66 results about "Synchronous orbit" patented technology

The invention provides a solar synchronous orbit quick response SAR satellite load platform integrated configuration, which comprises a satellite body, an SAR antenna, a solar array, a phased array data transmission antenna, a star sensor and a body-mounted solar cell, the satellite body is in a quadrangular prism shape, the cross section of the satellite body is an isosceles trapezoid, the satellite body comprises a group of opposite parallel surfaces and a group of opposite inclined surfaces, the phased array data transmission antenna and the star sensor are respectively arranged on two parallel surfaces, and the SAR antenna and the solar array are respectively arranged on two inclined surfaces; the body-mounted solar cell piece and the solar array are installed on the same inclined plane and located on the inner side of the solar array, and the solar array comprises two solar array plates and has an unfolded state and a folded state. According to the method, load platform integration is taken as a design thought, so that the AIT process of the SAR satellite and the time required by AIT are greatly shortened; meanwhile, the attitude requirements of energy and load work are met, and the reliability of the initial injection stage is improved through sufficient energy.

The invention relates to a generalized carrier rocket trajectory calculation method which comprises the steps that a target orbit and constraint conditions corresponding to the target orbit are set, the target orbit comprises a sun-synchronous orbit or a low-dip-angle orbit, and the constraint conditions at least comprise the geocentric vector diameter, the absolute speed and the flight path angle; input parameters are simplified, wherein the input parameters comprise configuration parameters, mass parameters, pneumatic parameters and engine parameters; and based on the constraint condition of the target orbit, the corresponding control variable and the input parameter, calculating the value of the control variable through a Newton iteration method so as to obtain the trajectory of the carrier rocket. The invention provides a universal carrier rocket trajectory calculation method. The carrying capacity of a carrier rocket is ensured by optimizing a typical target orbit; according to the method, input parameters of trajectory calculation are simplified and carded, the trajectory is obtained through calculation of the Newton iteration method, the adaptability to different configuration schemes is improved on the premise that the calculation accuracy is guaranteed, rapid trajectory iteration calculation can be conducted, and generalization is achieved.

The invention provides an intelligent quality control and inversion method for electric power meteorological multi-source data, and relates to the field of data processing. In the method, a multi-view polarized brightness temperature vector structure is constructed by using original brightness temperature observation data acquired by a plurality of satellite-borne microwave radiometers in a near-synchronous orbit intersection area, and a multi-dimensional radiation transmission equation set driven by an earth ellipsoid path integral model is input to generate a brightness temperature prediction result; an inversion optimization model is constructed based on view angle invariant residual constraint, initialization is carried out based on historical data and ground data, and variational inversion solving is carried out to obtain a joint inversion result; and evaluating the credibility through a profile quality vector, and finally supporting stability early warning and load correction in electric power meteorology. By implementing the technical scheme provided by the invention, the quality control and inversion precision of the power meteorological multi-source data profile can be improved.

The invention relates to the technical field of satellite constellation design, and particularly discloses a hybrid multilayer constellation design method for orbit precession synchronization and regression. S01, obtaining an orbit precession rate according to the orbit height and the orbit inclination angle, and constructing an orbit precession synchronous mixed multilayer constellation according to the orbit precession rate; s02, obtaining a change curve and a regression coefficient curve of the track height and the track inclination angle according to the regression track, and determining the track height and the track inclination angle according to the regression coefficient; s03, determining each layer of sub-constellation according to the change curve of the orbit height and the orbit inclination angle and the orbit precession rate, and obtaining a mixed multi-layer constellation with synchronous orbit precession and regression; and step S04, constructing a multi-objective optimization model, determining an optimization objective and a constraint condition, and optimizing the mixed multilayer constellation with orbit precession synchronization and regression.

The invention provides a synchronous orbit belt target searching method and a synchronous orbit belt target searching device. The searching method comprises the steps that a set searching area is divided into a searching hour angle-declination grid, the searching hour angle-declination grid comprises a plurality of hour angle strips, and each hour angle strip comprises a plurality of declination grid blocks; by taking the synchronous orbit belt target envelope curve and the synchronous orbit belt target dense distribution area as a reference, correcting the positions of the hour angle strips, so that each corrected hour angle strip is positioned in the synchronous orbit belt target envelope curve and covers the synchronous orbit belt target dense distribution area; and performing optical visibility judgment on each declination grid block on each corrected hour angle strip, and performing synchronous orbit band target search on the declination grid blocks by using a telescope under the condition that the declination grid blocks meet optical visible conditions. The method can be effectively applied to search observation of an optical telescope on a synchronous orbit belt target, and the target search efficiency and the data quality are effectively improved.

A method of sun-synchronous orbit design for remote sensing satellite based on revisit characteristics is proposed. The relationship between revisit and ground synchronization is established by Q value. The mathematical model of Q is established by node revisit sequence in a certain interval. Then the coverage rate is obtained by the mixed node access sequence and coverage area of orbit altitude and observation angle. Finally, the coverage rate of remote sensing satellite in sun-synchronous orbit is demonstrated from three aspects of time-varying coverage rate, minimum coverage time and minimum observation angle, which provides a reference for the design of sun-synchronous orbit of remote sensing satellite.

The invention provides a non-sun-synchronous orbit satellite energy optimal attitude sailboard control method and system. The method comprises the steps that S1, the illumination angle of each orbit in the satellite life period is calculated according to collected orbit parameters; s2, calculating the illumination area half angle and the illumination duration under the illumination angle of each track; s3, calculating the illumination energy of each track of the sailboard driving shaft under the combination of different swinging positions and different flight attitudes of the satellite; s4, comparing illumination energy of each track, and preferably selecting a combination of a posture with the maximum energy in each period and a sailboard driving position; and S5, obtaining a control strategy for the attitude of all orbital circles of satellites and the position of a sailboard driving shaft in the whole life period of the satellites. By comparing various feasible in-orbit attitude and sailboard position combinations, a sailboard position and attitude control method with optimal energy can be obtained through optimization, the in-orbit receiving energy of a two-dimensional driving solar sailboard satellite is improved, the required sailboard area is reduced under the same power consumption requirement, and the weight of the whole satellite is reduced.

The invention discloses a geosynchronous orbit sparse bunching SAR imaging mode realization method. The method comprises the following steps: constructing a geosynchronous orbit bunching SAR system wave position selection schematic diagram; designing a geosynchronous orbit sparse bunching SAR imaging mode wave position, and calculating mode parameters; calculating a yaw angle required by geosynchronous orbit SAR satellite zero Doppler attitude guidance; constructing a geosynchronous orbit sparse spotlight SAR imaging mode array antenna pattern model; and carrying out geosynchronous orbit sparse bunching SAR imaging mode performance analysis. According to the method, sparse microwave imaging and a geosynchronous orbit bunching SAR mode are combined, on the basis of an original SAR system, proper wave position design is carried out according to a more accurate zebra map to obtain a larger surveying and mapping bandwidth, the purpose of geosynchronous orbit bunching SAR high-resolution wide-width observation is achieved, and the method is suitable for large-scale popularization and application. And meanwhile, the system performance is improved in the aspects of reducing range ambiguity, inhibiting the influence of antenna rotation on azimuth ambiguity and the like.

The application discloses a high-throughput satellite access method and system based on 5G NR. The method is as follows: a beacon signal and a random access channel are arranged on a global signaling beam of a high-throughput satellite; a satellite terminal requests a service beam service of the high-throughput satellite through the random access channel; all satellite terminals share the random access channel, and resource competition is realized through a random backoff competition mechanism; the satellite terminal adjusts an antenna pointing direction and reports user position information by using the global signaling beam; a satellite system adjusts a variable service beam pointing direction according to the user position information, and provides access service for the user; the satellite system provides a 5G broadcast signal for the user through the service beam, and completes broadcast reception and random access of the 5G satellite system. The system realizes the high-throughput satellite access method based on 5G NR. The application realizes satellite terminal access based on 5G standards without affecting an existing synchronous orbit high-throughput satellite architecture.

The invention discloses a transmission control method in a satellite communication system and a related device. The terminal can determine a target satellite with the strongest signal from at least one synchronous orbit satellite through satellite selection. The terminal can determine the satellite transmission link direction based on the terminal position information and the target satellite position information. The terminal can also determine the radiation direction of the satellite antenna in the terminal based on the terrestrial magnetism data, attitude data and the like of the terminal. Then, the terminal can enable the radiation direction of the satellite antenna of the terminal to be aligned with the target satellite through the satellite transmission link direction and the radiation direction of the satellite antenna. The terminal can send the first data packet to the target satellite along the radiation direction of the satellite antenna after being aligned with the target satellite. Thus, a user can align the radiation direction of the satellite antenna of the terminal to the target satellite without depending on an external device, the communication performance between the terminal and the target satellite is enhanced, and satellite selection and satellite alignment operations of the user are simplified.

The present invention discloses a method and system for transmitting in a combined geosynchronous orbit and low-orbit double-layer satellite network. The method includes the following steps: S1, a geosynchronous orbit (GEO) satellite transmits signals to low-earth orbit (LEO) satellites and cellular users; S2, the LEO satellites and cellular users receive the signals transmitted by the GEO satellite; S3, the LEO satellites use the decode-and-forward relay protocol and adaptive non-orthogonal multiple access (NOMA) to send signals to the cellular users; S4, the cellular users receive the signals relayed by the LEO satellites and combine the signals from the GEO satellite and the LEO satellite using the maximum ratio combining method. The power allocation factor of the adaptive non-orthogonal multiple access technology proposed by the present invention is dynamically adjusted according to the channel state, satellite elevation angle, and co-channel interference, and can achieve differential power allocation for different users' dynamic channels, improving the spectrum utilization rate and power allocation fairness.

The invention discloses a synchronous orbit electric propulsion satellite short-range game control method based on differential game, which comprises the following steps: under an LVLH coordinate system, establishing a near-circular orbit relative motion dynamic model of spacecrafts of both pursuit and escape parties, and further determining a state space form in a spacecraft pursuit and escape game process; based on a state space form in a spacecraft pursuit game process, introducing a Hamiltonian function, and constructing a short-distance pursuit game model with optimal time; introducing a co-state equation, and describing a short-range pursuit game process as a two-point boundary value problem; and converting the problem into a parameter optimization problem, and carrying out optimization solution on the problem by utilizing an improved difference method so as to realize short-range game control.

A method for planning a drift-and-survey mission for a geostationary orbit space target monitoring and imaging satellite is disclosed. The initial time and corresponding initial position of the observation satellite's roving mission are determined based on requirements, as well as the approach observation time and corresponding approach observation position. At the first maneuver time, the observation satellite moves to the first maneuver position, and a first velocity increment is applied to the initial velocity vector at this point, causing the observation satellite to maneuver tangentially along the orbit to obtain the velocity vector after the first maneuver. At the second maneuver time, the observation satellite moves to the second maneuver position, and a second velocity increment is applied to the initial velocity vector at this point, causing the observation satellite to maneuver tangentially along the orbit to obtain the velocity vector after the second maneuver. At the approach observation time, the observation satellite is at the approach observation position and observes the target satellite under front lighting conditions using the observation vector. This invention can improve roving efficiency and flexibility, realize drift-and-survey observation of targets on different surfaces, save propellant, and improve satellite performance.

The invention provides a communication method, a communication device and a communication system, which are applied to the field of communication. The present application is applicable to a communication system comprising a UE and a satellite, the satellite being a synchronous orbit satellite. The communication method comprises the following steps: UE calculates a TA change value by combining own position information, wherein the TA change value comprises a TA added value and a TA reduced value; and the TA change value is reported while the TA is reported to the satellite, so that the satellite / base station can determine the potential conflict area based on the TA change value, and the potential conflict area can be determined by the satellite / base station when the satellite / base station configures transmission resources (including uplink transmission and downlink transmission) or schedules data (such as preferentially transmitting high-priority data). Therefore, the purpose of avoiding the conflict between uplink transmission and downlink transmission is achieved, and the influence caused by the conflict area is reduced to the minimum extent.

The present invention relates to a geosynchronous orbit SAR satellite phase consistency correction and compensation system and method, and in particular to the implementation of geosynchronous orbit SAR satellite phase consistency correction and compensation, and can also be applied to other spacecraft using the method, belonging to the field of SAR imaging technology. The present invention performs phase compensation on the transmitting channel on the +Y deck and the transmitting channel on the -Y deck, and at the same time performs phase compensation on the receiving channel on the +Y deck and the receiving channel on the -Y deck. When imaging is performed under this condition, the degree of deterioration of the imaging sensitivity index is reduced; the present invention performs phase compensation on the transmitting channel on the +Y deck and the transmitting channel on the -Y deck, and at the same time performs phase compensation on the receiving channel on the +Y deck and the receiving channel on the -Y deck. When imaging is performed under this condition, the degree of deterioration of the imaging fuzziness is reduced, which greatly improves the image quality.

The application discloses a time-difference-based synchronous orbit satellite fast maneuvering detection method, and aims at the problem of maneuvering detection of synchronous orbit satellites under a radio monitoring system. The difference between the time-difference measurement value of satellite signals arriving at two receiving stations and the theoretical value calculated by a predicted ephemeris can be approximately a linear function of satellite position error. The difference between two different time points is used as a test statistic to detect whether the satellite has maneuvered. The application greatly reduces the number of estimated parameters and the demand for observation arc length, and only needs two receiving stations to observe a short arc segment for several minutes to realize fast maneuvering detection of the synchronous orbit satellite, thereby reducing the system complexity and improving the timeliness of the system.

The invention discloses a synchronous orbit satellite rapid maneuvering detection method based on time difference, and aims to solve the problem of maneuvering detection of synchronous orbit satellites under a radio monitoring system. According to the property that the difference residual between a time difference measurement value of a satellite signal arriving at two receiving stations and a theoretical value of forecast ephemeris calculation can be approximate to a linear function of a satellite position error, the difference residual between two different moments is used as a test statistic to detect whether a satellite is maneuvered or not. According to the method, the number of the parameters to be estimated and the requirement for the observation arc length are greatly reduced, rapid maneuvering detection of the synchronous orbit satellite can be achieved only through several minutes of short arc section observation of the two receiving stations, and the timeliness of the system is improved while the complexity of the system is reduced.

The invention provides a novel ionosphere modeling technology based on a continuity equation and Beidou synchronous orbit satellite constraint, and relates to the technical field of ionosphere monitoring. Comprising the following steps: step 1, an ionosphere modeling method based on a continuity equation, step 2, constructing constraint conditions by using Beidou synchronous orbit satellite observation data, and step 3, establishing a high-precision ionosphere TEC model based on the constraint conditions so as to solve the problem of insufficient precision of an existing ionosphere function model. The ionosphere continuity equation reflects two physical processes of a photochemical reaction and a transportation process in the ionosphere, the physical law of ionosphere activity can be effectively considered by introducing the ionosphere continuity equation into the ionosphere model, meanwhile, continuous monitoring data of Beidou synchronous orbit satellite data on TEC at a part of IPP is introduced, a synchronous orbit satellite IPP point serves as a stable point, and the stability of the ionosphere is improved. Constraint conditions of the ionosphere model are established, and the accuracy of ionosphere TEC inversion and the sensitivity of ionosphere disturbance detection are improved.

The invention provides an inter-station satellite bidirectional time forecasting method, and belongs to the technical field of time calibration and forecasting. According to the method, a synchronous orbit GEO satellite is used as a forwarding node of a space segment, two stations respectively carry out BPSK modulation on local time mark signals to form frequency signals, and the frequency signals are transmitted to an opposite end through power amplification. In the data processing process, an inter-station time comparison result is calculated according to an existing model, then modeling and learning training are carried out on measured data by using an LSTM model, and finally a predicted inter-station time comparison sequence is output to be used for correcting inter-station time deviation of the next period and forecast of various clock differences.

The present invention provides an imaging method, device and electronic equipment for suppressing moving targets by a geosynchronous orbit synthetic aperture radar, which are applied to the fields of synthetic aperture radar signal processing and artificial intelligence technology. The method comprises: receiving echo data sent by a synthetic aperture radar; performing aperture segmentation on the echo data to obtain a plurality of sub-aperture data; performing the following operations on each sub-aperture data: performing range compression and back-projection on the sub-aperture data to obtain an imaging result of the sub-aperture data; determining phase information and amplitude information of the sub-aperture data based on the imaging result; determining a background image of the sub-aperture data based on the amplitude information; combining the phase information and the background image to obtain complex-valued data of the sub-aperture data; and coherently fusing the complex-valued data of a plurality of sub-aperture data to obtain a target image.

The invention provides a synchronous orbit SAR moving ship detection imaging method, device and equipment and a medium, relates to the technical field of satellite detection imaging, and is applied to a geosynchronous orbit synthetic aperture radar carried on a satellite platform. The method comprises the following steps: dividing a full-aperture echo signal into a plurality of sub-aperture echo signals of optimal sub-apertures along azimuth time; sequentially carrying out distance compression and platform motion compensation based on a scene center reference signal on each sub-aperture echo signal, and eliminating linear distance migration caused by a tangential component of a ship translation speed in the sub-aperture echo signals; focusing the sub-aperture echo signal after eliminating the linear range migration through phase compensation and azimuth coherent accumulation to obtain a focused image of the moving ship target; and processing the focused image by adopting a constant false alarm detection algorithm, and outputting a final detection result of the moving ship target.

The application discloses an autonomous program control system level test method, and proposes a solution method for the correctness, effectiveness, safety and integrity of satellite active stage operation period satellite-rocket separation program control, autonomous flight program control, synchronous orbit stage operation period machine cutting program control, and emergency program control task verification. Based on satellite 1553B bus data simulation function and automatic test, satellite program control execution process is simulated and forwarded, satellite autonomous instruction sequence during program control execution is analyzed or intercepted, satellite program control process safety risk hidden danger is guaranteed, and effective verification of satellite autonomous program control function and comprehensive interpretation of instruction telemetry are realized.

The present invention provides a satellite system and method for collaborative detection and imaging of low-orbit targets from a low-orbit orbit. The satellite system includes three sun-synchronous orbit reconnaissance satellites with orbital altitudes of 600km, 800km, and 1000km. The satellite carries a camera payload with optical imaging and detection capabilities. The satellite has three working modes: flyby imaging, fly-by imaging, and joint detection and positioning mode. The advantage is that it can perform real-time multi-angle detection of satellites within the orbital altitude range of 500 to 1100km, provide high-precision positioning and orbit determination of targets; and perform high-frequency flyby imaging, and the minimum imaging distance is short (less than or equal to 100km), the imaging effect is good, and it has multiple observation angles. It can quickly form a fly-by imaging configuration for sun-synchronous orbit satellites within the orbital altitude range of 500 to 1100km, and perform fly-by imaging of targets.

The invention discloses an orbit layout method for a global illumination lunar device, which is used for solving the problem that the lunar device cannot continuously obtain sun illumination when executing a task for a long time, and is directly related to stable energy supply and heat balance of a spacecraft. According to the method, a planar and three-dimensional long-distance retrograde orbit family is generated through a continuation and bifurcation method of an earth-moon space periodic orbit, the illumination condition of the orbit is obtained by utilizing a planetary shadow model, and a super sun-synchronous orbit is used as a lunar device orbit layout scheme. The relation among the sun, the lunar device, the moon and the earth is further analyzed, the illumination condition and shadow distribution are evaluated, and a reasonable orbit selection basis is provided. Besides, an attitude pointing scheme of the lunar device and a rotation control rule of the solar array are provided, so that the solar energy acquisition efficiency is improved, and sufficient sun illumination supply in a task is ensured.

The application discloses a geosynchronous orbit SAR sea surface wave imaging quality evaluation method and belongs to the technical field of geosynchronous orbit space correlation SAR sea surface wave imaging quality evaluation. The application obtains a sea surface wave echo signal, performs distance direction matching filtering and space correlation processing on the sea surface wave echo signal, generates an imaging result by using a back projection algorithm, calculates image intensity and a sea wave spectrum main energy direction slope, and finally quantifies imaging quality by using a space correlation evaluation factor. The evaluation factor can effectively represent the space coherence of sea surface wave imaging, and the larger the value is, the better the imaging quality is. The application solves the problem of insufficient applicability of existing evaluation methods in sea surface wave imaging due to low contrast and weak texture features, significantly improves the accuracy of geosynchronous orbit SAR sea surface wave imaging quality evaluation, and provides reliable technical support for marine environment monitoring.

The invention provides an illumination constraint-based sun-synchronous orbit satellite imaging probability analysis method, which comprises the following steps of: determining an orbit height and a latitude argument under a set time interval in an orbit period of a satellite; determining the geographic latitude, the latitude argument and the orbit height of the sub-satellite point of the satellite at each position of the orbit descending section; determining a geocentric field angle of the satellite at each position pointing edge projection point and a sub-satellite point in the orbit descending section; determining whether the to-be-analyzed latitude with the visible light imaging condition points to the position of the edge projection point or not in the orbit descending section of the satellite; determining the local time of the boundary line position after the solar altitude constraint is considered; comparing whether the latitude of the to-be-analyzed satellite with the visible light imaging condition points to the position of the edge projection point in the orbit descending section, and considering the local position of the boundary line position after solar altitude constraint, judging whether the visible light imaging condition is met, traversing the time of one year and the related latitude, and carrying out statistics to obtain the visible light imaging probability of the satellite.

The application provides a satellite configuration and switching method of a multi-band planar phased array antenna, which comprises a satellite platform 1, a flat panel antenna group and a solar cell array 5, the flat panel antenna group comprises multiple flat panel antennas of different frequency bands and is connected to the top plate of the satellite platform 1, the solar cell array 5 is connected to the bottom plate of the satellite platform 1, when in a launching state, the multiple flat panel antennas of different frequency bands are all folded and close to the first side surface, and the solar cell array 5 is folded and close to the second side surface; when in a flying state, the multiple flat panel antennas of different frequency bands are all unfolded until the multiple flat panel antennas of different frequency bands and the top plate of the satellite platform 1 are located in the same plane, and the solar cell array 5 is unfolded until the solar cell array 5 and the bottom plate of the satellite platform 1 are located in the same plane. The satellite configuration has stable structure and can bear large-size and large-mass load, and has high adaptability to satellites with flat panel type effective load in the current sun-synchronous orbit and low-inclination orbit.

The invention provides a sun-synchronous orbit inclination angle adjusting method and device, and the method comprises the steps: determining a position relation between an initial orbit and a target orbit, enabling two intersection points of the initial orbit and the target orbit to be located above an equator, and taking one of the intersection points as a satellite orbit transfer point; determining an orbital transfer angle required for adjusting the satellite from the initial orbital plane to the target orbital plane; according to the system state of the satellite and the task target, the single ignition duration of the satellite and the ignition moment and shutdown moment of the satellite are comprehensively determined; determining a satellite ignition direction; the speed increment of satellite monopulse ignition is analyzed and calculated, and the total impulse required for changing the inclination angle of the satellite orbit is determined according to the speed increment; the total satellite ignition orbit number is analyzed and calculated according to the total impulse and the actual impulse generated by each time of ignition; and based on the satellite orbital transfer point, the satellite ignition direction, the satellite ignition time and the shutdown time, the satellite is controlled to carry out secondary ignition orbital transfer, and then inclination angle adjustment is completed.

The geosynchronous orbit debris inclination vector evolution calculation method disclosed by the application comprises the following steps: firstly, calculating the influence of the J2 term of the earth's non-spherical perturbation on the change rate of the inclination debris, calculating the angular frequency of the geosynchronous orbit debris inclination vector, the period of the precession and the angular rate of the precession under the influence of the J2 term; then, calculating the frequency of the geosynchronous orbit debris inclination vector precession, the period of the precession and the angular rate of the precession caused by the sun's gravity and the moon's gravity respectively; finally, synthesizing and calculating the different angular frequencies, the periods of the inverse precession and the angular rates of the precession. The geosynchronous orbit debris inclination vector evolution calculation method disclosed by the application separately calculates the effects of the J2 term of the earth and the sun and the moon, and compared with the traditional geosynchronous orbit debris inclination vector evolution calculation method which adopts complete numerical calculation, the method has the advantages of fast calculation speed and can be used for the analysis and calculation of the long-term evolution of the geosynchronous orbit debris orbit.

The application discloses a positioning method and system based on Beidou PPP-B2b, and comprises the following steps: acquiring PPP-B2b orbit correction numbers broadcast by Beidou No.3 system geosynchronous orbit satellites; establishing a first full-network state space error estimation model of corresponding estimated parameters of satellite clock errors of multiple satellites, multiple satellites and multiple reference station servers according to the PPP-B2b orbit correction numbers; introducing reference constraints to the first full-network state space error estimation model, and redefining parameters to solve the satellite clock errors and the corresponding estimated parameters, so that positioning is performed according to the solved satellite clock errors. The application can quickly solve the satellite clock errors, improve the precision and reliability of the satellite clock errors, and realize wide-area real-time precise positioning.