a user inputs task emission information, and an input tensor is constructed based on the task emission information; inputting the input tensor into the radiation band ion flux intensity model and the radiation band flux distribution model to obtain two prediction tensors; and obtaining the environmental particle energy spectrum data of the earth radiation band based on the two prediction tensors.

The invention discloses a space radiant energy collection and conversion system, which relates to the technical field of energy conversion, and comprises a motor, a main shaft, a steam turbine, an expansion machine and a synchronous generator, a clutch I and a clutch II are respectively mounted on the main shaft on the right side of the motor and the left side of the steam turbine; and a transmission I, a transmission II and a transmission III are sequentially mounted on the main shaft between the clutch I and the clutch II. According to the space radiant energy collection and conversion system, energy sources are infinite, and radiant energy in air and water is utilized and is an inexhaustible energy source; the cost is extremely low: the cost of generating one kilowatt-hour can be reduced to one minute; the system does not depend on fossil fuel, and pollution of exhaust emission to the nature is avoided.

The invention discloses a reinforced p-GaN enhanced gallium nitride device resistant to single-particle burnout and a preparation method thereof, and mainly solves the problems that a gallium nitride device is prone to single-particle burnout in a space radiation environment and is insufficient in reliability. Comprising a substrate, a nucleating layer, a buffer layer, a channel layer, a barrier layer and a p-GaN cap layer which are sequentially grown on the substrate, a grid electrode formed by etching, and a mixed source electrode and a mixed drain electrode which are respectively formed by a plurality of deep embedded electrode regions and a plurality of surface contact electrode regions which are alternately arranged and are positioned on two sides of the grid electrode, wherein the deep embedded electrode region comprises a deep embedded source electrode and a deep embedded drain electrode and penetrates through the barrier layer and the channel layer, and the bottom of the deep embedded electrode region is in metal contact with the buffer layer; the surface contact electrode region comprises a conventional source electrode and a conventional drain electrode, and the bottom of the surface contact electrode region is in metal contact with the barrier layer or the channel layer. Accumulation of carriers in a channel region can be effectively inhibited, the single-particle burning resistance of the device is remarkably improved, and the performance of the device is improved.

The invention discloses a radiation detection system and a radiation detection method, and relates to the technical field of radiation detection. The radiation detection system comprises a power supply and a radiation detector, wherein a first end of the radiation detector is connected with the power supply; the particle counting circuit is connected with the second end of the radiation detector, and the particle counting circuit is used for collecting a first signal output by the radiation detector; the current integrating circuit and the particle counting circuit are connected with the second end of the radiation detector, and the particle counting circuit is used for collecting a second signal output by the radiation detector; the temperature sensor is used for collecting the temperature of the space where the radiation detector is located to obtain a temperature signal; the processor is connected with the particle counting circuit, the current integrating circuit and the temperature sensor and used for determining space radiation information of the space where the radiation detector is located according to the first signal, the second signal and the temperature signal. The detection range of the radiation detection system is expanded, and the application scene of the radiation detection system is expanded.

The invention relates to a terahertz high-power power amplifier assembly, which belongs to the field of electronic devices and comprises a synthesis network consisting of a synthesis network upper cavity and a synthesis network lower cavity, and a small signal amplification module, a medium-power amplification module, a driving-stage power amplifier module, a final-stage power amplifier module and a detection module are arranged on the back surface of the synthesis network lower cavity. An E-plane waveguide directional coupler is arranged in the synthesis network, the small signal amplification module, the medium-power amplification module, the driving-stage power amplification module, the final-stage power amplification module and the E-plane waveguide directional coupler are electrically connected in sequence, and a port of the E-plane waveguide directional coupler is electrically connected with the detection module; a waveguide tube is arranged in the installation position of each module in the synthesis network, and the modules are electrically connected through the waveguide tubes. According to the invention, each stage of amplifier is modularly designed, so that the isolation degree among devices of a link can be increased, and the self-excitation risk caused by space radiation is reduced. And the testability of a single module is improved, and the troubleshooting cost and time are reduced.

The invention relates to the technical field of system program storage of a controller, in particular to a satellite-borne dual-system program storage method and device capable of sharing a nonvolatile storage space. According to the technical scheme, the method comprises the following steps of: dividing a storage space of the nonvolatile memory into a first system program area, a second system program area and a sharing reserved area; the satellite-borne dual-system program storage can be upgraded independently, the program of the opposite side does not need to be compiled or adjusted again, the upgrading complexity and the testing cost are reduced, the dual-system program is solidified in a non-rewritable area, and the anti-radiation capacity is high; the shared reserved area is a dynamic allocation space during dual-system upgrading, storage waste caused by a traditional partition mode is avoided, and the requirement for flexibility of program version iteration is met; the first system directly runs in a non-volatile storage area, executable codes cannot be changed during system execution, and it is guaranteed that the satellite load basic communication function is not interrupted by the space irradiation environment; and the dual-system storage adapts to different hardware platforms.

A microstrip antenna, an antenna array, a radar, and a vehicle are provided. The microstrip antenna includes: a dielectric layer, and a metal layer and a ground plane layer disposed at two sides of the dielectric layer, wherein the metal layer includes a first radiation patch and a feeding portion; a length of a long side edge of the first radiation patch is determined based on an operating wavelength of the microstrip antenna, and a length of a short side edge of the first radiation patch is smaller than the length of the long side edge; the feeding portion is coupled between a center position of the long side edge of the first radiation patch and a short side edge, and the feeding portion is configured to transmit a high frequency signal to the first radiation patch or to transmit a space radiation signal received by the first radiation patch.

The invention relates to a gamma radiation field simulation method, a gamma radiation monitoring simulation training system and application of the gamma radiation field simulation method and the gamma radiation monitoring simulation training system, and a three-dimensional simulation gamma radiation field and the gamma radiation monitoring simulation training system are constructed based on the Beidou positioning technology, the computer and communication technology and the action law of gamma rays and substances. The simulation training system is composed of a guide center, a Beidou positioning and communication base station, a simulation training ground, a simulation gamma radioactive source and a simulation gamma radiation monitor. The parts of the system exchange information through wired or wireless communication. The simulated gamma radiation source and the simulated gamma radiation monitor both have an accurate positioning function, and the simulated gamma radiation monitor also has a function of calculating and obtaining a gamma radiation dose rate and a dose. The problem of simulation and monitoring simulation training of a space gamma radiation field generated by a plurality of real gamma radioactive sources is solved, so that the effects of simulation training such as searching for more than one gamma radioactive source, determining gamma radioactive contamination boundaries and measuring personal accumulated doses are close to reality.

The invention discloses a low-absorption high-emission thermal control coating resistant to an aerodynamic thermal environment and a preparation method of the low-absorption high-emission thermal control coating. The coating comprises a base material and a coating body. The coating is of a bottom surface layer structure, an organic silicon resin functional group modified phenyl methyl silicon resin component A and an organic silicon resin functional group modified phenyl methyl silicon resin component B serve as a binding agent, a resin component A comprises basic resin and a crosslinking catalyst, and a resin component B comprises basic resin and a crosslinking agent; the bottom surface layer structure comprises a bottom layer and a surface layer; mixed powder of boron nitride, aluminum oxide and hollow glass microspheres is used as filler in the bottom layer; zinc titanate powder and aluminum oxide whiskers are used as fillers in the surface layer. Aiming at various harsh working conditions such as maintaining a heat balance state required by the spacecraft in complex environments such as raining, high-temperature and high-speed pneumatic scouring, high-low temperature alternation and space radiation, the operation stability of a cabin of the spacecraft after experiencing various environments is improved, and the in-orbit space application environment requirements of the subsequent spacecraft are met.

The invention provides a memory error simulation method and device based on a satellite-borne intelligent computing system, a medium and a simulator, and relates to the technical field of satellites. The method comprises the following steps: inputting a deep learning neural network engine into a deep learning reasoning program of a satellite-borne intelligent computing system; executing a deep learning reasoning program to read a process page table; based on the DRAM standard file, the DRAM mapping file and the address mapping relation, determining a memory active area of the deep learning neural network engine in the virtual memory model; performing construction processing on the memory active area, constructing an error injection space represented in a bitmap tree form, and determining an error information injection position in the error injection space according to particle flipping error model information and a Monte Carlo random algorithm; and performing reverse translation processing on the physical address in the virtual memory model, and determining a target virtual address of the deep learning reasoning process. And a single-particle upset memory error and a multi-particle upset memory error caused by space radiation can be effectively simulated.

The invention discloses a target detection network radiation hardening method for a space spacecraft AI chip, and belongs to the technical field of neural network radiation resistance. The method comprises the following steps: acquiring a target detection network model; a Dropout enhancement model and an exponential bit quantization optimization model are adopted respectively; and carrying out target detection in a space environment by adopting the optimized model. According to the method, the robustness of the neural network in the space radiation environment can be remarkably improved, the reasoning precision and speed of the model can be kept, the problem of reliable operation of the deep learning model in the space environment is solved, and the stability and task success rate of a spacecraft intelligent system are optimized. Aiming at the problem of single event upset caused by high-energy particle radiation in a space environment, the invention provides a training-reasoning collaborative optimization strategy, and provides reliable guarantee for AI application on a spacecraft.

The invention relates to the field of space irradiation tests, and provides a multi-degree-of-freedom pose adjusting device for a space irradiation test. The device is formed by sequentially connecting a supporting base, a shear type lifting mechanism, a linear translation mechanism and a pitching mechanism, and can realize accurate translation of a test sample in X, Y and Z axis directions and pitching turnover around a horizontal axis in a vacuum environment. The device provided by the invention is compact in structure and high in adjustment precision, is especially suitable for performing multi-dimensional attitude control on a test sample in a vacuum irradiation environment, and remarkably improves the flexibility and stability of sample positioning and attitude adjustment in a space irradiation test; the problems of motion coupling, precision loss, large occupied space and the like existing in a traditional single-shaft or double-shaft mechanism are solved, high-precision multi-degree-of-freedom motion control under the complex vacuum environment is achieved, and the high-precision multi-degree-of-freedom motion control mechanism has the remarkable advantages of being high in structural integration degree, high in adaptability, high in repeated positioning precision and the like.

The invention provides a homogeneous composite material, a composite material system, a stacking structure and a radiation protection material design method, and relates to the technical field of space radiation protection materials.The homogeneous composite material is prepared from, by mass, 10-30% of epoxy resin, 10-90% of bismuth trioxide and the balance polyethylene and boron nitride which are equal in mass fraction. According to the invention, the radiation protection material with radiation resistance and light weight can be designed.

The invention provides a processing method and device for a multi-path radiation reference inter-satellite transmission result, and is applied to the technical field of space radiation measurement. The method comprises the steps that # imgabs 0 # atmospheric top spectral radiance correction and # imgabs 1 # uncertainty of a target spaceborne instrument are obtained and calculated through a multi-path radiation reference inter-satellite transmission method, and one reference satellite corresponds to one atmospheric top spectral radiance correction and one uncertainty; the outliers in the # imgabs 2 # atmospheric top spectrum radiance correction values are removed, and # imgabs 3 # atmospheric top spectrum radiance correction values and corresponding # imgabs 4 # uncertainties are obtained; under the condition that the # imgabs5 uncertainty does not meet a first condition, calculating a target transmission result based on a weighted average method; if the # imgabs6 uncertainty satisfies the first condition, a target delivery result is calculated on the basis of an arithmetic average method.

The invention relates to radiation shielding, shield suited therefore, and enclosures related thereto and method for (co-)designing and related material search methods. The invention also relates to enclosures, provided with such radiation shielding shields. In particular the invention relates to enclosures for protecting electronic devices (EEE components, (high-performance) computing devices) against such radiation. The invention also relates to enclosures for protecting humans for such radiation. The invention also relates to enclosure, sized to contain both electronic devices and humans. The invention also relates to arrangements wherein one enclosure (containing electronics) is part of a second (bigger) enclosure (wherein also one or more humans or users can fit, who may operate the electronics).

The utility model discloses an antenna structure and a mobile terminal, and relates to the antenna technology field, the antenna structure comprises a basic coupling body and a radiation body, the radiation body is in coupling connection with the basic coupling body and is vertical to the basic coupling body, the radiation body comprises at least two radiation branches, and the radiation branches are arranged in an inner and outer surrounding manner; according to the technical scheme of the utility model, the radiation body and the basic coupling body are vertically arranged, so that the antenna structure can be conveniently arranged in the mobile terminal, and the occupied space of the antenna structure can be reduced as much as possible; the internal and external surrounding arrangement of the radiation branches may help to form a more complex electromagnetic radiation mode, and improves the radiation efficiency and directivity of the antenna. The antenna structure can realize a larger radiation area in a limited space, the antenna gain and bandwidth are improved, and the working efficiency of the antenna structure is guaranteed.

The invention provides a planetary exploration intense radiation environment progressive ionizing radiation shielding protection method, which comprises the following steps: according to a planetary exploration task, carrying out space radiation environment analysis, forming an ionization total dose depth curve table, and formulating space environment protection design requirements; arranging total dose resistance capability indexes of all single machines to form a single machine ionization radiation resistance capability statistical table; carrying out protection grade confirmation on the matching of each single machine and the space environment protection design requirement; forming an intense radiation environment progressive shielding protection single machine list; performing effect evaluation on the shielding protection strategy of the progressive ionizing radiation screen; and formulating a progressive ionizing radiation shielding protection implementation scheme, defining a single-machine protection level, a shielding protection strategy, platform layout and guarantee conditions, and forming an engineering implementation scheme. The invention provides an intense radiation environment protection method aiming at the ionizing radiation protection requirement of a planetary exploration task, and the method can be applied and implemented in engineering.

The invention discloses an aperture sharing double-sided image double-frequency folding transmission array and a design method. The double-frequency folding transmission array comprises a first transmission and reflection metasurface, a second transmission and reflection metasurface and a horn feed source, wherein the rotation direction and the frequency of the first transmission and reflection metasurface are jointly controlled. The first transmission and reflection metasurface comprises m * m circular radiation-receiving units and (m + 1) * (m + 1) cross-shaped metal units which are arranged in a staggered mode, and phase regulation and control of efficient transmission of low-frequency electromagnetic waves and efficient reflection of high-frequency electromagnetic waves are achieved. The circular radiation-receiving unit is provided with three layers of metal and two layers of dielectric plates; the second transmission and reflection metasurface comprises n * n square radiation-receiving units which are arranged in a periodic continuation mode, and high-frequency electromagnetic wave efficient transmission phase regulation and low-frequency electromagnetic wave efficient reflection are achieved. The square radiation-receiving unit is provided with three layers of metal and two layers of dielectric plates. The aperture-sharing double-sided image double-frequency folding transmission array generates two circularly polarized wave beams with different frequency bands in opposite directions in the space under the excitation of a circularly polarized wave feed source, and has the remarkable advantages of high gain, low profile, total-space radiation and the like.

The invention relates to a long straight control cable space radiation field effect calculation and evaluation method, system and device and a medium. The method comprises the following steps: constructing a partial differential equation constraint model based on a cable geometric structure and electromagnetic transient characteristics; fusing an actually measured magnetic field and an additional physical rule through a physical information neural network, and generating a complete electromagnetic data set to compensate for electric field data missing; a multi-dimensional interference factor is calculated by combining time-frequency distribution characteristics, equipment sensitive parameters and cable equivalent inductance, and the radiation field effect complexity is objectively quantified; establishing a probability mapping model of interference indexes and effect states by adopting multi-dimensional Gaussian process regression to realize risk probability distribution prediction; and finally, generating a visual probability curved surface of an electric field-magnetic field plane, and identifying a high-risk area to guide electromagnetic protection optimization. According to the method, the evaluation precision is improved in a data limited scene, and a technical closed loop from multi-dimensional feature fusion to probabilistic risk early warning is realized.

The invention relates to an energy spectrum modulator design method and system for generating a solar proton event based on accelerator simulation, and the method employs a scattering target to guarantee the beam uniformity when the energy spectrum modulator is used for proton irradiation, and employs a Monte Carlo program to simulate a normalized proton energy spectrum at a sample test position. And comparing the similarity between the shape of the simulated proton energy spectrum and the shape of the solar proton energy spectrum, and verifying the design effect so as to iteratively optimize the design scheme, so that the similarity between the shape of the simulated proton energy spectrum and the shape of the solar proton energy spectrum reaches a satisfactory degree. The design method can effectively solve the problem that protons at the low-energy end of the solar proton event cannot be effectively simulated in an existing scheme. The energy spectrum modulator designed according to the invention not only can be used for space radiation effect mechanism, test and evaluation work of electronic devices, but also can be used for carrying out space radiation biological effect experiment research work of organisms.

The invention relates to a method for obtaining the equivalent silicon layer thickness and the single event upset LET threshold value of a device, belongs to the technical field of space radiation effect simulation experiment and radiation hardening, and solves the technical problem that the equivalent silicon layer thickness and the single event upset LET threshold value of the device are difficult to obtain. The acquisition method comprises the following steps: calculating average proton energy and an LET value and a range in silicon; acquiring a relation curve between the single event upset cross section of the device and the average proton energy; extracting the upper and lower limits of energy corresponding to the single event upset section peak of the low-energy proton of the device; calculating the equivalent silicon layer thickness of the device based on the energy lower limit; calculating a proton range, energy and an LET value in the sensitive volume of the device based on the energy upper limit; calculating a proton range, energy and an LET value in the sensitive volume based on the proton which is higher than and closest to the energy upper limit; and a step of obtaining an LET threshold value of single event upset of the device. According to the method, the equivalent silicon layer thickness and the single event upset LET threshold value of the device can be accurately obtained.

The invention discloses a shell temperature control method for a high-power-consumption spacecraft in a life evaluation test. The method comprises the following steps: determining heating power required by a heating resistor according to characteristics of the high-power-consumption spacecraft and an expected shell temperature during the life evaluation test; selecting the type and parameters of a heating resistor according to the required heating power, and determining the resistance value; determining power supply voltage required by the heating resistor according to the heating power and the resistance value; the heating resistor is fixedly installed on a shell of the large-power-consumption spacecraft part; and when the service life evaluation test is carried out on the large-power-consumption spacecraft part, the heating resistor is powered by the required power supply voltage. According to the method, the shell temperature of the large-power-consumption spacecraft in the life evaluation test process can be effectively controlled, so that the influence rule of thermal stress on key characteristic parameters of the device is explored in the life evaluation test, the service life of the large-power-consumption spacecraft in the space irradiation environment is predicted, and the design or process weak points of the large-power-consumption spacecraft are identified; and support is provided for improvement of large-power-consumption spacecraft parts.

The invention discloses an additional anti-radiation shielding structure for a YIG filter, belonging to the technical field of anti-radiation reinforcement of electronic components, comprising an upper shielding cylinder and a lower shielding cylinder which are symmetrical in upper and lower directions, wherein the upper shielding cylinder and the lower shielding cylinder are provided with bottom through holes at the same position on the bottom, the side walls where the upper shielding cylinder and the lower shielding cylinder are connected are provided with side wall notches, and the side walls of the upper shielding cylinder and the lower shielding cylinder are also provided with side wall through holes; the invention also discloses a filter with the additional shielding structure; the invention provides an additional anti-radiation shielding structure for a YIG filter, which is beneficial to enhancing the anti-space radiation capability of the YIG filter, enabling the YIG filter to withstand more severe space radiation and maintain stable working performance, thereby extending its service life in a space radiation environment.

The invention relates to a pathfinder test satellite suitable for a deep space exploration flight mission, and the satellite orbit of the pathfinder test satellite is a non-near earth orbit which avoids the influence of a normal Airy radiation band, and is a low orbit inclination angle which is free from the influence of strong space radiation. The method has the beneficial effects that the satellite orbit is not influenced by the Nabelian radiation band and is consistent with the actual deep space orbit environment.

The invention belongs to the technical field of integrated circuits, and particularly relates to an asymmetric switch applied to a satellite-borne wireless communication system. The circuit structure of the switch comprises an anti-radiation switch core circuit, a power detection circuit, an analog-to-digital converter and a control module circuit, an input signal is input to the anti-radiation switch core circuit, and an output signal is generated and output to the power detection circuit. The power detection circuit processes the received signal, outputs a processing result to the analog-to-digital converter, receives an instruction of the control module circuit and generates an output signal of the whole circuit; the analog-to-digital converter converts a processing result output by the power detection circuit into a digital signal and outputs the digital signal to the control module circuit; the control module circuit performs judgment according to the input digital signal, generates a control signal for controlling the working mode of the anti-radiation switch core circuit, and generates a control signal for controlling the power detection circuit and the analog-to-digital converter; the radiation-proof switch core circuit is composed of two paths of identical series-parallel asymmetric switches and three numerical control single-pole double-throw switches. Switching of the two switching circuits is controlled by a numerical control single-pole double-throw switch, and by means of the structure, the circuit failure probability caused by space irradiation can be remarkably reduced, and the anti-irradiation performance and stability of the circuit are improved.

The present application relates to a kind of device equivalent silicon layer thickness and the acquisition method of single event upset LET threshold, belong to space radiation effect simulation experiment technique and anti-radiation hardening technical field, solve the technical problem that device equivalent silicon layer thickness and single event upset LET threshold are difficult to obtain, its acquisition method includes obtaining average proton energy and LET value and range in silicon;Obtain the relationship curve of device single event upset cross section and average proton energy;Extract the energy upper and lower limit corresponding to the single event upset cross section peak of low-energy proton of device;Based on energy lower limit, the equivalent silicon layer thickness of device is calculated;Based on energy upper limit, the proton range, energy and LET value in the sensitive volume of device are calculated;Based on the proton higher than and closest to energy upper limit, the proton range, energy and LET value in the sensitive volume are calculated;The step of obtaining the LET threshold of device single event upset.The method can realize the accurate acquisition of device equivalent silicon layer thickness and single event upset LET threshold.