1002 results about "Satellite orbit" patented technology

Electronic monitoring systems and methods that permit full-time tracking and management of, and communication with, monitored clients that carry a client tracking unit and wear a transmitter, by a monitoring individual that carries a wireless portable monitoring device. A central monitoring station having a central database is ported to a plurality of processor interfaces, including RF, GPS, and integrated voice, for example. The central database is wirelessly linked to the portable monitoring device, which is programmed to remotely track and manage clients by way of the respective interfaces. A monitoring unit is coupled to (or includes) a dock that docks the client tracking unit. The client tracking unit has a GPS receiver that receives position signals from satellites orbiting the Earth to permit tracking of the client. The client tracking unit has a battery that houses a receiver that receives signals transmitted by the transmitter and monitors transmitted signals to determine if an alarm event has occurred relating to the transmitter or location of the client. The portable monitoring device has cellular and web browser capabilities that provide access to the central monitoring station by way of a network, and permits retrieval and changing of information by the monitoring individual regarding monitored clients. Information regarding specific clients or a group of clients may be retrieved (optionally using voice commands) from the central monitoring station, modified by the monitoring individual, or selected clients may be directly communicated with using the voice capabilities of the portable monitoring device and client tracking unit.

A continuous wave Light Detection and Ranging (CW LiDAR) system utilizes two or more laser frequencies and time or range shifted pseudorandom noise (PN) codes to discriminate between the laser frequencies. The performance of these codes can be improved by subtracting out the bias before processing. The CW LiDAR system may be mounted to an artificial satellite orbiting the earth, and the relative strength of the return signal for each frequency can be utilized to determine the concentration of selected gases or other substances in the atmosphere.

The invention discloses a satellite posture all-round controlling method based on a magnetic moment device and a flywheel, relating to an all-round posture controlling method for completing a satellite orbit-injection phase by using the magnetic moment device and the flywheel. The invention solves the problems of low reliability and short service life of the traditional satellite posture all-round controlling technology. The satellite posture all-round controlling method comprises the following steps of: 1, setting controller parameters according to the requirement of a control system; 2, measuring a geomagnetic field intensity vector Bb, a satellite angular velocity vector Wb and a solar azimuth, and sending the measured data to a satellite controller; 3, calculating an expected control moment vector Tm and a control magnetic moment vector Mm, and sending the control magnetic moment vector Mm to the magnetic moment device; 4, acquiring an effective solar azimuth vector Alfa; 5, calculating a control input moment vector Tw and sending to the flywheel; and 6, jointly completing the satellite posture all-round control by the magnetic moment device according to the control magnetic moment vector Mm and the flywheel according to the control input moment vector Tw. The invention is suitable for the field of satellite posture control.

A method and system for a mobile station to determine its position (or velocity) and time using a hybrid combination of satellite orbit data. In one aspect, the mobile station combines predicted orbit data from one satellite and real-time orbit data from another satellite in the determination of a fix. The combination can be made to the satellites in the same or different satellite systems. The mobile station can use the real-time orbit data of a satellite at one time period and the predicted orbit data of the same satellite at another time period. In another aspect, the mobile station can use the real-time orbit data to correct the clock bias in the predicted orbit data. The correction to the clock bias can be made to the same satellite that provides the real-time orbit data, or to a different satellite in the same or in another satellite system.

Provided herein are methods and system for enabling a navigation receiver to generate receiver specific satellite orbital models based on relatively small sets of parameters obtained from a server. In an embodiment, a set of parameters for a satellite includes a force parameter (e.g., solar radiation pressure), initial condition parameters (e.g., satellite position and velocity at a time instance) and time correction coefficients, which the receiver uses in a numerical integration to predict the position of the satellite. The set of parameters needed for the integration is small compared to current methods which require transmission of a complete set of ephemeris and other parameters for each satellite. Since the set of parameters is relatively small, it requires less communication resources to transmit compared to current methods. Further, the integration based on the small set of parameters enables the receiver to predict satellite orbits with low computational load.

A method and system of utilizing non-geostationary satellite orbit (NGSO) frequency spectrum in a geostationary satellite orbit (GSO) satellite communication system in a non-interfering manner. The GSO satellite communication system comprises an Earth terminal to transmit signals to a GSO satellite using a GSO frequency spectrum, the Earth terminal further operable to transmit signals to the GSO satellite using an extended frequency spectrum, the extended frequency band including the GSO frequency spectrum and a non-geostationary (NGSO) frequency spectrum; a command center operative to instruct the Earth terminal to transmit signals to the GSO satellite using the GSO frequency spectrum, when an NGSO satellite is expected to be in-line with respect to the Earth terminal and the GSO satellite; and wherein the command center is further operative to instruct the Earth terminal to transmit signals to the GSO satellite using the extended frequency spectrum, when no NGSO satellite is expected to be in-line with respect to the Earth terminal and the GSO satellite.

An electronic device having a reception unit that receives satellite signals from positioning information satellites orbiting the Earth; a time information generating unit that generates time information; a time correction information storage unit that stores time correction information for correcting the time information; a time correction information generating unit that generates the time correction information based on the satellite signals; an environmental information acquisition unit that gets information about the reception unit environment; a reception environment information generating unit that generates reception environment information for the reception unit based on the environment information; and a positioning information satellite selection unit that selects the positioning information satellite from which signals are to be received by the reception unit based on the reception environment information.

A propulsion system for the orbit control of a satellite with terrestrial orbit having an angular momentum accumulation capacity comprises a propulsion unit able to deliver a force along an axis F having a component perpendicular to the orbit, and a motorized mechanism connected on the one hand to the propulsion unit and on the other hand to a structure of the satellite, the motorized mechanism being able to displace the propulsion unit along an axis V parallel to the velocity of the satellite, and able to orient the propulsion unit so as to make it possible to control: a component of the force along the axis V, for orbit control, an amplitude and a direction of couple in a plane perpendicular to the axis F, for control of the angular momentum.

A propulsion system for the orbit control of a satellite in Earth orbit driven at a rate of displacement along an axis V tangential to the orbit comprises two propulsion modules, fixed to the satellite, and facing one another relative to the plane of the orbit, each of the propulsion modules comprising, in succession: a motorized rotation link about an axis parallel to the axis V; an offset arm; and a plate supporting two thrusters, suitable for delivering a thrust on an axis, arranged on the plate on either side of a plane P at right angles to the axis V passing through a centre of mass of the satellite; each of the two thrusters being oriented in such a way that the thrust axes of the two thrusters are parallel to one another and at right angles to the axis V.

The present invention provides an image motion compensation method for a space optical remote sensor, relating to an image motion compensation method and solving the problem that the current image motion velocity vector calculation method used in image motion compensation cannot satisfy complex imaging tasks and the calculation result is not accurate. The process of the image motion compensation method is as follows: creating five coordinate systems starting from ground targets to image points, transferring the coordinates for a plurality of times according to the rotation and translation principles among vectors, describing the positions of the targets and the image points in the camera coordinate systems, obtaining the image motion velocity vector calculation formula and the calculation method when the satellite forms images of the targets, then obtaining the image motion velocity vector used in the image motion compensation of the space optical remote sensor. The image motion compensation method overcomes the deficiency in the prior art, dependently calculates the target positions needed in the image motion velocity vector calculation and integrally considers the orbit and attitude parameters, besides. The image motion compensation method is suitable for complex imaging tasks and general satellite orbit, and is used in the fields such as atmospheric environment monitoring, resources exploration, disaster prevention and the like.

The invention provides an optimization design method of a low-orbit communication and navigation enhancement mixed constellation. The method comprises the following steps: determining a satellite orbit type; determining a satellite orbit height; determining a minimum observation elevation angle; selecting constellation configuration; determining an orbit inclination angle; determining a satellite quantity; determining an orbit surface quantity and a phase factor; selecting initial ascending node right ascension in an optimized mode; analyzing coverage performance of the low-orbit communication and navigation enhancement mixed constellation; and after traversing ends, comparing all mixed constellation parameters satisfying design requirements, and selecting an optimal solution. The method has the following advantages: through combination of factors needing to be considered for design of a communication and navigation enhancement constellation at each phase, the designed low-orbit communication and navigation enhancement mixed constellation can satisfy user demands, is excellent in constellation performance, is small in satellite quantity and quite good in compatible mutual operation capability between constellations.

The invention discloses a method for determining the satellite differentia pseudo-range deviation based on single-frequency navigation satellite data, and relates to a satellite differential pseudo-range deviation determination and correction technology in satellite navigation applications. The method comprises the steps of A, acquiring single-frequency GNSS original observation data and obtaining precision satellite orbit and clock error products; B, building single-frequency GNSS non-combination pseudo-range and phase observation equations; C, building a single-frequency non-combination precision single-point positioning function model; D, solving single-frequency non-combination precision single-point positioning Kalman filtering; and E, performing ionospheric delay modeling and determining the navigation satellite differential pseudo-range deviation. Determination for navigation satellite differential pseudo-range deviation parameters is realized by using a single-frequency receiver, and the hardware cost of an existing navigation satellite differential pseudo-range deviation estimation method can be reduced by more than 90%. Meanwhile, the method is reasonable and simple in design and improves the efficiency. The design is not only low in cost, but also high in efficiency.

The invention discloses a multi-satellite cooperative observation business scheduling method and relates to satellite observation business planning and scheduling technology in a satellite operation control field. The multi-satellite cooperative observation business scheduling method is based on a satellite operation control system, builds a star land resource management model, a satellite orbit calculation model and a satellite access information calculation model, adopts a satellite observation business dynamic planning algorithm to regulate satellite observation business rapidly and dynamically, adopts an automatic processing mechanism to make a satellite load control plan and a data receiving plan immediately, adopts a satellite actual load control instruction compilation business trigger mechanism to compile satellite actual load control instructions in real time, and schedules an electronic signal detection satellite and an imaging observation satellite to complete cooperative observation business. The multi-satellite cooperative observation business scheduling method has the advantages of being rapid in response speed, accurate in calculation method, high in automation and the like and is particularly suitable for a marine moving target multi-satellite cooperative observation field.

The invention discloses a data quality monitoring method for a local enhancing system, which mainly solves the problem that the satellite orbit position calculation accuracy by the traditional data quality monitoring method is relatively low. The method comprises the following steps of: firstly, checking the data integrity and validity of a received broadcast ephemeris to acquire a group of accurate and valid ephemeris data; secondly, checking the consistency of the group of ephemeris data; thirdly, carrying out real-time precision ephemeris detection, new and old ephemeris detection and ephemeris-almanac detection on the broadcast ephemeris data with uniformity respectively; and finally, according to the data availability detection result, generating an available matrix and an available broadcast ephemeris group of the broadcast ephemeris. The method has the advantages of high satellite orbit position calculation accuracy and low ephemeris fault error detection probability and can effectively solve the problem of man-made interference on the broadcast ephemeris and almanac of a satellite navigation system.

The invention discloses a method for realizing multi-satellite combined imaging. The method for realizing multi-satellite combined imaging includes the steps that an orbit rendezvous of transiting satellites in a given time quantum is obtained, the orbit rendezvous of the transiting satellites is solved in an optimization method to obtain a relatively optimum imaging scheme, and the imaging scheme is optimized to determine which satellite is adopted and what work mode is adopted by the satellite for imaging in a certain given time quantum. The method for realizing multi-satellite combined imaging combines the satellite orbit computing technology and the artificial intelligence technology, and includes the steps of rapid obtaining of the orbits of the transiting satellites, automatic selection of multi-target optimization algorithms, automatic optimization of an imaging coverage scheme, and the like. The method has the advantages of being high in degree of automation, efficient in algorithm and the like, and can be used for building a unified district observation platform for multi-satellite combined imaging. By means of the method for realizing multi-satellite combined imaging, a user can determine the optimum satellite resource from numerous satellite resources, and the cycle of obtaining satellite remote sensing data for the user is made to be as short as possible.

The invention discloses an area enhanced precision positioning service method suitable for large-scale users. According to the technical scheme, the method includes the steps that after the users effectively fix wide-lane ambiguity and L1 ambiguity of at least four satellites in a zero difference network RTK processing mode, area enhanced information of surrounding base stations does not need to be acquired, at this moment ambiguity fixed results and zenith troposphere delay residual errors acquired by interpolation are used as known truth values, received satellite UPD information is combined, and an ambiguity fixed solution in a PP-RTK mode can be immediately acquired without initialization. Due to the fact that satellite UPD, real-time satellite orbits and real-time satellite clock errors are only related to the satellites, and short-term forecast lasting tens of seconds to a few minutes can be conducted, the information can be broadcasted to the users through the communication satellites in a broadcast mode, and then real-time data communication burdens among the users and the base stations can be greatly reduced. Once user ambiguity is firstly fixed, the number of the users simultaneously serviced by an area enhanced system is no longer restricted at this moment.

The invention discloses a space-based phased-array radar space multi-target orbit determination method, which mainly solves the problems that the space weak target cannot be evaluated effectively and the target orbit determination precision is low in the prior art. The method comprises the following steps of: processing target echo data by a zero-setting conformal algorithm, acquiring distance prior information by utilizing a distance pulse compression principle, and segmentally processing echo signals according to the distance prior information; segmenting the echo signals according to the number of the targets, wherein each segment of data is a target signal and an adjacent unit signal; performing multi-target two-dimensional angle evaluation on each segment of data by utilizing a sum-difference multi-beam angle-measuring principle; performing coordinate conversion based on a space target tracking result and detection satellite orbit information; and performing orbit determination on different space targets by a Laplace type iterative algorithm, and improving the orbit determination precision by a least square algorithm. According to the method, the influence of strong signals on weak targets can be reduced and the parameters of the weak targets can be evaluated accurately. The method can be applied in the actual application fields of space situation awareness, orbit resource management and the like.