112 results about "Space radiation" patented technology

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 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.

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.

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 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.

The invention discloses a dual-node upset resistant nonvolatile static random access memory, belongs to the field of integrated circuits, and can be applied to realizing the non-volatility and dual-node upset resistant reliability of the static random access memory. According to the scheme, an MTJ transistor, a PMOS transistor and an NMOS transistor are added on the basis of a traditional 6T static random access memory circuit, non-volatility can be integrated for the static random access memory, and errors caused by the double-node overturning effect are effectively corrected. The method has the advantages of integration non-volatility, high reliability, low power consumption and good compatibility with the traditional process. In consideration of a double-node effect sensitive node pair, the reinforcement method can quickly correct error data bit flipping, is higher in double-node flipping resistance, and can be used for reliable storage of data in a space radiation environment.

We utilize high-quality-factor (high-Q) metasurfaces patterned either in or adjacent to electro-optical or thermo-optical materials such as lithium niobate, barium titanate, or thermally-sensitive polymers. The metasurface includes nanoantennas that act as dipole emitters; the particular structure and arrangement of nanoantennas can steer light to particular directions or focus light, The electromagnetic metasurface supports one or more guided mode resonances. The metasurface also includes a perturbation superposed on the metasurface features and configured to couple free-space radiation to the guided mode resonances.

The present application relates to a kind of terahertz high-power power amplifier components, belong to the field of electronic devices, it includes by synthesis network upper cavity and synthesis network lower cavity synthesis network is formed, in synthesis network lower cavity back surface installation setting has small signal amplification module, middle power amplifier module, push stage power amplifier module, last stage power amplifier module and detection module, in synthesis network setting has E face waveguide directional coupler, the small signal amplification module, middle power amplifier module, push stage power amplifier module, last stage power amplifier module and E face waveguide directional coupler are sequentially electrically connected, the E face waveguide directional coupler port is electrically connected with detection module;In synthesis network, waveguide tube is equipped in each module installation position, and each module is electrically connected by waveguide tube.The present application will be modularized design to each stage amplifier, can increase the isolation between the link each device, reduce the self-excitation risk caused by space radiation.And the testability of single module is improved, and troubleshooting cost and time are reduced.

The application discloses a kind of hardware supplement method, system and circuit of space data processing and knowledge management system, belong to spaceborne data processing technical field, for solving existing spaceborne data processing relies on central processing unit and software architecture, it is easy to be affected by space single particle effect, space radiation interference and appear operation exception, real-time and reliability insufficient problem.The core method of the application includes: reading cache knowledge according to time decay calculation current confidence;Data packet hop count or survival time is directly discarded when exceeding limit;After inter-satellite link interruption recovers, master artificial intelligence node is elected according to preset rule and conflict is judged;When cache is written, it is accumulated to the minimum writing unit after being written once, and wear leveling is triggered according to the number of erasing and writing.The whole process of the application is automatically executed by pure hardware circuit, without central processing unit, without instruction execution, without software code running, with the characteristics of anti-radiation, high real-time, high reliability, can be adapted to space on-orbit environment.

The application discloses a kind of on-orbit repair methods of space radiation damage of spaceborne photoelectric detector, comprising: disconnecting the power supply of TEC in photoelectric detector;Reverse voltage is applied to TEC;Chip temperature is maintained for a predetermined time;Disconnect the power supply of reverse application to TEC, end annealing repair;Normal on the power supply of TEC.The application utilizes the reverse heating of TEC of photoelectric detector, realizes the on-orbit real-time annealing repair of radiation damage, can dissipate interface charge to repair ionization damage, and can also repair lattice defects, the method only needs to set TEC reverse heating program, can extend the on-orbit working life and reliability of detector, and has broad application prospect.

The invention belongs to the technical field of space radiation, and discloses a carbon-based device single event effect pulse laser test system and an equivalent LET value calculation method, which can be used for guiding a carbon-based device single event effect pulse laser test. The system is composed of a pulse laser, a probe test platform, a power supply system, a control system and a high-frequency oscilloscope, based on the equivalence of the system, the method obtains equivalence = 1.02104 based on the structural characteristics of the carbon-based device through the front irradiation characteristics of laser, and the method has important significance for guiding the pulse laser test of the carbon-based device.

This utility model relates to the field of electronic switch technology, specifically a low-power aerospace-grade electronic switch. The displacement sensor and fault detection chip are connected by electrical signals. The main switch circuit module and the backup switch circuit module are in parallel. The fault detection chip and the MEMS switch unit are connected by electrical signals. The K-type thermocouple and the shape memory alloy spring are connected by electrical signals. Through the double-layer shielding of "tungsten metal film + nano-ceramic", the false alarm rate caused by space radiation is reduced by 97.5%, meeting the reliability requirements of a 10-year service life of low Earth orbit (LEO) satellites. It has a built-in temperature adaptive compensation system, and the contact resistance fluctuation is ≤±1% in the range of -196℃ (liquid nitrogen environment) to +200℃ (high temperature oven). No external temperature sensor calibration is required, making it suitable for extreme temperature difference scenarios such as engine compartments.

The invention discloses an aerospace power control electronic device accelerated life test method based on failure physics. The method comprises the following steps: firstly, determining a temperature stress level and a thermal correlation failure mechanism acceleration factor of an accelerated life test; determining initial acceleration test time according to the thermal correlation failure mechanism acceleration factor; in combination with the temperature stress level, sequentially cooperating with other failure mechanisms including an electrical correlation failure mechanism, a vibration correlation failure mechanism and a space radiation correlation failure mechanism to obtain stress levels and acceleration factors under the corresponding failure mechanisms, and on the basis of the initial acceleration test time, performing acceleration test time optimization; and finally, based on the determined acceleration factors and corresponding stress levels under each failure mechanism and the finally optimized acceleration test time, carrying out an acceleration life test. The method provided by the invention can provide a scientific basis for reliability evaluation of the electronic product in an on-orbit environment, and can accurately predict the life index of the product under a multi-stress comprehensive condition.

The invention provides a silicon photon gyroscope with a film-coated mode filtering double-Y waveguide integrated structure. The silicon photon gyroscope comprises a laser, a detector, a symmetrical double-Y waveguide, a first filter, a second filter, a third filter, a fourth filter, a first phase modulator, a second phase modulator and a ring, symmetrical optimization design is adopted for the symmetrical double-Y waveguides, namely mode excitation is reduced by conducting collaborative optimization on the front Y waveguide and the rear Y waveguide, the bifurcation angle of the front Y waveguide and the rear Y waveguide is controlled to be 8-12 degrees, the high-order mode excitation rate is controlled to be within 1%, and therefore space radiation mode errors and zero drift are remarkably reduced. A high-order mode excited in the beam splitting process is suppressed through the first and second filters, and a new mode of temperature gradient or stress introduction is prevented through the third and fourth filters; selective suppression of a high-order spatial mode is realized by adopting the filter with a film-coated structure, and meanwhile, low-loss transmission of a fundamental mode is kept, so that the zero-bias stability and the measurement precision of the silicon photon gyroscope are remarkably improved.