4 results about "Medium Earth orbit" patented technology

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.

A positioning method and device, the method comprising: receiving a first request for requesting positioning; receiving a first signal from a first satellite and a second signal from a second satellite; receiving first information for indicating a first time delay, the first time delay being an ionospheric time delay between the first satellite and the second satellite; and determining a position of a terminal device according to the first signal, the second signal and the first time delay. The method can realize joint positioning of the terminal device based on high medium earth orbit satellites and low earth orbit satellites, help to improve positioning efficiency and positioning accuracy of the terminal device, and can also expand the positioning range as much as possible.

The application provides a kind of low-orbit satellite constellation-oriented computing resource arrangement method, system and equipment, it is related to satellite communication technical field, including: low-orbit satellite receives remote sensing satellite in current time slot under the task set generated, and the computing resource arrangement problem of task set is decomposed into task scheduling subproblem and resource allocation subproblem;Low-orbit satellite models task scheduling subproblem as Markov decision process, utilizes the scheduling strategy network based on deep reinforcement learning to solve Markov decision process, to determine the target low-orbit satellite corresponding to task, and issues task to target low-orbit satellite;Low-orbit satellite models resource allocation subproblem as convex optimization process, utilizes Lagrange multiplier algorithm to solve convex optimization process, to allocate target computing resource for the task received by low-orbit satellite.The application can significantly improve the problem of task demand diversification, satellite resource limited heterogeneity and satellite load imbalance in low-orbit satellite constellation.

This application proposes a testing method and apparatus for a satellite simulation demonstration system. The testing method includes: dividing different physical orbit regions based on the orbital characteristics of low Earth orbit, medium Earth orbit, and high Earth orbit; defining the spatial boundary coordinates and simulation coverage of the simulation layered regions according to the altitude range and orbital characteristics of each physical orbit region; dividing the satellite cluster into multiple satellite groups; configuring corresponding functional testing strategies and performance parameter acquisition strategies for each simulation layered region based on the number, spatial distribution, and on-orbit trajectory of the satellite clusters corresponding to each simulation layered region; generating a general simulation scenario compatible with both functional and performance testing; simultaneously acquiring the functional and performance test items corresponding to the general simulation scenario; and determining whether the overall operating condition of the general simulation scenario meets the preset test requirements. The technical solution of this application can accurately and comprehensively determine the overall operating condition of the system, improving testing accuracy and reliability.