58 results about "Pitch angle" patented technology

The invention belongs to the technical field of new energy equipment anomaly analysis, and relates to a variable pitch component anomaly detection method and system and a readable medium, and the method comprises the following steps: calculating the actual pitch angle standard deviation of a blade, and recognizing whether the variable pitch angle is abnormal or not through the actual pitch angle standard deviation; if the variable pitch angle is not abnormal, the standard deviation of the collected data of all the measuring points is obtained, and whether measurement abnormity exists in all the components or not is judged one by one according to the standard deviation of the collected data; if the measurement abnormity does not exist in each part, calculating the slope of the standard deviation of the collected data, so as to judge whether the standard deviation of the collected data has a rising trend or not and judge whether a gradual deterioration risk exists or not; and if the deterioration risk does not exist, calculating a correlation matrix among the measuring points under various working conditions through the established working condition model, and judging whether the variable pitch component is abnormal under various working conditions according to the correlation matrix. According to the method, more complete and careful abnormal detection of the variable-pitch component can be realized.

The invention discloses an outdoor field large depression angle measurement method and system, and the method comprises the steps: S1, determining the position of a measured target, erecting a calibration ball and a positioning ball, determining the flight height of an unmanned plane, and setting a scanning path; s2, establishing a coordinate relationship among the calibration ball, the positioning ball and the unmanned aerial vehicle; s3, testing the calibration ball and the positioning ball in different directions, and acquiring frequency sweeping echo frequency domain data in different directions; s4, removing the calibration ball, and erecting a measured target at the position of the calibration ball; s5, testing the positioning ball and the tested target in different orientations, and acquiring frequency-sweeping echo frequency domain data in different orientations; and S6, performing phase compensation on the measurement data through theoretical values of different distances from the positioning ball to the radar on the measurement path, and obtaining two-dimensional imaging data and an RCS result of the measured target. The method is suitable for outdoor field measurement, target scattering characteristic diagnosis under complex environments such as large depression angle ground and sea can be realized, flexible deployment requirements can be realized, and the test cost is reduced.

The invention relates to a deep-sea shadow region target rapid orientation estimation method, which comprises the following steps: firstly, performing orientation estimation on a target signal received by a large-aperture horizontal line array by using conventional beam forming, and assuming that a sound source distance is estimated by an existing signal processing method; secondly, on the basis of the virtual source theory, the arrival pitch angles of four primary seabed reflection sound ray paths in the shadow area are calculated; based on the representation relation among the sound ray arrival pitch angle, the target physical orientation and the orientation estimation value, the target orientation estimation result is corrected, then the real orientation of the target is obtained, and the direction finding precision of the deep-sea shadow region target is improved.

The invention relates to the technical field of attitude estimation, in particular to an attitude estimation method in a magnetic interference environment, which comprises the following steps of: obtaining a conversion relation between an Euler angle and a quaternion; calculating the quaternion at the next sampling moment; respectively solving a first state transition matrix, a first process noise matrix and a first prior covariance according to the first state equation; respectively solving a second state transition matrix, a second process noise matrix and a second prior covariance according to a second state equation; elements in the nb-series rotation matrix are used as observed quantities of state variables in the parameter-series rotation matrix, a corresponding Kalman gain is calculated, and a Jacobian matrix is designed by using the observed quantities; calculating an observation noise covariance matrix by using the Jacobian matrix; updating the Kalman gain by using the observation noise covariance matrix; and updating the state equation and the posterior covariance by using the updated Kalman gain and the observed quantity. The method solves the problem of how to prevent the calculation of the roll angle and the pitch angle from being influenced by magnetic interference when the magnetic interference exists.

The invention discloses a robust adaptive fusion filtering astronomical attitude determination method and system, and belongs to the technical field of radio navigation. The method comprises the following steps: constructing an integrated navigation model of a starlight and inertial integrated navigation system based on Lie group description; obtaining an observation residual error and an observation residual error covariance of a corresponding mode; robust and adaptive mode parallel sub-filtering is carried out, and posterior states and covariances in the two modes are updated; updating the mode probability; and fusing the updated posterior state with the covariance to obtain fusion output of parallel sub-filtering, taking the fusion output of the parallel sub-filtering as final estimation of the starlight and inertial integrated navigation system based on Lie group description, and outputting an astronomical attitude determination result containing an azimuth angle, a pitch angle and a roll angle. The high-precision astronomical attitude determination method has strong adaptability, strong robustness and accuracy when coping with complex noise and measuring outliers, and can realize high-precision astronomical attitude determination of starlight and inertial integrated navigation in a complex dynamic environment.

The invention discloses an equipment attitude automatic correction method and device and an optical terminal intensity instrument, the equipment attitude automatic correction method is applied to a preset monitoring terminal comprising a triaxial MEMS accelerometer and a magnetometer, and the method comprises the following steps: collecting acceleration and magnetometer data; calculating acceleration stable three-axis offset; calculating roll and pitch angles and determining a horizontal plane; positioning magnetic north and calculating a magnetic north azimuth angle; calculating a magnetic declination angle and a yaw angle by combining longitude and latitude; generating a rotation matrix and converting a coordinate system; judging angle change and updating the matrix; and completing calibration and attitude stabilization. According to the technical scheme provided by the invention, the monitoring terminal equipment can be ensured to automatically and accurately adjust and stably maintain the attitude after being installed, so that the effective operation of the earthquake monitoring and early warning system is ensured, and the earthquake disaster prevention and flooding earthquake (vibration) monitoring performance is improved.

The embodiment of the invention provides an aviation gravity and magnetic vector dynamic measurement method based on multi-source data synchronous fusion, and relates to the technical field of data acquisition, after sensor array data on a driving flight platform is acquired, a specific force measurement value, a carrier pitch angle, a carrier roll angle and a carrier motion parameter are calculated and output; calculating three output gravity disturbance components by adopting carrier motion parameters and specific force measurement values; fusing total field data of the optical pumping magnetometer to carry out magnetic vector calculation on three-component data of the fluxgate and outputting geomagnetic total elements; and taking a carrier pitch angle, a carrier roll angle, a carrier position, a carrier speed and a carrier course angle as carrier pose data, combining the geomagnetic total elements and the carrier pose data, and outputting a dynamic measurement result of the gravity-magnetic vector field. The problems that in the prior art, gravity measurement and magnetic measurement are separated, equipment redundancy is low in efficiency, collection time is asynchronous, and data precision is reduced are solved. The effect of high-precision, high-dynamic and high-efficiency synchronous acquisition of the gravity and magnetic vector data under the single platform is achieved.

The invention relates to a high and low orbit satellite tracking method based on geomagnetic correction. The method comprises the following steps: constructing a geomagnetic model, calculating an azimuth angle and carrying out magnetic field interference analysis; carrying out factory calibration by utilizing a three-dimensional geometric calibration mode, including horizontal correction and vertical correction; the current azimuth angle and pitch angle are continuously corrected based on the carrier coordinate system by using the signal intensity, and the deviation is obtained so as to continuously approach the real angle; utilizing the known coordinates of the three-dimensional space to inversely calculate the current position; and the current data is corrected by using the big data, so that the current data meets the use requirements. The current attitude angle and the satellite signal receiver are used for tracking the target satellite, and then the known azimuth angle is used for correcting the geomagnetic data, so that the azimuth angle precision is improved, the cost of a phased-array antenna or a mechanical antenna is reduced, the tracking precision is improved, and the tracking speed is improved.

The application belongs to the technical field of magnetic variable measurement, and solves the technical problem of poor magnetic field measurement precision caused by single attitude adjustment of the existing Hall measurement system. The vacuum Hall measurement system for the in-vacuum undulator comprises a vacuum chamber, a Hall probe and a motion execution mechanism. The motion execution mechanism comprises a guide rail and a pose adjustment mechanism. The Hall probe is movable along the extension direction of the guide rail. The pose adjustment mechanism drives the Hall probe to move three-dimensionally to measure the magnetic field distribution through the guide rail. The pose adjustment mechanism comprises a Z-direction swing platform to adjust the pitch angle of the guide rail, a Y-direction swing platform to adjust the roll angle of the guide rail, a Y-direction moving platform, an X-direction moving platform and a Z-direction moving platform. The application can adjust the attitude in two directions and the position in three directions in space, reduce the parasitic displacement, make the Hall probe move three-dimensionally in the undulator and improve the magnetic field measurement precision.

The application discloses a kind of space target abnormal change discrimination methods based on imaging auxiliary data, first acquire the azimuth and pitch angle of space target turntable theory and measured data, using improved amplitude limiting filtering algorithm to eliminate outliers;Filter estimation is carried out to the data after eliminating outliers, to obtain estimated real data to correct measured data;The actual similarity between the estimated real data and the theoretical data is calculated, and the similarity function is fitted;For continuous new time, the absolute value of the difference between the actual similarity and the estimated similarity obtained by the similarity function is taken as the similarity difference value.The application does not need astronomical positioning, can detect target orbit abnormal change while imaging target characteristics, improve the timeliness of research and judgment and the safety of space target on-orbit operation, effectively reduce the risk of space target collision, fill the blank of detecting target orbit abnormal change by using on-orbit satellite small aperture telescope.

This invention discloses a method for measuring the magnetic field pitch angle using rotating Doppler microwave reflection. A Doppler backscattering meter (DBS) simultaneously transmits X-mode and O-mode polarized microwave signals to the plasma and receives the scattered signals returning along the transmitted optical path. A beam splitter divides the received scattered signals into two paths: one path enters the original DBS, and the other enters a rotatable antenna to adjust the vibration direction of the received electric field component. Based on the steady-state discharge conditions of EAST, a high-speed rotating platform rotates the rotatable antenna 360° during the stable discharge period, completing the scanning of the vibration directions of the electric and magnetic field components of the scattered signal, thus obtaining the magnetic field pitch angle at the detection frequency cutoff layer. This method is low-cost, causes almost no interference to the plasma, and allows for real-time, interference-free measurement of the magnetic field pitch angle at a localized location within the core of a magnetic confinement fusion device.

The application discloses a method for measuring a pitch angle of a magnetic field in a core of a magnetic confinement fusion device, which comprises the following steps: simultaneously emitting microwave signals of X-mode and O-mode polarization to plasma by a Doppler backscattering diagnostic system (DBS), and receiving scattered signals returned along a transmission light path; dividing the received scattered signals into two paths by a beam splitter, one of which enters the original DBS, and the other of which enters a rotatable antenna for selecting a vibration direction of an electric field component; adjusting an included angle between the vibration direction of the electric field component of the rotatable antenna and the vibration direction of the electric field component of the DBS transmission antenna according to the vibration direction of the electric field component of the DBS transmission antenna, obtaining the vibration direction of the electric field component of the backscattering signal through the ratio of the signal intensity received by the two antennas, and further obtaining the pitch angle of the magnetic field. The above method has the advantages of low cost, almost no interference to plasma, high time resolution, and can be used for real-time measurement of the pitch angle of the magnetic field in the core of the magnetic confinement fusion device without interference.

The present invention discloses a method for estimating the pitch angle of an aerial target using a spaceborne radar based on satellite posture. The method comprises: selecting the position of the spaceborne radar, the position of the aerial target, the projection point of the aerial target on the ground, and the position of the center of the earth as reference points, and constructing a geometric relationship model between the spaceborne radar and the aerial target; obtaining a first parameter set and a second parameter set based on the geometric relationship model; constructing a first expression for a lower viewing angle according to the first parameter set, and constructing a second expression for a lower viewing angle according to the second parameter set; and jointly solving the pitch angle by using the first expression for the lower viewing angle and the second expression for the lower viewing angle. The present invention solves the problem of large errors in the pitch angle estimation value of the aerial target when the spaceborne radar undergoes posture transformation.

This application belongs to the technical field of vibroseis seismic exploration. Specifically, it relates to a method, device and system for attitude data fusion of marine vibroseis. By obtaining the original axis data of multiple detection sensors; fusing and filtering the roll angle data and pitch angle data of the gyroscope with the roll angle and pitch angle data of the acceleration sensor to obtain the roll angle data and pitch angle data of multiple detection sensors; performing tilt compensation on the magnetometer data based on the roll angle data and pitch angle data of the detection sensors and calculating with the geomagnetic declination at the location of the magnetometer to obtain the tilt-compensated magnetometer data; fusing the tilt-compensated magnetometer data with the yaw angle data of the gyroscope to obtain the attitude angle data. By fusing the measurement data of multiple sensors to estimate the attitude of the vibroseis, the zero drift error of the original sensor signal is reduced, the accuracy of the attitude data is improved, and the non-offset output of the attitude information of the marine vibroseis is realized.

The embodiment of the application provides a dynamic measurement method for aviation gravity and magnetic vector based on multi-source data synchronous fusion, relates to the technical field of data acquisition, and outputs the specific force measurement value, the carrier pitch angle, the carrier roll angle and the carrier motion parameter after driving the flight platform to collect the sensing array data; adopts the carrier motion parameter and the specific force measurement value to output the gravity disturbance three components; fuses the total field data of the optical pumping magnetometer to perform the magnetic vector calculation and output of the geomagnetic full element of the flux gate three component data; takes the carrier pitch angle, the carrier roll angle, the carrier position, the carrier speed and the carrier heading angle as the carrier pose data, combines the geomagnetic full element and the carrier pose data, and outputs the dynamic measurement result of the gravity and magnetic vector field. The problems that the gravity and magnetic force measurement are separated in the prior art, the equipment is redundant and inefficient, the acquisition time is asynchronous, and the data precision is reduced are solved. The effect of high-precision, high-dynamic and high-efficiency synchronous acquisition of the gravity and magnetic vector data under a single platform is achieved.

The invention discloses a method for measuring the spiral angle of a core magnetic field of a magnetic confinement fusion device, and the method comprises the steps: transmitting X-mode and O-mode polarized microwave signals to plasma at the same time through a Doppler backscatterometer diagnostic system (DBS), and receiving a scattered signal returned along a transmitting light path; a received scattering signal is divided into two paths through a beam splitting sheet, one path enters an original DBS, and the other path enters a rotatable antenna and is used for selecting the vibration direction of a receiving electric field component; according to the vibration direction of the electric field component of the DBS transmitting antenna, the included angle between the vibration direction of the electric field component of the rotatable antenna and the vibration direction of the electric field component of the DBS transmitting antenna is adjusted, the vibration direction of the electric field component of a backscattering signal is obtained through the ratio of the received signal intensities of the two antennas, and then the magnetic field pitch angle is obtained. The method is low in cost, almost has no interference to plasma, has high time resolution, and can measure the magnetic field pitch angle at the local position of the core of the magnetic confinement fusion device in real time without interference.

This application describes creating, modifying, and bending electromagnetic solitons at large scales for the various applications. An electromagnetic soliton generator system controls the magnetic soliton such that the orientation, rotation rate, pitch angle, and magnetic field strength of the solitons are modified to provide the described standing waves and generate a magnetic flux differential.

The invention belongs to the technical field of magnetic variable measurement, and provides an in-vacuum Hall measurement system for an in-vacuum undulator, which solves the technical problem of poor magnetic field measurement precision caused by single attitude adjustment of an existing Hall measurement system. The in-vacuum Hall measurement system for the in-vacuum undulator comprises a vacuum chamber, a Hall probe and a motion executing mechanism, the motion executing mechanism comprises a guide rail and a pose adjusting mechanism, the Hall probe can move in the extending direction of the guide rail, and the pose adjusting mechanism drives the Hall probe to move in a three-dimensional mode through the guide rail to measure magnetic field distribution. The pose adjusting mechanism comprises a platform swinging around the Z direction so as to adjust the pitch angle of the guide rail; swinging the platform around the Y direction to adjust the overturning angle of the guide rail; a Y-direction moving platform, an X-direction moving platform and a Z-direction moving platform. According to the invention, the attitude in two directions and the position in three directions in the space can be adjusted, the parasitic displacement is reduced, the Hall probe is enabled to perform three-dimensional motion in the undulator, and the magnetic field measurement precision is improved.

The present invention discloses a method for quickly identifying dim targets of space debris based on daytime guide star images, comprising the following steps: tracking the target according to the predicted value; collecting the target area image and recording it as the image at time T0; adjusting the telescope pointing azimuth angle ΔA and pitch angle ΔE; collecting the target area image and recording it as the image at time T1; comparing the pixels of the image P0 at time T0 and the image P1 at time T1, taking the pixel difference as the image ΔP, searching ΔP, and obtaining the target centroid coordinates; judging the change in the centroid coordinates and determining the target; calculating the target centroid miss amount and adjusting the pointing. The present application can quickly identify dim targets under strong background noise during the day, and after identifying the target, the deviation of the target angle change from the theoretical value can be quickly obtained, which is used for target pointing and distance deviation correction in future daytime space debris laser ranging.

This application discloses a geomagnetic sensor calibration method, apparatus, and electronic device, belonging to the field of electronic device technology. The method includes: when the geomagnetic sensor of the electronic device is detected to be subjected to magnetic interference, acquiring the current yaw angle, pitch angle, rotation angle, magnetic tilt angle, and Earth's magnetic field strength of the electronic device; determining the current standard triaxial magnetic field data of the electronic device based on the yaw angle, pitch angle, rotation angle, magnetic tilt angle, and Earth's magnetic field strength; determining the triaxial magnetic field deviation value of the geomagnetic sensor based on the measurement data of the geomagnetic sensor and the standard triaxial magnetic field data; and calibrating the geomagnetic sensor based on the triaxial magnetic field deviation value.

The invention provides a system and method for improving the azimuth angle measurement precision of a training simulator, and the system comprises a firearm simulator, a magnetic field measurement module and a cooperative control module, the magnetic field measurement module is used for collecting and processing a geomagnetic vector to generate a horizontal component, and the cooperative control module is used for receiving geomagnetic data and inclination angle data to generate a displacement instruction. The beneficial effects of the invention are that through the physical integration of the firearm simulator, the magnetic field measurement module and the cooperative control module, the error coupling of the distributed layout is eliminated, and the orientation measurement stability is improved; a hardware platform support is provided for subsequent leveling and magnetic field interference suppression, and a low-delay dynamic calibration foundation is laid; through the physical linkage design of the universal hinge and the push rod, synchronous adjustment of the pitch angle / roll angle is achieved, and the leveling response time is remarkably shortened; the tilt angle sensor is matched with the closed loop of the push rod, and idle stroke errors of traditional mechanical transmission are eliminated.

The invention discloses an attitude angle stabilizing method and device of an inertial measurement unit, equipment and a storage medium. The attitude angles comprise a pitch angle, a roll angle and a course angle, and the method comprises the following steps: acquiring a current attitude angle of the inertial measurement unit; determining whether filtering stabilization needs to be carried out on the current attitude angle according to the angle fluctuation condition at the current moment; if the current attitude angle needs to be subjected to filtering stabilization, obtaining a stability coefficient, performing filtering stabilization on the current attitude angle according to the stability coefficient to generate a current stable angle, and outputting the current stable angle; and if the current attitude angle does not need to be subjected to filtering stabilization, outputting the current attitude angle. According to the attitude angle stabilizing method of the inertial measurement unit, small-amplitude fluctuation of the attitude angle can be filtered out, and stable attitude angle data can be output.

The application discloses a method for calculating an interplanetary cross scaling coefficient according to particle phase space density correlation characteristics, comprising the following steps: obtaining particle flux sequences of a standard A star and a to-be-scaled B star; under a T89c external magnetic field model, respectively calculating a modified third adiabatic invariant and a second adiabatic invariant of the A star and the B star, and calculating a local magnetic field intensity; performing uniform grid division on time and the third adiabatic invariant, and performing logarithmic uniform grid division on the first adiabatic invariant and the second adiabatic invariant; obtaining a local pitch angle and energy in the grid; screening out points with data in the same grid to obtain particle phase space densities of the A star and the B star respectively; calculating a particle phase space density average in the grid; respectively establishing particle phase space density matrices of the A star and the B star; screening out points with data in the same grid of the particle phase space density matrices of the two stars to obtain a cross scaling coefficient of the B star.

The invention discloses a method for measuring a pitch angle of a magnetic field by rotating Doppler microwave reflection, which comprises the following steps of: simultaneously transmitting X-mode and O-mode polarized microwave signals to plasma through a Doppler backscatterometer diagnostic system (DBS), and receiving a scattered signal returned along a transmitting light path; a received scattering signal is divided into two paths through a beam splitting sheet, one path enters an original DBS, and the other path enters a rotatable antenna to be used for adjusting the vibration direction of a received electric field component; based on the EAST steady-state discharge condition, the rotatable antenna is rotated by 360 degrees through a high-speed rotating platform in the discharge stationary period, scanning of the vibration direction of the scattering signal electric field component and the vibration direction of the magnetic field component is completed, and the magnetic field pitch angle at the detection frequency cut-off layer is obtained. The method is low in cost, almost has no interference to plasma, and can measure the magnetic field pitch angle at the local position of the core of the magnetic confinement fusion device in real time without interference.

A dynamic attitude measurement method for a dual-axis stabilized platform is firstly performed by using an inertial coordinate system rough alignment method to obtain the initial value of the attitude angle, and then a series of navigation solutions of the attitude angle, attitude angular rate, velocity position are performed. In the navigation solution process, the Kalman filter technology is used to perform combined navigation and combined calibration of the strapdown inertial navigation system, and the misalignment angle, velocity error, and position error are estimated. The quaternion, solution velocity, and solution position of the strapdown inertial navigation system are corrected by using the Kalman filter technology to make the calculated navigation coordinate system coincide with the real navigation coordinate system as much as possible. At the same time, if time permits, the error (gyroscope drift and acceleration bias) of the inertial element is also estimated. The method can enable the dual-axis stabilized platform to maintain a stable accuracy of pitch angle and roll angle ≤10" (RMS) under the condition of a large load of an 80kg gravimeter and a large dynamic condition of the fourth level sea state.

The invention relates to a deep sea magnetometer in-situ correction control method, and relates to the technical field of magnetometers, and the method comprises the following steps: S01, obtaining an original magnetic field measurement value, a carrier attitude angle, an angular velocity and a depth in real time through a magnetometer, an inertial navigation unit and a depth sensor carried by a carrier; calculating a geomagnetic reference field and a change rate thereof based on the carrier position and a global geomagnetic model; and S02, constructing a reinforcement learning agent taking the interference model parameter covariance matrix as input, and dynamically generating a maneuvering instruction sequence of yaw angle increment, pitch angle increment, depth increment and stabilization time under the condition that maneuvering constraint conditions of the deep sea operation platform are met. The novel method for in-situ detection and compensation control of the magnetic deviation of the magnetometer carrier can be realized without depending on water surface type maneuvering navigation, so that the accuracy and the reliability of deep sea magnetic measurement data are guaranteed.

The invention discloses a mobile equipment attitude estimation method and device based on IMU nine-axis data, and the method comprises the steps: firstly initializing a quaternion describing the attitude of mobile equipment by taking an east-north-sky coordinate system as a world coordinate system according to the data of an acceleration sensor and a magnetic field sensor in an initial window; the environment magnetic field distribution in a complex environment is approximated to a multi-magnetic dipole magnetic field distribution model, and a weight attenuation geomagnetic field estimation method is designed according to the attenuation characteristics of the magnetic dipole model; then, a multi-layer sliding window method is used, and a gyroscope, an acceleration sensor and a magnetic field sensor are respectively used for estimating quaternion, a roll angle, a pitch angle and a yaw angle of the mobile equipment; finally, the fusion effect of nine-axis sensor data estimation equipment attitude is optimized by using a self-adaptive complementary filter. The precision and the stability of attitude estimation of the mobile equipment can be remarkably improved.

The invention provides an oscillation detection method and an oscillation detection device. The oscillation detection method comprises the following steps: generating an oscillation magnetic field through an oscillation generation device; the oscillation generating device is arranged on an object to be detected; continuously collecting real-time speed information of the to-be-detected object in the oscillation process; performing data processing on the real-time speed information to obtain a pose state oscillogram of the to-be-detected object in the oscillation process; the pose state oscillogram comprises the oscillogram of pitch angle information and roller angle information of the to-be-detected object in the oscillation process. In the embodiment of the invention, the real-time speed information of the to-be-detected object can be continuously detected through the measuring unit to obtain the pose state oscillogram of the to-be-detected object in the oscillation process, so that people can read whether the rotation center and the mass center of the permanent magnet deviate and cause vibration or not through the pose state oscillogram; and whether resonance exists between the oscillator and the helmet or not is judged, so that the vibration phenomenon and the resonance phenomenon can be eliminated.

The invention discloses a space target transaction discrimination method based on imaging auxiliary data, and the method comprises the steps: firstly obtaining the theoretical and measurement data of the azimuth angle and pitch angle of a space target rotary table, and eliminating outliers through employing an improved amplitude limiting filtering algorithm; filtering estimation is carried out on the data after the outliers are removed, and estimated real data are obtained to correct the measurement data; calculating and estimating the actual similarity between the real data and the theoretical data, and fitting a similarity function; for continuous new moments, the absolute value of the difference between the actual similarity and the estimated similarity obtained through the similarity function is calculated as a similarity difference value. According to the method, astronomical positioning is not needed, the target orbit transaction can be rapidly detected while target characteristic imaging is carried out, the research and judgment timeliness and the space target in-orbit operation safety are improved, the space target collision risk is effectively reduced, and the blank that the in-orbit satellite small-caliber telescope is used for detecting the target orbit transaction is filled.