22 results about "Synchronous orbit" patented technology

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 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.

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 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 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 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 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.

An autonomous mission planning method for ultra-low sun-synchronous orbit optical remote sensing satellites includes the following steps: extrapolating the satellite orbit considering atmospheric drag and thrust effects; planning orbit maintenance arcs according to an autonomous orbit maintenance strategy; planning imaging and data transmission arcs respectively according to imaging and data transmission mission requirements; eliminating overlapping orbit maintenance, imaging, and data transmission arcs based on priority; estimating whether the planned arcs meet the energy requirements; if not, eliminating the planned arcs; updating the surface-to-mass ratio based on the planned arcs, and replanning using the updated surface-to-mass ratio until the planned arcs remain unchanged compared to the previous one; completing the autonomous mission planning for the next few orbits. This invention uses electric propulsion for autonomous orbit maintenance as a key constraint in mission planning, prioritizing satellite energy for orbit maintenance, and on this basis, maximizing the performance of imaging and data transmission missions.

The invention discloses a co-orbit satellite system and 5GNR system coexistence interference simulation method and device, and is used for solving the problems of complex simulation system and low simulation efficiency in the prior art, and the method comprises the steps: S11, constructing an interference evaluation scene; s12, configuring related parameters of a synchronous orbit satellite system, a 5GNR system, a 5GNR user terminal, a satellite user terminal and the like according to the interference scene; s13, distributing 5GNR base stations in the coverage area of the satellite network according to the configuration parameters; s14, distributing satellite network users and 5GNR user terminals, and establishing association between the users and the base station; and S15, calculating signal to interference plus noise ratios of the single system and the heterogeneous system, and performing interference assessment by adopting a throughput loss method. According to the method, the complexity of evaluation between large-scale heterogeneous systems can be reduced, the evaluation process between the large-scale heterogeneous systems is simplified, the simulation efficiency is high, and the practicability is high.

This invention provides a method and apparatus for adjusting the inclination of a sun-synchronous orbit. The method includes: determining the positional relationship between an initial orbit and a target orbit, such that the two intersection points of the initial orbit and the target orbit are located above the equator, and using one of the intersection points as the satellite's orbit change point; determining the orbit change angle required for the satellite to adjust from the initial orbital plane to the target orbital plane; comprehensively determining the satellite's single ignition duration, ignition time, and shutdown time based on the satellite's system status and mission objectives; determining the satellite's ignition direction; analytically calculating the velocity increment of the satellite's single pulse ignition, and determining the total impulse required to change the satellite's orbit inclination based on the velocity increment; analytically calculating the total number of satellite ignitions based on the total impulse and the actual impulse generated by each ignition; and controlling the satellite to perform a single ignition orbit change to complete the inclination adjustment based on the satellite's orbit change point, ignition direction, ignition time, and shutdown time.

The invention discloses a remote drifting game control method for synchronous orbit electric propulsion satellites. The method comprises the steps that the synchronous orbit electric propulsion satellites are divided into cooperative targets and non-cooperative targets; carrying out remote floating approaching control on the cooperative target by adopting a transverse thrust control method; for a non-cooperative target, establishing an absolute dynamic model considering J2 perturbation, constructing a time-optimal pursuit game saddle point strategy problem of introducing a Hamilton function based on the absolute dynamic model, and converting the time-optimal pursuit game saddle point strategy problem into a two-point boundary value problem; and converting a two-point boundary value problem into an unconstrained parameter optimization problem, performing global search and local optimization solution on the unconstrained parameter optimization problem, and performing remote drifting game control on the non-cooperative target according to an optimal solution. According to the invention, the low-cost floating game control of the geosynchronous orbit electric propulsion satellite is realized by designing a game control strategy with high success rate approaching.

The application provides a geosynchronous orbit high-energy electron flux prediction method, a model and a model construction method, and relates to the field of electron flux prediction; the geosynchronous orbit high-energy electron flux prediction method comprises the following steps: constructing a geosynchronous orbit high-energy electron flux prediction model; inputting the following parameters into the geosynchronous orbit high-energy electron flux prediction model: a time point T, spatial coordinates of a spatial point in a radiation belt, and average solar wind speed in a time range of [T-a hours, T-b hours]; calculating high-energy electron flux at the geosynchronous orbit height passing through the spatial point in a quiet period; judging whether the spatial point at the geosynchronous orbit height is in a storm time or not, and outputting high-energy electron flux at the geosynchronous orbit height passing through the spatial point in the quiet period or the storm time. The high-energy electron flux prediction method provided by the application can automatically switch the flux prediction mode in the quiet period or the storm time, and significantly improves the prediction accuracy under different geomagnetic activity conditions.

The invention relates to the technical field of satellite orbits, in particular to a sun-synchronous orbit dip angle offset calculation method and device, equipment and a medium. According to the method, an orbit perturbation equation containing earth non-spherical gravity and atmospheric damping perturbation is constructed, and the influence of semi-major axis attenuation caused by atmospheric resistance on the inclination angle offset is considered. According to the method, the influence of atmospheric damping on the orbit height and different orbit height maintaining strategies are comprehensively considered, more accurate orbit injection parameters are calculated in combination with the prior art, and a more reliable guarantee is provided for subsequent on-orbit normal operation of a spacecraft. In the initial stage of orbit design, more accurate spacecraft orbit injection parameters can be calculated by introducing more perturbation models. The orbit height maintaining strategy is also considered, which means that the later-stage spacecraft in-orbit operation and maintenance cost is also considered, the engineering implementation is more reliable, the result is more accurate, and meanwhile, flexible adjustment can be realized by fully combining actual conditions.

This invention provides a space-based monitoring platform for space debris detection and its optimized control method, comprising: employing a sun-synchronous orbit satellite platform, configuring optical detection sensors on the satellite platform, and integrating the satellite platform and optical sensors into a unified design. The satellite platform uses a geocentric-sunset plane reference coordinate system for closed-loop attitude control, ensuring that the satellite platform's body coordinate system O is stable during flight. b X b Y b Z b Down, +Z b While pointing towards the Earth's center, ±X b The orientation is always perpendicular to sunlight, ensuring that the optical detection sensor is in a forward-facing position for target observation, enabling natural rendezvous and observation with space debris during operation. This proposed method is reasonable and simple to implement. Compared to traditional three-axis stabilized Earth-oriented attitude control methods, it can set and fix the optimal lighting conditions for space debris detection, resulting in high mission efficiency.

The present application discloses a geosynchronous orbit system preliminary search spatial decoupling method, relating to the field of satellite communication, comprising the following steps executed in sequence: step one, analyzing the spatial selectivity of the receive beamforming output, and decoupling at least one one-dimensional off-diagonal search space from the joint / complete three-dimensional search space; step two, based on the peak position guess from the off-diagonal search space, establishing and forming the corresponding two-dimensional reduced dimension search space, and performing the first peak position detection in the reduced dimension search space; step three, based on the detection result of the first peak position detection, performing the second peak position detection in the off-diagonal search space; and step four, integrating the peak position detection results of the off-diagonal search space and the reduced dimension search space, and reconstructing the final peak position.

The invention provides an Internet of Things terminal multi-access communication method, system and device of a generic synchronous orbit constellation and a storage medium, relates to the technical field of satellite communication, and aims to realize low-cost, efficient and reliable communication of mass terminals of the satellite Internet of Things. The method comprises the following steps that: a ground operation and control center generates a pre-planning type resource allocation scheme according to the data uploading quantity of all ground areas in an ended regression period, and uploads the pre-planning type resource allocation scheme to each satellite in a generic synchronous orbit constellation; the mth satellite in the generic synchronous orbit constellation determines N ground areas needing to be served by the mth satellite in a regression period in the future and time-frequency resources allocated to the nth ground area from a pre-planning resource allocation scheme, and broadcasts the allocated time-frequency resources to the Internet of Things terminals in the nth ground area; and the Internet of Things terminal in each ground area uploads the data acquired by the terminal to the satellite by using the time-frequency resources allocated to the ground area.

This application relates to a method and system for obtaining joint maneuver parameters for geostationary orbit transfer and rendezvous. The method first obtains the initial parameters of the geostationary orbit transfer and rendezvous mission and determines the total number of orbital maneuvers, the total mission duration, and the rendezvous terminal aiming parameters. Then, it sequentially calls pre-constructed GTO transfer maneuver parameter acquisition problem models and GSO rendezvous maneuver parameter acquisition problem models for calculation. Next, it calls a pre-constructed joint maneuver parameter acquisition model for geostationary orbit transfer and rendezvous, considering the GTO transfer maneuver and the GSO rendezvous maneuver together. Finally, it uses a sequential quadratic programming algorithm to optimize and solve the joint maneuver parameter acquisition model for geostationary orbit transfer and rendezvous, obtaining the joint maneuver parameters. This allows for rapid rendezvous with the target spacecraft using the tracker's own thrust-limited orbital control engine, effectively shortening the orbital rendezvous mission time.

This invention discloses a joint fixed-point acquisition method based on continuous small thrust. This method, targeting geostationary orbit satellites using continuous small thrust for orbit transfer, employs a multi-step strategy to gradually approach the satellite's mean longitude to a fixed position. First, before the semi-major axis reaches its final position, the satellite's longitude is continuously moved eastward by manipulating the arrival time, until the semi-major axis reaches the geostationary orbit and is at the fixed longitude position. Then, while correcting inclination and eccentricity isolation residuals, the effects of ground shadows and unexpected ignition failures are overcome by manipulating the stop-fire arc segment, maintaining the satellite's mean longitude at the fixed position. Finally, once the inclination and eccentricity are both in place, a short high-precision fixed-point acquisition is performed, ensuring that the satellite's geographic latitude and longitude are entirely within the dead zone controlled by the geostationary orbit.

The present application relates to a kind of flexible solar wing for sun synchronous orbit satellite constellation and on-orbit control method, solar wing is flexible stacked structure, stack on satellite body in retracted state, solar wing includes oppositely arranged single wing, the single wing includes: substrate assembly, it is configured to carry out photoelectric conversion, the substrate assembly includes: rigid substrate and several flexible substrates;Unfolding mechanism, it is configured to provide unfolding stiffness for solar wing, to ensure that the flexible substrate keeps planar form;And unfolding motor, it is configured to drive the unfolding mechanism unfolding or folding, to realize the retraction or unfolding of solar wing;First solar wing driving mechanism and lifting mechanism are provided between oppositely arranged single wing.The present application is overall used flexible stacked structure form retraction envelope size small, light in weight, does not need additional use satellite attitude control system to carry out attitude adjustment and realizes sun tracking.

The invention discloses a geosynchronous orbit double-frequency radar intelligent detection and imaging integrated system design method, which comprises the following steps of: constructing a geosynchronous orbit L-band system wave position selection schematic diagram, and designing a wave position and related parameters; target grouping is realized on the basis of information such as multi-batch target speeds and position time sequences obtained through L-band target detection and tracking; constructing a geosynchronous orbit C wave band system wave position selection schematic diagram, wherein the designed multiple wave positions can fully cover L wave band footprints; c-band wave position intelligent selection is carried out based on grouping information, and high-frequency-band long-time observation of the target is realized; and sparse SAR imaging is carried out on incomplete aperture echo data obtained in tracking observation. According to the invention, on the basis of the designed L / C dual-band wave position, target tracking information of the L band is utilized to group multiple moving targets, indication information is provided for intelligent selection of the wave position of the C band, long-time observation of the moving targets and sparse zoom imaging of supporting the moving targets are realized, and satellite resources are effectively saved.