1264results about "Sagnac effect gyrometers" patented technology

The invention provides a fiber-optic gyroscope drift compensation method and system fused with LMS self-adaptive filtering, and relates to the technical field of LMS self-adaptive filtering, the method comprises the following steps: synchronously collecting multi-point temperature data, temperature change rate, axial and radial gradient information and original output signals of a gyroscope shell, and calculating the multi-point temperature data, the temperature change rate, the axial and radial gradient information and the original output signals of the gyroscope shell; the original signal is separated into a temperature drift component and a non-temperature noise component through variational mode decomposition, and noise is filtered out; establishing a nonlinear mapping relation by combining the temperature field data and the drift component to generate a drift predicted value, and inputting the predicted value and the residual error of the actual drift component into an LMS adaptive filter for dynamic error compensation; and finally, superposing the compensation result and the predicted value, and outputting a corrected gyro signal. According to the invention, the drift compensation precision and stability of the fiber-optic gyroscope in a complex variable-temperature environment are improved.

The invention relates to the technical field of optical fiber sensing and fault diagnosis, in particular to an optical fiber gyroscope fault monitoring method and system. The method comprises the following steps: extracting four-dimensional characteristics of phase difference, light intensity fluctuation, polarization state drift and temperature drift from an output signal of an optical fiber gyroscope, and constructing a high-dimensional characteristic matrix after unifying a time reference; establishing a dynamic prediction model based on historical data to generate a residual matrix, and orthogonally separating the residual into an internal structure abnormal signal and an environment disturbance signal through covariance characteristic decomposition; mapping the structure residual error sequence into a topological graph, calculating an evolution index in real time, and capturing a fault gradient trend in combination with sliding window gradient analysis; a multi-dimensional vector is constructed by fusing topological features, an adaptive classifier of an online Gaussian mixture model is adopted to identify a fault mode and quantify a health index, and meanwhile, a health measurement result is fed back to a prediction model and topological analysis parameters to realize closed-loop optimization. According to the invention, full-process adaptive monitoring from anomaly detection to health measurement is realized.

The invention relates to a method for testing and compensating a gyroscope installation error angle of a fiber-optic gyroscope inertial platform, which is used for testing the installation error angle of a fiber-optic gyroscope platform relative to a hexahedral coordinate system after the fiber-optic gyroscope is installed on a platform body. The gyroscope installation error and the ground velocity are coupled in gyroscope output during error coefficient calibration, so that the true value of the calibration result of the instrument error coefficient is influenced, calibration is carried out in different orientations, the ground velocities coupled with the gyroscope installation error are different, and therefore, the calibration results of four orthogonal orientations are combined, and the gyroscope installation error angle calculation is realized in an analytic mode. And compensating the obtained gyroscope installation error angle into the error model, thereby solving the problem of testing the precision of the gyroscope of the high-precision fiber-optic gyroscope platform.

The invention belongs to the technical field of integrated optics and inertial sensing, and particularly relates to a thin-film lithium niobate heterogeneous integrated chip configuration for a fiber-optic gyroscope. The thin-film lithium niobate hybrid photon integrated chip is utilized to realize on-chip heterogeneous integration of functional devices of the fiber-optic gyroscope. The discrete optical path device of the gyroscope is monolithic integrated and integrally packaged, the size and cost of the optical path are greatly reduced, optical fiber interconnection is reduced, the complexity of the assembly process is obviously reduced, and the long-term reliability of the performance of the gyroscope is effectively improved. By means of the CMOS technology with mature silicon photons, low-cost and large-scale batch production of the miniature fiber-optic gyroscope can be achieved, and the requirements for miniaturization and light weight of a future weapon system are met.

The invention discloses an airborne combined measurement calculation method for closed-loop optical fibers, which comprises the following steps that: an orthogonally distributed three-axis closed-loop optical fiber gyroscope array acquires a Sagnac phase difference signal in real time, each optical fiber ring adopts an asymmetric pretightening force winding process, the pretightening forces of X / Y / Z axes are 12 + / -0.5 N, 8 + / -0.3 N and 15 + / -0.5 N respectively, the diameter ratio of the optical fiber rings is 1: 0.8: 1.2, environmental disturbance compensation is carried out, and the Sagnac phase difference signal is acquired in real time. Data of 48 PT1000 temperature sensors embedded in the axial direction of an optical fiber ring at the interval of 5 mm and full spectrum data of a three-axis vibration sensor at the frequency band of 0-2000 Hz are synchronously collected, and a coupling error model is constructed based on temperature gradient distribution and vibration spectrum characteristics. Therefore, through an asymmetric winding process, temperature-vibration coupling compensation, improved data fusion and dynamic closed-loop control, the problems of nonreciprocal errors caused by the symmetric winding process, insufficient environmental adaptability of single temperature compensation, limited nonlinear error processing capability of standard Kalman filtering and stability of a fixed parameter controller are solved; high-precision and high-reliability airborne combined measurement is realized.

The invention provides an orbital angular momentum interferometer based on a double-resonance spiral long-period fiber grating and application, and belongs to the field of optical fiber sensing and optical communication passive devices. According to the invention, the double-resonance spiral long-period fiber grating is used as an OAM mode converter, the wavelength of the laser is secondarily regulated and controlled to match left and right resonance peaks, phase superposition of conjugate OAM beam pairs is realized, and secondary sensitization of the OAM interferometer is realized based on a single mode converter. The OAM interferometer is applied to the field of temperature and strain sensing, high-sensitivity detection of temperature variation and strain variation is achieved by combining a double-phase matrix decoupling algorithm, and the problem of cross sensitivity is effectively solved. The invention provides an all-fiber integrated and environment interference resistant innovative solution for high-sensitivity OAM optical fiber sensing, and is suitable for the fields of industrial monitoring, environment sensing and optical communication.

The invention provides a device and a method for universally testing the performance of a silicon optical chip and a gyroscope. The device comprises a chip and gyroscope measurement and control module, an external light source module, an external phase modulator, an optical fiber loop and a light source module, wherein the chip and gyroscope measurement and control module comprises a driving and temperature control unit, a power supply control unit, an electric switch control unit, an optical switch control unit, a signal generation unit and an acquisition and control unit and is used for testing instruction processing and data processing, and the light source module is used for providing stable optical power input for a silicon optical chip without a light source. The analog electric switch controls the signal generation unit to output signals which are respectively applied to the phase modulator on the silicon optical chip or the external phase modulator, and the four optical switches form three test channels and are communicated with the external phase modulator and the optical fiber loop to form a gyroscope optical path. According to the invention, the universal test of the performance of different types of silicon optical chips and gyroscopes can be realized, and the accuracy and timeliness of the test are ensured.

A fiber optic gyroscope temperature drift modeling and real-time compensation method is provided, and the specific steps are as follows: Step 1: Design a fiber optic gyroscope temperature test, and collect the fiber optic gyroscope output value and the fiber optic gyroscope internal temperature sensor data within the full temperature range of ‑30° to 70°; Step 2: Perform wavelet threshold denoising preprocessing on the fiber optic gyroscope output obtained in step 1; Step 3: Establish a fiber optic gyroscope temperature drift segmented compensation model F with temperature change and temperature gradient as independent variables and the fiber optic gyroscope output signal after wavelet threshold denoising preprocessing as the dependent variable; Step 4: Calculate the coefficient of the temperature compensation model F by the least squares method and compensate the fiber optic gyroscope output in real time. The present invention meets the requirements of fast calculation speed and simplicity in engineering, meets the requirements of real-time compensation in engineering, and can effectively solve the problem of fiber optic gyroscope temperature drift, thereby improving the accuracy of the fiber optic gyroscope.

The present invention discloses a low crosstalk optoelectronic co-sealed three-axis integrated transceiver module and an optical fiber gyroscope. By arranging the light source assembly, the first to sixth beam splitting prisms, and the lithium niobate thin film waveguide chip, the light signal's splitting, beam combining, polarization, and modulation functions are completed. On this basis, by designing three detectors on the transmission path of the optical signal to be measured, the optical signal to be measured can be detected and photoelectrically converted. Since the optical signal to be measured carries the information of the measured current, the measured current can be finally obtained by analyzing the electrical signal output by the detector through the processing circuit. Through the above scheme of the present invention, the integration of the optical path and the circuit part is realized, forming a three-axis optical and optical receiving and transmitting circuit and an optoelectronic co-sealed design, realizing a three-axis integrated structural design and transceiver function, and having the advantages of miniaturization, low crosstalk, high integration, and high reliability.

The invention belongs to the technical field of micro photoelectric mechanical systems and micro inertial devices, and particularly relates to a cascaded Fabry-Perot cavity-based ultra-wide optical bandwidth MOEMS gyroscope, which comprises a mass block, an optical structure, an anchoring structure, an electrostatic comb-shaped driving structure, a detection frame, an anchoring frame, an induction spring, a driving spring and a driving frame, the mass block is connected with the optical structure, anchoring structures are arranged at the four corners of the mass block respectively, electrostatic comb-shaped driving structures are arranged on the two sides of the mass block respectively, detection frames are connected to the two sides of the mass block respectively, and the mass block is connected with the anchoring frames through induction springs. On the basis of the Coriolis force measurement principle, the angular velocity is measured by detecting the wavelength or intensity change of an output harmonic peak caused by the structural change of the cascade cavity. Benefited from broadband tuning characteristics and high compactness of a cascade cavity structure, the device can be used in an optical bandwidth range exceeding 175 nm, and has a highly compact structure consisting of an all-silicon micro waveguide and a cavity.

The utility model discloses an auxiliary cavity adjusting device for a laser gyroscope, which comprises a He-Ne laser, a collimation laser, an adjustable first reflecting mirror, a semi-transparent semi-reflecting mirror, a second reflecting mirror, a third reflecting mirror, an imaging mechanism and a light beam coincidence verification structure, and is characterized in that the collimation laser is arranged on the right side of a cavity to be adjusted and corresponds to a left upper plane mirror of the cavity to be adjusted; the first reflecting mirror and the third reflecting mirror are located between the cavity to be adjusted and the collimating laser, the semi-transparent and semi-reflecting mirror is located between the second reflecting mirror and the He-Ne laser, the light beam coincidence verification structure is movably located between the semi-transparent and semi-reflecting mirror and the second reflecting mirror, the He-Ne laser is located right above the collimating laser, and the He-Ne laser is located right above the collimating laser. The semi-transparent semi-reflecting mirror is located over the first reflecting mirror, the second reflecting mirror is located over the third reflecting mirror, and the imaging mechanism is located on the right side of the cavity to be adjusted and corresponds to a left lower plane mirror of the cavity to be adjusted. According to the utility model, the cavity adjusting efficiency and accuracy of the laser gyroscope can be improved.

A spherical multi-axis optical fiber sensing device is formed by a three-axis optical interference sensor composed of a multi-level opto-mechanical integrated unit kit. The opto-mechanical integrated unit kit is composed of three fiber rings, which are respectively a large fiber ring, a medium fiber ring and a small fiber ring. The multi-level opto-mechanical integrated unit kit is combined with the use of the mechanism component technology that can be freely rotated and positioned to achieve the functional purpose of establishing a three-axis orthogonal optical fiber sensing unit in a single sphere volume.

The invention relates to the technical field of optical fiber gyroscopes, in particular to a temperature control optical fiber inertial navigation structure and a design method thereof.The design method comprises the following steps of detecting heat flow direction changes, extracting offset numbers, generating frequency density, analyzing the thickness contour and deformation coincidence rate, outputting correction gradients, matching jump trends and structural connection, and generating a priority sequence; and screening offset channel numbers, integrating compression and deformation trends, and outputting a design scheme. According to the method, by capturing heat flow direction change points and extracting offset area numbers, density expression of a heat energy propagation path is achieved, the space recognition capability of thermal disturbance is enhanced, the structural adaptability of thermal response is improved, and stable conduction of heat flow between structural levels is optimized through sequence integration of a temperature jump trend and a connection relation; and extracting a stable channel number in a lateral offset state, enhancing path directivity, integrating a multi-region compression trend and structural deformation mapping, and improving thermal situation identification capability and structural thermal adaptability.

The invention relates to the technical field of perception fusion, and discloses a tug fusion enhanced perception method based on target tracking and obstacle recognition, which comprises the following steps: processing an AIS, an optical fiber compass, a Beidou RTK, a laser radar, a millimeter wave radar and a panoramic camera on a tug to establish a ship coordinate system; and collecting message data of the AIS and combining with the MMSI information to screen the target ship to obtain the initial position of the target ship. And predicting the state sequence of the target ship to obtain the position, speed and heading information of the target ship. And carrying out target identification on the image, outputting identification results of semantic levels of the ship, the buoy and the quay wall, and carrying out space projection alignment with radar data. And fusing the processed results to obtain a fusion result, and performing early warning according to the fusion result. According to the method, the target ship relative pose resolving precision and the obstacle recognition reliability are improved, the sensing link time delay is shortened, and the driver blind area risk is reduced.

The invention provides a three-axis modulator chip structure and a three-axis fiber-optic gyroscope. The three-axis modulator chip structure comprises an electro-optical modulation chip, a first optical fiber and a second optical fiber, the input fiber is connected with the side of the chip. The input waveguide is embedded in the top surface of the chip, and the first end is coupled with the input fiber; a main port of the one-to-three coupler is coupled with the second end of the input waveguide; first branch ports of the three first one-to-two couplers are respectively coupled with three branch ports of the one-to-three coupler, second branch ports of the three first one-to-two couplers are respectively coupled with the three photoelectric detectors, and total ports of the three first one-to-two couplers are respectively coupled with total ports of the three second one-to-two couplers; each group of Y waveguide modulators comprises a Y waveguide and a modulation electrode, and first ends of two branch arms of the Y waveguide are coupled with two branch ports of the second one-to-two coupler; each output optical fiber group comprises two output optical fibers which are respectively coupled with the second ends of the two branch arms of the Y waveguide; the sealing cover covers the top surface of the chip. Welding is not needed, the assembling difficulty is reduced, and the overall size is reduced.

The invention belongs to the technical field of optoelectronic devices, and provides a laser gyroscope frequency stabilization system and a frequency stabilization method thereof.The laser gyroscope frequency stabilization system comprises a large laser gyroscope to be subjected to frequency stabilization, an electro-optical modulator, an adjusting light path, a signal generator, a mode matching mirror set, a PID regulator, a frequency mixer, a photoelectric detector, an ultra-stable cavity, a low-pass filter, a computer and a data acquisition card; and a square transmission light path is arranged in the ultra-stable cavity. According to the invention, the problem of insufficient isolation caused by an optical isolator consisting of a polarization splitting prism and a 1 / 4 wave plate is effectively avoided, the influence of an optical feedback effect is reduced, and the optical isolator is better adapted to the field of high-precision measurement related to a large laser gyroscope.

The invention discloses a method for reducing an angle measurement error of a fiber-optic gyroscope under a launching load. The method comprises the following steps: establishing a full-gun finite element dynamic model; correcting dynamic model parameters based on the seat ring test acceleration data; establishing a fiber-optic gyroscope mounting platform angular acceleration response maximum pulse value and pulse width prediction model taking a firing angle as an input variable by adopting an approximate modeling technology, and predicting the fiber-optic gyroscope mounting platform angular acceleration response maximum pulse value and pulse width corresponding to firing data; establishing a three-axis fiber-optic gyroscope zero offset increment prediction model under a half-sine angular acceleration impact load by adopting an angular impact test platform calibration method, and predicting the fiber-optic gyroscope zero offset increment corresponding to the obtained maximum pulse value and pulse width; and compensating the zero offset error of the fiber-optic gyroscope according to a zero offset increment prediction result before emission. According to the invention, the angle measurement precision of the fiber-optic gyroscope in a launching impact environment is effectively improved.

A miniaturized interferometric integrated photonic gyroscope structure with top silicon oxide, middle silicon oxide and bottom silicon oxide deposited on a silicon substrate comprises broadband optical source or a semiconductor optical amplifier with silicon nitride ring resonator wavelength filter, connected with a thin film lithium niobate or piezoelectrically actuated silicon nitride phase modulator vertically coupled with a silicon nitride waveguide spiral loop. The silicon nitride waveguide spiral loop is patterned on thin bottom oxide layer with air trenches below it and connected with a germanium detector either through photonic wire bonding or vertically integrated through reflecting mirror embedded into silicon wafer. Various methods of coupling alternative materials are described and the potential of connecting several spiral waveguides for enhanced sensitivity in a gyroscope application.

The invention relates to the field of performance testing of high-precision fiber-optic gyroscopes, and discloses an automatic testing method and system for the extinction ratio of a high-precision fiber-optic gyroscope, and the method comprises the following steps: constructing a signal light path and a reference light path, and combining the output light of the signal light path and the reference light path into a combined light signal in an orthogonal polarization state; integrally measuring the extinction ratio of the combined optical signal by using an extinction ratio tester to obtain a measured value; the control unit compares the measured value with a target value of 0dB and generates a control instruction based on a difference value; the voltage controller automatically adjusts the voltage of the integrated optical modulator in the signal light path according to the instruction, and iterative optimization is carried out through closed-loop feedback until the actually measured extinction ratio reaches a target value; and finally recording and solidifying the optimal voltage value. According to the invention, single and accurate extinction ratio overall measurement is used for replacing two times of error-prone independent optical power measurement, full-automatic closed-loop control is realized, the precision, efficiency and consistency of optical power balance are remarkably improved, and the skill requirements on operators are reduced.

According to the fiber-optic gyroscope for suppressing the relative intensity noise of the light source based on the double Y waveguides, interference signal light output by the same light source and noise polarization correlation of matched reference light are utilized, fine adjustment is carried out through the design of the two Y waveguides, so that the output intensity of the two Y waveguides is precisely consistent, polarization states are orthogonal, and the relative intensity noise of the gyroscope light source is suppressed; the precision of the gyroscope is improved; multiple polarization beam splitter assembly light paths are specially designed in a gyroscope light path, polarization state orthogonality and equal-light-intensity light splitting and light combination can be achieved, the specific use method of the gyroscope light path design is further provided, fiber-optic gyroscope homologous interference signal light and matched reference light can specifically meet the adjustment requirements, and the method is suitable for popularization and application. The light source relative intensity noise is effectively reduced, and the output signal-to-noise ratio is improved. The device is simple in design structure, low in implementation difficulty, capable of being finely adjusted, high in adaptability, good in noise suppression effect, suitable for single-axis and multi-axis fiber-optic gyroscopes and also suitable for other fiber-optic sensors with similar optical path structures.

The invention provides a dual-super satellite maneuvering ground test system and method based on air floatation gravity unloading. The platform cabin body and the load cabin body are mainly formed by building aluminum profiles and aluminum plates, and the platform cabin body is located on a single-axis air floating platform or a three-axis air floating platform; the load cabin uses a self-carrying gas cylinder to supply gas and floats on the marble platform through a plane gas bearing. The two cabins are respectively provided with a power supply module unit capable of providing related power supply, a central computer for operating a real-time system, a gyroscope for measuring the angular velocity and an auxiliary cable. Meanwhile, the two cabins are connected through a magnetic suspension actuator. By installing corresponding execution mechanisms in the platform cabins, full-physical test verification in the aspects of cooperative steady-state control of the two cabins of the double-super satellite, rapid attitude maneuver control, inter-cabin cable disturbance and the like can be achieved. The test method has the advantages of simple structure, low manufacturing cost and rapidness in implementation.

An interferometric inertial ultracold-atom sensor of gyrometer type, including an atom chip comprising at least one set of a first and second elementary sensor, a power-supplying device, the magnetic-field generator and the power-supplying device being configured to apply the magnetic field, the DC currents and the microwave signals in a predetermined sequence, the arrangement of the group of one or more conductive elements of each sensor and the sequence further being configured so that the path associated with the first elementary sensor and the path associated with the second elementary sensor are identical and traced simultaneously and in inverse directions by the clouds of ultracold atoms associated with a given internal state, the sensor further comprising a detecting system.

The invention provides a thin-film lithium niobate integrated optical engine for a fiber-optic gyroscope. The thin-film lithium niobate integrated optical engine comprises a substrate, a lower cladding, a lithium niobate thin-film waveguide core layer and an upper cladding, the lithium niobate film waveguide core layer comprises an incident unit, a polarizing unit, a coupling unit, a beam splitting unit, a spot size conversion unit, a phase modulation unit and an emergent unit; the input unit and the polarization unit are gas-phase proton exchange waveguides and naturally have a polarization function; the coupling unit and the beam splitting unit are integrated into a whole, the structure is 2 * 2MMI, and a gas-phase proton exchange process is adopted for preparation; the phase modulation region adopts a lithium niobate film ridge waveguide structure, and coplanar traveling wave electrodes are arranged to realize an electro-optical modulation function; and spot-size conversion structures are additionally arranged between the gas-phase proton exchange waveguide and the ridge waveguide as well as between the ridge waveguide and the output optical fiber, so that mode field matching is realized. According to the embodiment of the invention, the lithium niobate film platform is utilized, and gas-phase proton exchange is combined with a ridge waveguide etching process, so that multiple functions of polarization, coupling, beam splitting, modulation and the like are integrated, the problem of optical coupling loss is solved, and the purposes of miniaturization and low cost of future fiber-optic gyroscopes are achieved.

An accelerometer-type interferometric ultracold atom inertial sensor including an atom chip including at least one set of a first and a second elementary sensor; an atom generation device; a generator for generating a uniform magnetic field; a power supply device; with the arrangement of the group of one or more conductive elements of each sensor and the sequence being further configured so that the trajectories associated with the first elementary sensor and the trajectories associated with the second elementary sensor are parallel to each other, are of the same length, are covered simultaneously and so that the departure direction of the first clouds, from the first and the second elementary sensor respectively, are opposite; the sensor further comprising a detection system.

Embodiments utilize an optical frequency comb generator coupled to an optical resonator of an optical gyroscope. The optical frequency comb generator generates an optical frequency comb having frequency peaks that each correspond to a respective resonance frequency of the optical resonator. A control servo can be coupled to the optical frequency comb generator and controls the optical frequency comb output from the optical frequency comb generator. In doing so, the optical frequency comb remains tuned to the resonance frequencies of the optical resonator during gyroscope operation.

The invention provides an optical fiber inertial navigation system based on a three-axis vibrating beam accelerometer, which comprises a three-axis vibrating beam accelerometer, an SOC processor or MCU processor, a satellite navigation module, a power supply module and an optical fiber gyroscope assembly, the three-axis vibrating beam accelerometer is composed of three orthogonally installed vibrating beam accelerometers, a peripheral circuit and the like, and is an integral assembly; a frequency pulse is directly output or acceleration data is output to the SOC processor or the MCU processor through an RS422 serial port; the SOC processor or the MCU processor exchanges data with the fiber-optic gyroscope assembly and the satellite navigation module through a UART serial port, and the power supply module converts an externally input 9V-36V power supply into a positive / negative 5V power supply and a positive / negative 3.3 V power supply required by the SOC processor or the MCU processor and the fiber-optic gyroscope assembly, and provides voltage for the triaxial vibrating beam accelerometer.

The invention discloses an integrated optical chip, a preparation method and an optical gyroscope, the integrated optical chip comprises a first device layer and a second device layer, the first device layer is provided with a phase modulator, the phase modulator comprises two fourth waveguides used for being connected with an interference ring, the second device layer is provided with a detection unit, and the detection unit comprises two fourth waveguides used for being connected with the interference ring. The detection unit comprises a first coupler and a detector, the first coupler comprises a first waveguide, a second waveguide and a third waveguide, the first waveguide is used for connecting a light source, the first waveguide is connected with the third waveguide, the second waveguide is connected with the third waveguide, and the third waveguide is connected with the phase modulator; the detector is connected with the second waveguide; wherein a light beam is transmitted to the phase modulator through the first waveguide and the third waveguide and is transmitted to the interference ring through the phase modulator, and a test light beam transmitted back by the interference ring is transmitted to the detector through the third waveguide and the second waveguide.

The invention relates to a disassembly-free online self-calibration double-shaft laser gyroscope strapdown inertial navigation implementation method, which designs a modulation working mode based on double-shaft rotation, according to the design, a double-shaft rotating mechanism is additionally arranged on an inertial navigation unit, and the inertial navigation unit respectively rotates around three gyroscope sensitive shafts by utilizing an outer horizontal shaft and an inner azimuth shaft; exciting a navigation error generated by a scale factor error and an installation error of the laser gyroscope; sensitive shafts of the three accelerometers are enabled to point to the sky respectively, and navigation errors generated by scale factor errors, installation errors and zero positions of the accelerometers are excited; and then obtaining the navigation errors by taking external reference information as a benchmark, establishing an error relation model between the navigation errors and parameters needing to be calibrated, and completing estimation of each calibration parameter by adopting a Kalman filtering algorithm, so as to realize disassembly-free online self-calibration of the double-shaft laser gyroscope strapdown inertial navigation.

The invention belongs to the technical field of integrated optics and inertial sensing, and particularly relates to a full-on-chip integrated photon chip gyroscope. The active devices integrated on the silicon-based heterogeneous integrated chip comprise an SLD light source, a thin film lithium niobate modulator and a detector; the passive device integrated on the silicon-based heterogeneous integrated chip comprises an isolator, a one-to-two coupler, a polarizer, a one-to-two coupler and an on-chip waveguide ring; the silicon-based heterogeneous integrated chip is also integrated with a spot size converter, a bending waveguide, a bending waveguide and a spot size converter.

The invention provides a method and a system for realizing a weak measurement enhanced chip-level microcavity gyroscope. The method comprises the following steps of: 1, providing a coherent state input by a system by using a single-frequency laser; 2, the output of the single-frequency laser is switched between a first path and a second path through an optical switch, the laser beam is transmitted to the first path in the first half part of the period, and the laser beam is transmitted to the second path in the second half part of the period; 3, the light transmitted along the first path and the second path respectively passes through an optical resonant cavity to sense the rotation angular speed, and a weak value amplification effect is achieved by setting front and back selection states; and step 4, weak measurement enhanced output results transmitted along the first path and the second path are respectively received by a photoelectric detector, and the value of the rotation angular velocity is demodulated according to the obtained output results. According to the invention, the optical microcavity is used as a sensing unit of the gyroscope, the sensing performance of the integrated optical gyroscope is greatly enhanced through a weak measurement technology, and the whole set of system can realize chip-level integration.