157 results about "Space radiation" patented technology

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 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 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 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.

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 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 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 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 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.

The present invention relates to the field of space radiation effects and reinforcement technology, specifically to a single-particle upset recovery analysis method that combines experiments and simulations. This method addresses the shortcomings of existing numerical simulations of single-particle upset recovery, which fail to consider the coupling effects of surrounding storage cells and cannot accurately predict the impact of upset recovery on multi-cell upsets. Furthermore, due to the random location of single-particle upset recovery in the storage array and its short duration, the response process is difficult to directly capture experimentally. This combined experimental and simulation single-particle upset recovery analysis method organically combines experiments and simulations, leveraging the complementary advantages of heavy ion broad-beam experiments, heavy ion microbeam experiments, and numerical simulations to more comprehensively and meticulously reveal the mechanisms and influencing factors of single-particle upset recovery.

This application relates to a device and method for protecting high-voltage space radiation output from a charge pump. It includes a radiation-resistant reference and self-calibration module and a dual-mode overvoltage response module. The radiation-resistant reference and self-calibration module automatically verifies and maintains the stability of the generated reference voltage under radiation conditions by comparing the output signals of a buffer circuit and a redundant buffer circuit. The dual-mode overvoltage response module monitors the high voltage output from the charge pump using the reference voltage and automatically triggers two protection modes based on whether it exceeds a first-level threshold or a higher second-level threshold: when the first-level threshold is exceeded, a first protection mode is triggered, suppressing the clock pulse input to the charge pump and opening the leakage current to reduce the high voltage; when the second-level threshold is exceeded, a second protection mode is triggered, directly shutting off the clock pulse of the charge pump and opening the leakage current. This invention ensures the reliability of the judgment reference from the source and achieves highly reliable protection against overvoltage caused by space radiation through an adaptive dual-mode response mechanism.

An electronic spatial system is disclosed including an electronic circuit that is sensitive to spatial radiation, including at least one signal input port and / or at least one signal output port; a signal processing unit; an electronic spatial radiation detection unit electrically connected to the signal processing unit; and at least one protective switch electrically connected between the electrical ground of the electronic spatial system and at least one out of the signal input or signal output ports of the sensitive electronic circuit, and controlled by the signal processing unit. The signal processing unit is configured to switch the at least one protective switch to the electrical ground upon detecting an amplitude of a signal that is representative of an amount of spatial radiation greater than a predefined radiation threshold.

The invention discloses a foam material with a radiation protection function and a preparation method thereof. Specifically, the invention provides a PMI foam material for deep space radiation protection. The foam material comprises the following raw materials: a carboxyl-containing acrylic monomer, a cyano-containing acrylonitrile monomer, a conjugated ring-containing monomer, a radiation protective agent, an anti-settling agent, an initiator and a foaming agent, and the radiation protective agent comprises a boron-containing compound. The foam material disclosed by the invention has relatively good radiation protection effects such as thermal neutron shielding and the like, and can be applied to radiation protection materials in the fields of aviation and spaceflight.

The invention relates to the technical field of signal detection, in particular to mobile phone signal detection equipment, which comprises a central control module; the radio frequency channel simulator is connected with the central control module and is used for receiving the synchronous control instruction and the time-varying channel parameters from the central control module; the space environment simulation device is used for radiofrequency signals and dynamically adjusting space radiation characteristics and link loss of the space environment simulation device based on instructions of the central control module; the protocol stack simulation and signaling interaction module is used for simulating cellular network protocol stack behaviors according to the instruction of the central control module and carrying out signaling interaction with the mobile phone to be tested; a multi-dimensional data acquisition and analysis module; according to the device, the radio frequency channel simulator, the space environment simulation device and the protocol stack simulation module are dispatched in a unified mode through the central control module, complex wireless scenes from geographical environment and channel characteristics to network behaviors can be accurately reproduced, and the reliability and repeatability of testing are greatly improved.

This invention discloses a SRAM memory cell hardened based on FDSOI technology and its single-event effect evaluation method, mainly addressing the problem of decreased radiation resistance performance under low critical charge conditions in existing technologies. It includes: a pair of cross-coupled memory inverters, a memory node, and symmetrical accessors. The memory inverter includes two series-connected PMOS transistors and two series-connected NMOS transistors, forming pull-up and pull-down branches respectively, with interlocking transistors connecting the branches. Each connection point constitutes a memory node. The accessor includes four NMOS transistors, with their sources connected to the memory node, drains connected to the bit line, and gates connected to the word line. The pair of memory inverters achieves functional complementarity of the memory nodes through cross-connection of the memory node and the gate of the series-connected transistor at the opposite end. This invention can reproduce the current tailing effect of single-event transient pulses in FDSOI devices, improve radiation resistance performance under low critical charge conditions, and achieve quantitative evaluation of radiation resistance performance. It can be used for reliability evaluation of aerospace-grade integrated circuits under space radiation environments.

This invention discloses a microwave heating device with high-order mode suppression, belonging to the field of microwave heating technology. It includes: a heater comprising a rectangular waveguide and metal ridges; the rectangular waveguide has a microwave cavity extending laterally; two metal ridges are symmetrically arranged front-to-back within the microwave cavity, with a front-to-back spacing between them, and each ridge has a material passage hole extending front-to-back; and two high-order mode suppressors, respectively located at the front and rear ends of the heater, each high-order mode suppressor having a material cavity for the workpiece to be heated to pass through, extending front-to-back and communicating with the material passage hole. This invention features a compact structure, strong electric field, rapid and uniform heating, and protection against high-frequency radiation, preventing harm to operators from microwave spatial radiation and ensuring the safe use of the microwave heating device.

The invention discloses a multi-legged robot radiation source autonomous positioning method based on AI dynamic path optimization, and belongs to the technical field of nuclear radiation monitoring and intelligent robots, and the method comprises the steps: collecting space radiation intensity data, eliminating pseudo sources, calculating a radiation gradient field, and constructing a radiation field in real time; an improved social network search algorithm is adopted to solve a target function of an optimal path, the target function dynamically fuses a path length and a radiation gradient integral, and a path weight coefficient alpha and a radiation weight coefficient beta are adjusted in real time through a Sigmoid function according to environmental complexity; the multi-legged robot conducts gait self-adaptive control according to the optimal path, and the movement speed is adjusted according to the real-time radiation intensity. According to the method, dynamic path optimization, multi-mode perception and pseudo source elimination are fused, the problems of path disjunction, data distortion, pseudo source interference, insufficient dynamic adaptability and the like in the prior art are solved, and an autonomous and credible radiation source positioning solution is provided for nuclear leakage emergency.

The invention discloses application of ellagic acid in preparation of a medicine for preventing or treating ionizing radiation injury, and belongs to the technical field of biological medicine and radiation protection. Experiments prove that ellagic acid with an effective concentration can inhibit lipid peroxidation, enhance the activity of glutathione transferase and superoxide dismutase and promote the expression of antioxidant related genes such as sod-1, sod-2, gst-1 and gst-29 and immune related genes such as lys-1, irg-1, irg-2 and mul-1, so that the ellagic acid with an effective concentration can inhibit lipid peroxidation and improve the activity of glutathione transferase and superoxide dismutase. Therefore, oxidative damage, inflammatory response, reduced stress tolerance, accelerated aging and shortened service life caused by ionizing radiation exposure are relieved, and the compound can be applied to preparation of drugs for preventing or treating ionizing radiation damage and is suitable for nuclear accident emergency protection, space radiation protection of astronauts and adjuvant therapy of tumor radiotherapy patients. The invention provides a theoretical basis for developing an efficient and low-toxicity ionizing radiation protective agent based on ellagic acid, and has a wide application prospect.

The application belongs to the technical field of antennas and relates to a cross-dipole antenna which comprises a metasurface layer, a radiation layer and a ground layer; the metasurface layer is connected with the ground layer and forms a containing space between the metasurface layer and the ground layer; the radiation layer is arranged in the containing space, is connected with the ground layer and is arranged in a spaced mode with the metasurface layer; the radiation layer comprises two pairs of cross-dipoles; two feeding structures are arranged on the ground layer and are connected with the two pairs of cross-dipoles respectively; the radiation layer comprises a dielectric plate and four radiation patches which are arranged in a spaced center-symmetrical mode about the center of the dielectric plate; the dielectric plate and the radiation patches are square structures, one side of the radiation patch is parallel to one side of the dielectric plate; two radiation patches are adjacently arranged on the top surface of the dielectric plate, and the other two radiation patches are adjacently arranged on the bottom surface of the dielectric plate; two opposite radiation patches are connected to serve as a dipole. The application can reduce the profile of the antenna.

The invention belongs to the technical field of wireless communication, particularly relates to a non-reciprocal full-duplex filtering antenna based on substrate integrated waveguide and space-time modulation, and aims to realize full-duplex communication and ensure efficient transmission of a receiving path and a transmitting path. And port isolation of a transmission path from the antenna port to the transmit port and a transmission path from the transmit port to the receive port. The method comprises the following steps: firstly, constructing a non-reciprocal circulator based on a space-time modulation technology, realizing directional transmission characteristics from an antenna port to a receiving port and from a transmitting port to the antenna port, and simultaneously obtaining high isolation from the antenna port to the transmitting port and from the transmitting port to the receiving port; and secondly, by utilizing the filtering characteristic of the substrate integrated waveguide, band-pass filtering response is integrated in transmission paths of the three ports, so that low-loss transmission in a working frequency band and effective suppression of out-of-band signals are realized. And finally, integrating a slot antenna structure at an antenna port to complete the space radiation and receiving functions of signals. Through the above design, the device realizes integration of three functions of circulation, filtering and radiation.

The application relates to an array P island and a multi-buffer layer SiC MOSFET with improved anti-single particle capability, and belongs to the microelectronic technology field. The application aims to solve the problems of weak anti-single particle burnout capability and high thermal failure risk of a silicon carbide device in a space radiation environment. The technical scheme comprises arranging four buffer layers with a doping gradient between a drain metal and a drift layer, and embedding an array structure composed of multiple left and right P islands and a middle P island in the buffer layers. The structure forms a super-junction-like electric field distribution on a single particle incident path. The technical effect of the application is that, through the synergistic effect of the array P island and the multi-buffer layer, the electric field peak value in the device is effectively flattened and homogenized, the carrier multiplication effect is inhibited, the transient power density and lattice temperature caused by single particle incidence are significantly reduced, and the single particle burnout threshold voltage of the device is greatly improved on the premise of basically maintaining the original electrical characteristics of the device.

The invention provides a GEO electric propulsion satellite orbital transfer process solar cell radiation effect rapid evaluation method, which comprises the following steps that: firstly, a solar cell radiation damage space distribution database is constructed through space radiation effect analysis software, and the database comprises daily average equivalent 1MeV electron flux distribution data under different orbit heights, inclination angles and cover glass thicknesses; generating satellite space track data according to an electric propulsion orbital transfer strategy; counting accumulated operation time of the satellite in each height and dip angle interval according to a preset interval; and finally, multiplying and accumulating the daily average equivalent 1MeV electron flux corresponding to each interval by the accumulated running time to quickly obtain the accumulated equivalent 1MeV electron flux in the whole orbital transfer process. Therefore, the problem of long calculation time consumption of a traditional method is solved, and rapid evaluation support can be provided for radiation mitigation optimization design of the orbital transfer strategy.

Systems, methods, and computer-readable storage media for simulating a non-homogenous space environment. A system can include a ion beam generator, a moderator block, a radiation detector, at least one processor which can execute operations including: transmitting, 7o the ion beam generator, a beam generation signal, the beam generation signal specifying an energy level of an ion beam and a duration of the ion beam, the ion beam making first contact with the moderator block and subsequent contact with a test animal; receiving, from the radiation detector after the duration of the ion beam is completed, energy deposition within the test animal. The system can then execute computational models to determine moderator block computational results animal computational results, then generate projected human results for the ion beam based on the moderator block computational results and the animal computational results.

The present invention provides a W-S-Ti-O lubricating film and its preparation method and application, which belongs to the field of space lubrication technology. The present invention provides a W-S-Ti-O lubricating film, which has a dense amorphous structure and is composed of WS2 phase, WS x O y The present invention introduces Ti and O elements into the WS2-based film to inhibit the growth of WS2 crystals, thereby forming a W-S-Ti-O lubricating film with an amorphous dense structure, which has good vacuum tribological properties and resistance to space radiation, especially atomic oxygen corrosion. The results of the embodiment show that the W-S-Ti-O lubricating film prepared by the present invention exhibits good resistance to atomic oxygen radiation after being exposed to the environment of the windward surface outside the space station for 6 months. The vacuum friction coefficient of the film after irradiation is 0.03, and the lubrication life is higher than 4.0×10 5 r.

The invention provides a steady-state measuring device and method for measuring radiation heat flux of an extraterrestrial space, and the device comprises a mounting bottom plate which is made of a thermal insulation material; the first heat flow meter is assembled in the first area of the mounting bottom plate; comprising a first measuring assembly and a second measuring assembly, the second measuring assembly is stacked on the surface of the first measuring assembly, and the diameter of the second measuring assembly is smaller than that of the first measuring assembly; the surface layer of the first measuring assembly is provided with a first compensating plate. The surface layer of the second measuring assembly is provided with a first temperature-sensing wafer. The second heat flow meter is assembled in the second area of the mounting bottom plate; comprising a third measuring assembly and a fourth measuring assembly, the fourth measuring assembly is stacked on the surface of the third measuring assembly, and the diameter of the fourth measuring assembly is smaller than that of the third measuring assembly; the surface layer of the third measuring assembly is provided with a second compensating plate. The surface layer of the fourth measuring assembly is provided with a second temperature-sensitive wafer. The lunar orbit solar radiation, the lunar reflection and the lunar infrared radiation heat flow can be measured at the same time.

The application provides a planetary exploration strong 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 ionizing total dose depth curve table, and formulating a space environment protection design requirement; collating total single machine anti-total dose capacity indexes, and forming a single machine anti-ionizing radiation capacity statistics table; confirming a protection level of matching of each single machine and the space environment protection design requirement; forming a strong radiation environment progressive shielding protection single machine list; evaluating an effect of the progressive ionizing radiation shielding protection strategy; formulating a progressive ionizing radiation shielding protection implementation scheme, and clearly defining single machine protection levels, shielding protection strategies, platform layouts and guarantee conditions, and forming an engineering implementation scheme. The application provides a strong radiation environment protection method for the ionizing radiation protection requirement of the planetary exploration task, and can be applied to engineering and implementation.

The invention relates to the technical field of operating systems, in particular to a software triple modular redundancy method for realizing serial port drive, which comprises the following steps of: modifying a key code path of the serial port drive, and adding a struct TmrCommon structural body and an int tmrvoteandrepair function; when any key code path is executed, a first part of data, a second part of data and a third part of data are obtained through a struct TmrCommon structural body, and three-mode voting, error repairing and fault diagnosis are achieved through an int tmrvoteandrepair function. According to the scheme, the influence of a space radiation environment is overcome, the probability that traditional serial port communication breaks down after encountering single event upset in space is reduced, and the requirement for high reliability of a spaceborne system is met.