97 results about "Satellite orbit" patented technology

The application relates to the field of meteorological data processing and satellite navigation application, and provides a multi-source meteorological data fusion method and system based on a Beidou space-time reference. The method comprises the following steps: acquiring Beidou data and multi-source meteorological data to be fused, taking the coordinated universal time timestamp output by a Beidou ground-based enhancement station as a global time reference, and setting a sliding window; taking the world geodetic coordinate system corresponding to the Beidou positioning data as a space reference, resampling the multi-source meteorological data to a preset standard grid, and combining terrain elevation data to construct a unified space coordinate system; calculating the confidence degrees of fused static terrain features and dynamic change features based on Beidou satellite orbit residual and clock difference parameters, adjusting the feature weights of the fused static terrain features and dynamic change features, and generating an enhanced fusion feature matrix.

The application provides a kind of InSAR deformation monitoring point high-precision geometric positioning method combined with three-dimensional model data, belongs to synthetic aperture radar technical field, comprising: converting three-dimensional model data into space rectangular coordinates, combined with satellite orbit parameter iteration to solve row and column coordinates in SAR image, calculate the slant range projection distance of satellite-observation vector, screen and eliminate invalid data in shadow area;With the screening result as a mask, obtain a subset of three-dimensional model data, calculate the row and column coordinates of the InSAR deformation monitoring point of the subset of three-dimensional model data, and search for candidate points based on plane geometric constraints, match the accurate elevation of the monitoring point by height system deviation;Based on the determined accurate elevation, construct the RD positioning model of distance constraint, Doppler frequency constraint and ellipsoid constraint, and solve the high-precision geometric position of InSAR deformation monitoring point. It can realize the high-precision geometric positioning of infrastructure InSAR deformation monitoring point, and improve the applicability in infrastructure fine deformation monitoring.

The application relates to the technical field of satellite intelligent access, and discloses a multi-satellite intelligent access method, system and equipment based on AI prediction, which comprises the following steps: collecting satellite orbit data and user terminal position data of a multi-satellite system, and performing satellite position prediction through an orbit prediction neural network to obtain satellite predicted positions and communication window information; each intelligent agent perceives communication environment parameters and constructs an environment perception vector; a multi-agent strategy network is driven based on the satellite predicted positions and the environment perception vector to generate a first access strategy; each intelligent agent performs resource conflict processing according to the first access strategy to obtain a second access strategy; the application adopts a multi-agent architecture to replace traditional centralized control, each intelligent agent has independent decision-making capability and realizes cooperation through a distributed negotiation protocol, single-point failure problems are avoided, robustness and scalability are improved, and resource competition and access conflicts are effectively reduced.

This invention proposes a high-dynamic real-time yaw rate adjustment and image shift compensation optical scanning imaging method and device, belonging to the field of optical remote sensing technology. It solves the technical problem of ensuring the quality of satellite on-orbit imaging. The method includes: using a combined imaging mode of vertical orbit scanning with a tilting mirror and pitch return to perform high-dynamic vertical orbit wide-area scanning imaging, determining the satellite imaging motion law, and establishing a high-precision multi-coordinate system object-image geometric mapping and image shift calculation model to calculate the variation law of image shift compensation parameters; measuring satellite orbit information, attitude information, and camera optical axis pointing information through a high-precision sensor, predicting the camera optical axis motion law using filtering, and substituting it into the image shift calculation model to obtain the line frequency; and achieving graded yaw rate adjustment through fixed yaw rate adjustment, curve fitting, and adjustment of the installation angle. This invention is applied to optical remote sensing satellites with high-dynamic vertical orbit wide-area scanning imaging, achieving on-orbit image shift compensation imaging that balances wide-area coverage and high resolution.

The application discloses a non-cooperative target satellite rendezvous orbit design method based on active disturbance rejection control and belongs to the technical field of space orbit control. In order to solve the problem of modeling and simulation of relative motion between a mobile satellite and a target satellite under the condition that the parameters of the target satellite are unknown, the application calculates initial position and velocity components in the first geodetic coordinate system of the earth center according to prior orbit parameters of the mobile satellite and the target satellite; a dynamic and kinematic model of the mobile satellite and the target satellite is established; a state equation of relative motion between the mobile satellite and the target satellite is constructed by taking relative motion position, velocity and disturbance acceleration as independent variables; an extended state observer is adopted to estimate state variables; a mobile satellite orbit motion control model is established based on a proportional and differential control framework; and disturbance acceleration is compensated by adopting active disturbance rejection design to realize the rendezvous orbit design of the non-cooperative target satellite. The application does not need to accurately obtain orbit motion characteristics of the target satellite, and the method has strong adaptability.

A method, system, product, equipment, and storage medium for autonomous control of the satellite's semi-major axis based on energy constraints are disclosed. Belonging to the field of on-orbit satellite orbit control, this invention solves the problem that existing technologies rely on manual ground planning and command uploading, making it difficult to meet the needs of efficient autonomous orbit control for large-scale constellations. The method involves acquiring the satellite's real-time position and velocity, calculating the corresponding orbit control discrimination parameters, combining a bilateral semi-major axis threshold orbit control strategy to obtain the required orbit control quantities, acquiring the current solar phase angle and satellite orbit parameters, calculating the shadow area initiation phase, and the start time of control. Based on the required orbit control quantities and the energy constraints of a single orbit control operation, the planned orbit control duration parameters are calculated. The start time and planned orbit control duration parameters are used as orbit control execution parameters to achieve autonomous control of the satellite's semi-major axis.

The application relates to a rotation error correction method of a distributed autonomous navigation constellation, and comprises the following steps: S1, each satellite calculates the orbit plane orientation error of the satellite in orbit and distributes the result to all visible satellites in the constellation in real time; S2, each satellite fits a local constellation rotation quantity according to the orbit plane orientation error of the satellite and the collected orbit plane orientation error; S3, each satellite determines a virtual satellite orbit observation quantity according to the local constellation rotation quantity of the satellite; S4, each satellite constructs a conditional constraint equation of virtual observation according to the virtual satellite orbit observation quantity and the second type of non-singularity orbit root number; and S5, each satellite solves the satellite orbit through filtering according to the conditional constraint equation of virtual observation, so that the overall rotation effect of the constellation is inhibited and corrected. The application can inhibit the rotation effect of the constellation, improve the distributed autonomous orbit determination precision of the satellite, does not increase the inter-satellite data interaction communication pressure, and can stably maintain the constellation configuration for a long time.

The application discloses a kind of multi-star multi-station space-ground communication window timing planning methods based on constraint driving time grid, comprising: based on the satellite orbit parameters of the constellation to be studied, ground station position parameters, combined with constraint condition configuration, carry out visibility calculation, generate the visible time window of each ground station and each satellite, combined with the number of each ground station antenna, obtain the visible time window based on antenna granularity;According to the grid interval of constraint driving, carry out grid index calculation and persist for each visible time window;Two-stage window timing planning is carried out to all visible time windows in constellation, in the first stage, carry out continuity preliminary selection, by traversing all visible time windows, successively execute multidimensional conflict detection and constraint verification, obtain preliminary selection result;In the second stage, traverse the preliminary selection result of each satellite, carry out recursive candidate filling to the gap position between adjacent time windows, to maximize the filling communication gap;Output scheduling scheme and evaluation index.

An inter-satellite pointing target attitude high-precision real-time online prediction method, first, the ground uses the orbit determination program corrected by on-orbit data observation to generate a double-satellite orbit position and velocity value sequence in a predetermined time period, and samples according to the control period, then for each sampling time, the double-satellite orbit position and velocity is used to establish the local orbit coordinate system, and the component of the target star position vector in the local orbit coordinate system is calculated, the pitch and yaw target attitude angle values are calculated according to the target attitude angle definition, the pitch target angle sequence is linearly averaged and estimated, the average orbit period value and the long-term change rate parameter are calculated, and the modified sequence after deducting the long-term change rate is given, for the pitch target angle correction sequence and the yaw target angle sequence, data of a specified average orbit period number is taken from a specified initial time, the fitting coefficient is calculated, finally the generated fitting coefficient is uploaded to the satellite, and the satellite uses the high-precision fitting determination formula to calculate the inter-satellite pointing target attitude angle online every control period.

This invention discloses a ground-based experimental system and method for onboard autonomous maneuvering mission planning. It utilizes a ground-based telemetry, tracking, and command (TT&C) simulation module to manage TT&C resource constraints, satellite-ground status, and mission requirements based on the test scenario. An onboard computer equivalent module performs autonomous mission planning based on mission instructions generated by the ground-based TT&C simulation module, generating control commands or mission execution sequences. A spacecraft dynamics simulation module determines the satellite's orbit, attitude, and visibility based on the control commands. A space environment simulation module generates sensor simulation data based on the orbit and attitude. A navigation sensor simulation module initiates or terminates the mission based on control commands and generates measurement data based on the sensor simulation data, sending it to the onboard computer equivalent module. A payload execution simulation module simulates the payload's operation process based on the mission execution sequence. This allows for the simulation and comprehensive verification of the entire mission planning algorithm, from mission injection to execution feedback.

This invention discloses a multipath error fusion correction method and system based on BeiDou multi-orbit differences. The method includes: collecting BeiDou carrier phase observation data from a reference station and a monitoring station; obtaining double-difference residuals through preprocessing and double-difference calculation, and converting them into single-difference residual sequences; classifying BeiDou satellites into three categories based on their orbital types: geostationary orbit satellites, inclined geosynchronous orbit satellites, and medium Earth orbit satellites; extracting stable background information from the GEO residuals, slowly changing information from the IGSO residuals, and anomalous disturbance information from the MEO residuals by combining satellite azimuth and elevation angle information; constructing a basic hemispherical model based on the stable background information of each satellite, and using the stable background information, slowly changing information, and anomalous disturbance information to constrain and update the basic background correction value, generating the current epoch multipath correction value; and applying the correction value to the corresponding satellite observation value to complete the observation correction and deformation monitoring calculation.

The present application relates to a kind of unmanned aerial vehicle-multiple orbit satellite uplink transmission interruption performance analysis method.The orbit parameters of multiple orbits where satellite is located are obtained;The probability density of the distance between unmanned aerial vehicle and satellite in respective orbit is determined based on the orbit parameters;The probability density function and cumulative distribution function representing the distance distribution between unmanned aerial vehicle and satellite in respective orbit are derived based on the probability density;Based on the overlapping interval between multiple orbits, the probability density function and cumulative distribution function of the distance between unmanned aerial vehicle and satellite in multiple orbits are expressed in a segmented manner, which accurately describes the distance distribution between satellite and unmanned aerial vehicle;The outage probability of satellite communication link is calculated by combining the segmented expression with the signal-to-noise ratio distribution characteristics of satellite communication link.The present application quantitatively analyzes the influence of satellite orbit parameters and signal transmission power and other system parameters on the outage probability of satellite communication link through the closed-form expression of the outage probability of unmanned aerial vehicle-multiple orbit satellite uplink transmission communication link.

This invention relates to the field of remote sensing satellite orbit control technology, and discloses a satellite autonomous pipeline control method based on differential interferometric SAR imaging missions. The method includes: acquiring initial satellite orbit parameters; employing a multi-objective optimization algorithm for orbit optimization under a high-order gravity field; sampling and constructing a reference orbit point set; calculating orbit control deviations based on the actual orbit and the reference orbit; generating orbit control triggering rules and avoidance strategies through ground system simulation; executing orbit control strategy generation and control onboard system; and evaluating orbit control effectiveness and the evolution trend of orbit control deviations through the ground system. Existing technologies mainly rely on ground command injection, making it difficult for satellites to achieve efficient autonomous orbit control when performing heavy-orbit differential interferometric SAR imaging missions, and hindering the decoupling of orbit control and imaging tasks. This invention improves the efficiency and autonomy of orbit control, the execution efficiency of imaging missions, and the safety of on-orbit operation by constructing a closed-loop control system encompassing satellite-ground collaboration, strategy formulation, command execution, and effect evaluation.

This application relates to a high-precision modeling method for low-Earth orbit (LEO) satellite orbits based on measured data correction. The method includes: first, acquiring measured orbital error data of in-orbit LEO satellites; setting the simulation scenario duration; periodically extending or pruning / segmenting the error data; generating a pseudo-random sequence using a 10-level feedback shift register; modulating and combining the pseudo-random sequence to obtain a first and a second sequence; filtering the valid second sequence through correlation calculation to obtain uncorrelated sequences for each segment; finally, combining and sampling according to the number of satellites, adding the orbital error to the error-free orbit to achieve high-precision modeling. This method can accurately reflect the characteristics of measured orbital errors, achieving high-precision modeling of LEO satellite orbits.

This invention relates to the field of satellite telemetry, tracking, and command (TT&C) technology, and provides a satellite orbit prediction method, system, equipment, and medium for a multi-coordinate system. The method includes the following steps: S1: Receiving prediction request parameters input by the user, the prediction request parameters including satellite identifier and prediction type; S2: Obtaining the satellite orbit status based on the satellite identifier; S3: Identifying the prediction algorithm to be used based on the prediction type; S4: Performing prediction based on the satellite orbit status and the prediction algorithm; S5: Outputting the prediction result. This solution can unify the multi-coordinate system prediction interface, improve prediction efficiency, simplify the operation process, ensure data consistency, optimize coordinate transformation, and enhance system scalability.

The application discloses a ground test system and method for on-orbit autonomous mobile task planning, which comprises a ground measurement and operation control simulation module, a satellite computer equivalent module, a spacecraft dynamics simulation module, a space environment simulation module, a navigation sensor simulation module and a load execution simulation module. The ground measurement and operation control simulation module generates a task instruction based on a test scene, a measurement and operation control resource constraint, a satellite-ground state and a task demand. The satellite computer equivalent module generates a control instruction or a task execution sequence based on the task instruction generated by the ground measurement and operation control simulation module. The spacecraft dynamics simulation module determines a satellite orbit, an attitude and visibility based on the control instruction. The space environment simulation module generates sensor simulation data based on the orbit and the attitude. The navigation sensor simulation module starts or terminates a task based on the control instruction and generates measurement data based on the sensor simulation data and sends the measurement data to the satellite computer equivalent module. The load execution simulation module simulates a load working process based on the task execution sequence. The application can simulate and verify the whole process of a task planning algorithm from task injection to execution feedback.

The application discloses a high-cost-performance all-weather antenna precise star tracking implementation method and system, and relates to the fields of antenna tracking and satellite application. The method comprises the following steps: obtaining antenna position data, satellite orbit data and bit protection data; calculating the spatial orbit position of a satellite in a future time period, generating antenna guide data after correcting the pointing error of the antenna; publishing the antenna guide data to an antenna control unit; and controlling the antenna to point to the satellite according to the antenna guide data. The antenna guide data is format data of the azimuth angle, the elevation angle and the polarization angle required by the antenna for precise star tracking at any time and any geographical position. The antenna control unit is an execution mechanism for adjusting the azimuth angle and the elevation angle of the antenna. The application simplifies the construction complexity of an antenna tracking system, shortens the construction period, and realizes the function of precise star tracking of the antenna under all-weather conditions at low cost, and is suitable for the automatic tracking of high, medium and low orbit satellites.

This invention discloses a space-ground coordinated radiometric characteristic calibration method for spaceborne active microwave sensors in the field of radar Earth observation technology. It constructs a space-ground coordinated calibration system consisting of a radiation reference source satellite and a ground calibration processing station. The method includes: determining the orbital parameters of the radiation reference source satellite; the satellite transmitting signals to the ground station in Earth observation mode, using a known RCS target on the ground to calibrate its own antenna gain and link gain; receiving signals from the satellite to be calibrated in Earth observation mode, accurately calculating and transmitting echo signals based on the calibrated parameters; and the satellite to be calibrated calibrating its own transmit / receive link gain based on the received echo signals. This invention can be widely applied to the on-orbit radiometric calibration of active microwave sensors such as synthetic aperture radar, altimeters, and microwave scatterometers, significantly improving calibration frequency and accuracy, supporting multi-band, high-stability quantitative remote sensing tasks, and providing reliable technical support for precise observation in fields such as ocean monitoring, weather forecasting, and topographic mapping.

The application relates to a target detection simulation method based on a satellite-borne load, which comprises the following steps: satellite orbit simulation, star background simulation, visible target judgment and detection image simulation; image processing is performed on the ideal detection image so that the detection image simulation result approaches the detection image of the actual satellite-borne load. The method is realized by using C++ programming to improve the algorithm safety and flexibility.

The application provides a satellite orbit prediction method, system and device based on revisiting nominal orbit, relates to the technical field of satellite orbit prediction, and the prediction method comprises the following steps: acquiring on-satellite GPS telemetry data of a satellite; obtaining a descending node time and a descending node longitude of an actual orbit of the satellite within a preset time period according to the on-satellite GPS telemetry data; matching the descending node longitude of the actual orbit with a plurality of descending node longitudes of a revisiting nominal orbit stored in advance, selecting a descending node state corresponding to the descending node longitude of the revisiting nominal orbit with the minimum deviation from the descending node longitude of the actual orbit as a matching nominal orbit state; and inputting the descending node time of the actual orbit and the matching nominal orbit state into an improved high-precision orbit dynamics model for orbit recursion to obtain predicted orbit data. The application can realize long-time and high-precision orbit prediction, and significantly improves the reliability and precision of satellite mission planning.

This application provides a method and system for correcting the brightness temperature of a spaceborne one-dimensional integrated aperture microwave radiometer. The method includes: acquiring two-dimensional observed brightness temperature data O along the vertical satellite orbit and along the satellite orbit for different ascent and descent orbits of the microwave radiometer; acquiring external data such as atmospheric profiles, surface data, and sea surface salinity along the radiation transmission path to obtain simulated Earth radiation brightness temperature data B, and removing outlier data; subtracting the observed brightness temperature data from the simulated brightness temperature data to obtain O-B data for multiple single orbits, and removing outlier data; taking the median of the O-B data to obtain the average difference in O-B brightness temperature and the two-dimensional corrected brightness temperature; dividing the average difference in O-B brightness temperature by the observed brightness temperatures in the corresponding two vertical directions to obtain two-dimensional relative brightness temperature correction coefficients based on different ascent and descent orbits; and correcting the observed brightness temperature using the two-dimensional relative brightness temperature correction coefficients or the two-dimensional corrected brightness temperature. The advantage of this application is that the established two-dimensional correction coefficients have a better correction effect.

The application relates to a satellite orbit and satellite attitude determination method and device after satellite-rocket separation. The method comprises the following steps: calculating a first position vector and a first velocity vector of a satellite in an epoch equatorial coordinate system according to orbit elements of a rocket in a second earth-centered equatorial coordinate system and a satellite-rocket separation time; determining a second position vector and a second velocity vector of the satellite in a J2000 earth-centered inertial coordinate system based on the first position vector and the first velocity vector; taking the second position vector and the second velocity vector as orbit initial values, and determining orbit parameters of the satellite before injection into an orbit by using an orbit recursion algorithm; determining an attitude direction cosine matrix of the satellite in the J2000 earth-centered inertial coordinate system at the satellite-rocket separation time based on a launch time; and taking the attitude direction cosine matrix as attitude initial values, and determining attitude parameters of the satellite before injection into the orbit by using a star gyroscope combination filtering method. The scheme can quickly determine the orbit and the attitude of the satellite, and improves the autonomous detection capability of the satellite.

A problem to be solved by the present invention is that a host vehicle position calculated on the basis of a GNSS is affected by shielding, reflection, diffraction, and the like of a positioning radio wave due to a structure, depending on a structure environment present around a receiver and an arrangement of positioning satellites at the date and time, and a detected measured position is output in a biased manner. A map processing device 10 of the present invention processes map information used for positioning a host vehicle, and includes: a satellite orbit information acquisition unit 103 that acquires position information of a plurality of positioning satellites; a pseudo distance acquisition unit 102 that calculates a pseudo distance from the plurality of positioning satellites based on positioning radio waves respectively received from the plurality of positioning satellites; a positioning available satellite verification unit 104 that identifies, among the plurality of positioning satellites, a positioning satellite for which a distance to the host vehicle position and the pseudo distance do not match as a positioning unavailable satellite; and a map generation unit 106 that generates a map in which a direction from the host vehicle position to the positioning unavailable satellite is stored in association with the host vehicle position as a shielded range in which a positioning radio wave from the positioning unavailable satellite is shielded.

The application relates to a GNSS high-sensitivity acquisition method and equipment applied to a deep space spacecraft. The core process of the method is as follows: the time and corresponding position of receiving GNSS signals by the spacecraft are acquired, the satellite position at the receiving time is calculated by combining the pre-stored target satellite orbit information, and the signal transmission time is obtained through iterative correction; the starting time of digital intermediate frequency data storage is determined according to the subframe period of the navigation message, so that the key specified bits of the message are completely contained, and the navigation message is stripped by using the fixed and predictable bits; the Doppler center frequency offset is obtained by calculating the relative speed of the line-of-sight direction between the star and the earth, the search range is determined by combining the speed uncertainty, the signal acquisition is completed in the limited range, and the code phase and the carrier frequency offset are solved. The application is suitable for the scene that the deep space signal is weak, the propagation time delay is long, and the Doppler characteristic is complex, the position mismatch error is avoided through iterative correction, a high-precision time reference is acquired, and the GNSS signal acquisition performance is significantly improved.

The application provides a network RTK differential correction number generation method based on Beidou and low-orbit constellation fusion, which comprises data acquisition, receiving pseudorange observation values and carrier phase observation values of Beidou satellite navigation system satellites and low-orbit constellation satellites through a ground reference station receiver simultaneously; constructing a joint observation model of Beidou satellite navigation system and low-orbit constellation, and using an extended Kalman filtering algorithm to estimate receiver clock difference and system bias between the two systems in real time; adaptive weighted differential correction number calculation, calculating pseudorange differential correction numbers of Beidou satellites and low-orbit satellites respectively based on the estimated system bias; correction number broadcasting, dynamically determining the effective duration of the differential correction number of the low-orbit satellite according to the orbit height of the low-orbit satellite, and encoding the correction numbers of the Beidou satellites and the low-orbit satellites into RTCM text format to broadcast to the user end; the user end receives the correction numbers, corrects the local Beidou satellite and low-orbit satellite observation values, performs joint RTK solving, and verifies and confirms ambiguity fixing.

The application provides an interferometric SAR satellite data query method based on space-time baseline precalculation, comprising the following steps: analyzing user order information and extracting product key identification information; screening interferometric SAR satellite product information in the order according to preset product level, imaging mode, orbit direction and other screening rules; obtaining metadata corresponding to the product identification information from the data center storage device according to a metadata specific naming format and a storage path; analyzing satellite imaging parameters and satellite orbit position information in the metadata; taking the product image with the earliest imaging time as the main image for space-time baseline calculation, and taking other product images as auxiliary images; and providing a basis for efficient application of interferometric SAR satellite data products by the user in the future, so as to precalculate space-time baseline information of the queried data products when the user queries the interferometric SAR satellite data products.

The application provides a satellite antenna automatic pointing method based on PPO reinforcement learning, comprising: initializing an antenna controller, a sensor group and a satellite orbit prediction module, loading a pre-trained PPO reinforcement learning model, defining a state space and a continuous action space; based on real-time antenna angle and signal strength data obtained by the sensor group, combining theoretical position data calculated by the satellite orbit prediction module, performing data fusion processing to generate a dynamic state vector; based on the dynamic state vector, performing policy inference processing through an Actor network to generate a continuous action, and performing safety evaluation processing on the continuous action through a Critic network to obtain a safety decision result; based on the obtained state change data after the antenna rotates, performing dynamic reward calculation to obtain a reward value, and storing the reward value and the state change data into an experience pool. By using the method, high-precision pointing control can be realized in a dynamic environment through real-time policy optimization of the continuous action space.

This invention proposes an on-orbit autonomous geometric calibration method and system for wide-field-of-view optical remote sensing satellites. The method includes: camera imaging and transmitting the captured images to an on-board calibration type autonomous identification module; the on-board calibration type autonomous identification module, combined with satellite orbit and attitude data, determines whether the camera's field of view simultaneously images deep space and the ground; if both exist simultaneously, the Earth's edge is extracted as the boundary between stars and landmarks to delineate their distribution areas; if not, the calibration point type is explicitly determined to be either a landmark or a star; based on the calibration point type, the corresponding image is transmitted to an on-board stellar autonomous calibration module or an on-board landmark autonomous calibration module, and geometric calibration parameters are calculated; the calculated calibration parameters are transmitted to an on-board information processing unit for satellite imaging. This invention ensures the geometric calibration accuracy across the entire field of view of the camera; it avoids the process of transmitting satellite images down to the ground for calculation, thus improving the real-time performance of the calibration parameters.