30 results about "Orbital plane" patented technology

The invention discloses a radar imaging detection satellite constellation design method, which comprises the following steps of: decomposing a constellation into a plurality of orbit surfaces, uniformly describing each orbit surface through four parameters, constructing an asymmetric constellation structure, and establishing a multi-target optimization model for solving by taking the total cost of the constellation, the maximum revisit time and the detection performance as targets. Non-dominated quantizer sorting is introduced in the sorting process, and satellite constellation design is completed. According to the method, single-satellite-based optimization of the salted fish is converted into orbital plane-based optimization, the optimization variable dimension is remarkably reduced, the method is particularly suitable for large-scale constellation design comprising hundreds of satellites, meanwhile, the Pareto frontier is obtained through non-dominated sorting, various constellation configuration schemes emphasizing different performances are provided, and the method is suitable for large-scale constellation design. Compared with an existing constellation design method, the problems that the to-be-optimized parameters are increased along with the number of satellites, and efficiency is low are solved, the scheme output by the algorithm is more reasonable through the improved sorting mode, and the method can be used for constellation design.

The invention discloses a satellite network laser inter-satellite link establishment method and system, electronic equipment and a storage medium, and mainly solves the problem of low availability of a satellite network established in the prior art due to sun-sun influence. According to the scheme, the method comprises the following steps: inputting constellation configuration parameters of a satellite network, and calculating satellites which are uniformly distributed on each orbit surface; according to the input constellation configuration parameters, establishing a same-orbit inter-satellite laser link between all satellites in the constellation and adjacent satellites in the same orbit plane where the satellites are located; according to the constellation configuration parameters, calculating boundary phase factors used for judging different-orbit link connection modes; and according to the phase factor of the constellation and the boundary phase factor, establishing a different-orbit laser inter-satellite link between satellites on all adjacent orbits, and completing the construction of the whole-network inter-satellite laser link. According to the method, the optimal link connection configuration can be screened out in the satellite network construction stage, the availability of the satellite network is improved, and the method can be used for inter-satellite link sun-sun avoidance.

The invention discloses a visibility prediction method for a low-orbit communication satellite, a terminal and a storage medium. The method comprises the following steps: initializing terminal parameters and target constellation parameters; acquiring ephemeris data of a corresponding satellite based on the target constellation parameter; calculating precession parameters of a satellite orbit in combination with the ephemeris data and the terminal parameters; distributing reference satellites for each orbit of the constellation according to the precession parameters; and predicting the visibility of all satellites of the constellation to the terminal based on the reference satellite and the terminal parameters. According to the method, the reference satellite represents the motion characteristics of the whole orbital plane, so that the calculation complexity of visibility prediction is remarkably reduced, and efficient and rapid prediction of the visibility of the low-orbit communication satellite is realized.

The application discloses an initialization method of a conic surface under a projection linearization track surface, and belongs to the technical field of calculation, reckoning or counting. The method first obtains a preliminary estimation of a target track through three groups of observation data; determines a conic surface containing an initial track surface according to initial track information and geometric knowledge; estimates the missing height information in combination with the conic surface, and obtains more position information of the target in combination with the existing angle information; projects the position information of the target into a two-dimensional section, re-estimates the track parameters by using a least square algorithm, and more accurate track parameters can be obtained; then the iteration process is repeated by using the newly obtained track information until a certain initial orbit determination accuracy requirement is met. The algorithm firstly fits the height information of the target by using a conic surface coordinate system, and realizes linear fitting of the position vector by using a track surface projection method, so that the calculation amount is small and the accuracy is high.

The application discloses an antenna switching method for inter-satellite networking. When the included angle between the direction vector of any antenna in a closed state and the direction vector of the opposite satellite is less than or equal to a preset value within a continuous specified time length, the antenna is opened, and the currently opened antenna is closed.

The invention provides a navigation constellation autonomous orbit determination method based on space-based observation, which comprises the following steps: establishing inter-satellite routing, and permanently establishing a link based on phases between satellites in the same orbit plane; a laser inter-satellite link observation value is obtained, and a vector between every two satellites in the same orbital plane is obtained based on laser inter-satellite link distance measurement and angle measurement observation, that is, the laser inter-satellite link observation value represents vectors from the satellite i to the satellite j; coordinate system conversion: converting the laser inter-satellite link observation value from a satellite body coordinate system to an inertial system; establishing an observation equation; establishing a motion equation; and generating a normal equation, combining the observation equation and the motion equation to generate the normal equation, and performing inversion to obtain an orbit determination result. According to the method, the feasibility of realizing autonomous orbit determination of the navigation constellation through laser inter-satellite link and star-sensitive observation is explained. The direction precision of the laser inter-satellite link is equivalent to or even higher than that of a fixed star sensor, and a high-precision and long-term stable orientation reference can be provided for a normal equation, so that the autonomous orbit determination precision and reliability are improved.

The application provides a stable hierarchical routing method, device and electronic equipment of a star-ground fusion Internet, and relates to the technical field of communication. The method comprises the following steps: dividing the star-ground fusion Internet into three routing domains, the first routing domain comprising a plurality of ground nodes, the second routing domain comprising a plurality of orbital planes, and the third routing domain comprising a plurality of orbits in the same orbital plane; determining the first routing domain according to a ground node address, the ground node address being determined based on the coordinates of the geographic block where the ground node is located in the routing coordinate system; in the case where the first routing domain and the second routing domain are interconnected, using a relay ground station or an opportunistic link to route data from a source end to a destination end; and in the case where the first routing domain and the third routing domain are interconnected, routing data from the source end to the destination end based on an inter-satellite topology state and a routing coordinate system. The scheme of the application can construct a stable and efficient routing hierarchy in a dynamically running star-ground fusion Internet.

Various approaches for the deployment and coordination of network operation processing, compute processing, and inter-satellite communication coordination, within one or multiple satellite non-terrestrial networks, are discussed. Among other examples, a data center located at one or more satellites operating in a middle Earth orbit (MEO) plane, geosynchronous orbit (GEO) plane, or high-Earth elliptical orbit (HEO) plane, may be used to provide network and data processing operations for a low-Earth orbit (LEO) constellation.

The invention provides a space-based service load migration method and system based on thermodynamic diagram dynamic region division. The system comprises a thermodynamic diagram generation module, a dynamic region division module, a migration decision module and a fault-tolerant execution module. The dynamic region division module generates a service load thermodynamic diagram according to the thermodynamic diagram generation module, divides a network region, identifies a service hotspot region and quantifies the level; the migration decision module plans a service load migration path according to the service hotspot area; and the fault-tolerant execution module searches for replacement nodes to generate a plurality of paths, and executes load migration according to the optimal migration path. According to the method, global calculation is decomposed into parallel calculation of multiple orbit planes, global balance of space-based satellite networking platform loads is achieved, and the defect that under low-orbit rasterized giant constellation networking, resource waste and network congestion of partial regions are caused by uneven service loads is overcome.

A system includes a plurality of satellites in orbit around a celestial body in a plurality of orbital planes. Each satellite includes an imaging device having a field of view (FOV) to capture an image of a sky that includes celestial image features of resident space object (RSO), stars, and / or planets. The satellite processor is configured to receive image data from sensors in the imaging device, to increase a positional detection accuracy of the celestial image features by defocusing imaging optics of the imaging device, to capture image data in a volume of the sky as the FOV of the imaging device on each satellite moves in an orbital plane, and generate by a centralized computer at least 1,000 celestial image features using the image data transmitted from each of the satellites.

The invention discloses a double-satellite remote sensing system and method based on inter-satellite laser communication and tracking and pointing integration, and relates to the technical field of space remote sensing. The system is composed of a first satellite and a second satellite which fly back and forth in the same orbital plane, and the first satellite and the second satellite are respectively provided with a multispectral camera, a hyperspectral camera and a transmission system integrating tracking and pointing, inter-satellite laser communication and multi-dimensional calibration functions. The transmission system comprises an inter-satellite laser communication load and a Beidou short message backup load, a stable laser link can be established autonomously, and tracking and pointing precision is guaranteed through three calibration modes of fixed star, satellite-ground and inter-satellite. The system transmits trigger information through an inter-satellite laser link, and realizes collaborative observation of multispectral general survey-hyperspectral detailed survey. The method comprises the steps of calibration preposition, laser link establishment, collaborative observation, calibration maintenance and the like, and supports data collaboration and emergency communication. The timeliness and observation precision of double-satellite remote sensing are improved, and the high-reliability and high-timeliness requirements of scenes such as earth surface anomaly monitoring and the like can be met.

This invention discloses a method for initial orbit determination of a non-cooperative target under space-based angle-only extremely short arc observation, belonging to the technical field of initial orbit determination. This invention addresses the failure of existing initial orbit determination methods under extremely short arc conditions. The method includes: using the unit normal vector of the target orbital plane as the variable to be optimized; obtaining the relationship between the slant distance and the unit normal vector based on the geometric relationship between the target position vector, the slant distance between the space-based platform and the target position, the target azimuth unit vector, and the space-based platform position vector; transforming the solution of the unit normal vector into the solution of the X-axis and Y-axis components of the unit normal vector based on the normalization characteristics of the unit normal vector, and determining the constraints of the solution; and employing a heuristic algorithm to solve for the X-axis and Y-axis components of the unit normal vector, thereby determining the unit normal vector and achieving initial orbit determination. This invention improves the accuracy and robustness of initial orbit determination.

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.

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.

Dental facebow device for orbital plane alignment

This invention discloses a midnight sun avoidance method for geostationary satellites that ensures effective imaging. This method not only prevents sunlight from entering the beveled sunshade, but also ensures that satellite camera imaging quality meets operational requirements during the midnight sun avoidance period, reducing the satellite's daily detection blind time to minutes. Furthermore, the camera's optical axis autonomously returns to pointing toward the Earth's center before and after midnight sun avoidance. Three avoidance strategies are designed based on the annual change in the angle between the sun vector and the satellite's orbital plane to optimize the avoidance trajectory and improve coverage of key observation areas.

This invention discloses a large-scale space target collision early warning combination screening method, belonging to the field of space situational awareness. The implementation method is as follows: Preliminary screening of similar targets is performed based on the distance between intersection points on the orbital plane intersection line to quickly reduce the number of satellite combinations to be analyzed; by decomposing the analytical solution considering the minimum relative distance between satellites under J2 perturbation, it is divided into long-term terms and exact solutions; based on the evolution characteristics of the long-term terms, a second screening is performed using the trend characteristics of the long-term terms; a third screening is performed using the analytical exact solution considering the relative distance between satellites under J2 perturbation; based on the results of the third screening, satellite combinations with collision risk are determined, realizing large-scale space target collision early warning combination screening, thereby protecting the safety of space assets. This invention fully considers the long-term evolution characteristics of orbits under perturbation, significantly reducing the calculation time for early warning, and is suitable for rapid screening of long-term collision early warnings for large-scale space targets.

The invention discloses a multi-satellite cooperative computing and task scheduling method and system suitable for constellation scale evolution, and the method comprises the steps: obtaining heterogeneous state data of each satellite based on an orbital plane state view under a current time slot, carrying out the unified feature coding, obtaining the feature representation of each satellite, and aggregating the feature representation into an orbital plane-level global state feature; segmenting and coding each to-be-decomposed task according to the global state characteristics to obtain a sub-task decomposition frequency, a task decomposition scheme and an action vector for executing a satellite allocation scheme of each to-be-decomposed task; calculating the task completion rate of each priority group according to the action vector and the task priority to determine a system-level reward value; and updating each satellite state according to the computing resources correspondingly used by each to-be-decomposed task under the current time slot to generate a next time slot orbital plane state view, returning to execute the step of obtaining the heterogeneous state data until all time slots are iterated, and obtaining a task scheduling scheme based on the action vector corresponding to each to-be-decomposed task under each time slot.

The embodiment of the invention provides a navigation enhancement method and a communication system, the method is applied to a satellite, and the method comprises the following steps: receiving a first navigation enhancement request sent by a base station; the first navigation enhancement request is generated based on enhancement information in a second navigation enhancement request and a satellite identifier of a satellite after the base station receives a first control plane signaling carrying the second navigation enhancement request sent by the core network; on broadcast sub-resources respectively corresponding to a plurality of beams of a satellite, respectively broadcasting enhancement data through the plurality of beams, and respectively obtaining enhanced navigation information by terminals respectively corresponding to the plurality of beams based on the enhancement data and corresponding GNSS observation data; the broadcast sub-resource is a combination of a time slot resource and a sub-carrier resource, and sub-band resources associated with adjacent track planes are different. The GNSS observation data is enhanced through the enhancement data, more accurate navigation information is obtained, and inter-satellite interference is reduced while the time-frequency resource utilization rate is improved.

The invention relates to the technical field of atmospheric science and remote sensing, in particular to a space-based distributed near space atmosphere detection method, system, device and product, and the method comprises the steps: designing a plurality of satellites for detecting near space atmosphere based on the number of orbital planes and the number of satellites included in each orbital plane; detecting the near space atmosphere at a target moment based on each satellite, and obtaining state parameters of the near space atmosphere from different angles; obtaining a tomographic equation based on the global three-dimensional grid diagram and the obtained state parameters; and solving the tomographic equation to obtain the three-dimensional distribution characteristics of the near space atmosphere at the target moment. A plurality of satellites are designed through an orbital plane, various observation modes can be effectively compatible, and multi-dimensional data of near space atmosphere can be obtained; the state parameters are processed by using the global three-dimensional grid diagram so as to extract key three-dimensional parameter information, and the state and the change process of the near space atmosphere can be accurately monitored and predicted.

This invention provides a method for optimizing the configuration of a GEO satellite sunshade and the sunshade itself, including the following steps: Step A: Establishing an orbital coordinate system and calculating the solar vector, the angle between the Earth-axis composite plane and the orbital plane, and their maximum values; Step B: Selecting a suitable basic configuration of the sunshade based on the onboard layout requirements; Step C: Calculating the distance from the sunshade plate perpendicular to the orbital plane to the camera's line of sight; Step D: Drawing the upper curve of the sunshade plate; Step E: Determining whether the sunshade plate constructed based on the upper curve obstructs the camera's field of view; Step F: Drawing the tangent to the curve and using the tangent as the upper curve of the sunshade plate; Step G: Determining whether the sunshade plate constructed based on the tangent to the upper curve obstructs the camera's field of view. This invention eliminates the need for large-scale simulations using specialized optical simulation tools, facilitating rapid optimization of the large field-of-view camera and other onboard layouts by satellite engineers.

This invention discloses a multi-satellite collaborative computing and task scheduling method and system applicable to constellation-scale evolution. The method includes: acquiring heterogeneous state data of each satellite based on the orbital plane state view of the current time slot, performing unified feature encoding to obtain the feature representation of each satellite, and aggregating them into a global state feature at the orbital plane level; segmenting and encoding each task to be decomposed according to the global state feature to obtain an action vector including the number of sub-task decompositions, the task decomposition scheme, and the satellite allocation scheme for each task to be decomposed; calculating the task completion rate of each priority group based on the action vector and task priority to determine the system-level reward value; updating the state of each satellite according to the computing resources used by each task to be decomposed in the current time slot to generate the orbital plane state view of the next time slot, and then returning to the step of acquiring heterogeneous state data, until all time slots are iterated, and obtaining a task scheduling scheme based on the action vector corresponding to each task to be decomposed in each time slot.

The application discloses a satellite network topology discovery method, a path construction method and device, the method comprising: dividing the satellite network into autonomous domains and establishing a SID matrix and a satellite node adjacency matrix by assigning each satellite an extended SRv6 SID containing a network prefix, an orbital plane number, a node number, a service type and a resource margin; the satellite node perceives its own resource state, periodically detects the link state by using a BFD protocol, synchronizes the values of each element in the matrix by using an incremental update mechanism, and realizes dynamic topology perception; meanwhile, a routing path construction method based on the SID matrix and the adjacency matrix is proposed, which supports the satellite node to locally perform path calculation. The method supports heterogeneous service identification and resource state perception, can effectively reduce signaling overhead, improve the accuracy of satellite network topology discovery and routing efficiency, and improve the cross-constellation computing power pooling and collaborative computing capability.

The invention discloses a configuration, deployment and maintenance integrated design method for a ground coverage heterogeneous constellation. Comprising the steps of performing task and resource analysis, determining a direct constraint condition, calculating an indirect constraint condition, and constructing an alternative satellite library; a genetic algorithm is adopted, minimization of constellation total cost is taken as an optimization target, direct and indirect constraint conditions are combined, hierarchical step-by-step solving is carried out on the number of the sub-constellations and the configuration parameters of all the sub-constellations, and the optimal number of the sub-constellations and the configuration parameters of all the sub-constellations are obtained; the configuration parameters comprise an inclination angle, a semi-major axis, the number of orbital planes, an ascending node right ascension set, the number of satellites per orbit and satellite type selection; for each sub-constellation, determining a deployment scheme of each orbital plane; and for each sub-constellation, determining a maintenance scheme of each orbital plane. The method comprises configuration design, deployment scheme design and maintenance scheme design, and the whole-process design and comprehensive efficiency optimization of the ground coverage heterogeneous constellation are realized.

This invention provides a polar-orbiting satellite navigation constellation system, a navigation method, and a user terminal. The polar-orbiting satellite navigation constellation system includes: four orbital planes, each with its intersection point with the equator evenly distributed along the equator, with a longitude interval of 45 degrees between adjacent orbital planes; nine satellites evenly distributed on each orbital plane, with a phase interval of 40 degrees between adjacent satellites; each satellite orbits at an altitude of 80,000–90,000 km and an orbital inclination of 90 degrees. It also employs an isotope power supply system and a redundant cold / hot backup system in the attitude and orbit control system. This invention utilizes a high-orbit scheme that avoids the influence of the Van Allen radiation belts, effectively solving the radiation effects caused by the Earth's radiation belts and increasing the reliability of the navigation system; the use of an isotope power supply system improves the operational lifespan of the navigation system; and the cold / hot redundant backup of the attitude and orbit control system enhances the reliability of the control system.

The invention provides a giant constellation multi-objective optimization design method based on knowledge migration, and the method comprises the steps: firstly building a giant constellation system key subject analysis model which is used for providing a model basis for the subsequent giant constellation analysis; constructing a mathematical optimization model which takes the orbit height, the orbit inclination angle, the orbital plane number and the like as design variables, considers constellation ground coverage constraints, and realizes the minimization of the total mass of the giant constellation system and the maximization of the inter-satellite capacity; on the basis, in order to avoid the problem of cold start in the design process, a population screening strategy and a sequence sampling mechanism are customized, a multi-objective optimization design method based on knowledge migration is constructed to optimize pre-selected design variables, and a design scheme that the total mass of a constellation system is as small as possible and the inter-satellite capacity is as large as possible is obtained. And then the giant constellation scheme design is completed. According to the method, the optimization efficiency of the overall design stage can be improved, the design period can be shortened, and the design, modification and optimization of the giant constellation scheme can be quickly completed.

This invention discloses a laser reflection tomography three-dimensional imaging method and system, relating to the field of three-dimensional imaging technology. The method is used to achieve high-resolution imaging and accurate identification and description of the three-dimensional contour structure of space targets; it includes: acquiring multi-angle echo information of the target, completing the reconstruction of a two-dimensional image of the orbital plane, and efficiently and accurately calculating the target's orbital axial reflectivity distribution based on multiple sets of orbital plane two-dimensional images, thereby completing the accurate reconstruction of the target's three-dimensional image and solving the problem of high-resolution three-dimensional reconstruction of the external structure of space targets. In this method, three-dimensional laser reflection tomography provides an additional dimension of information for reconstructing the three-dimensional image; thus more comprehensively reflecting the target's shape, size, and structural details, which is more conducive to further processing of the target image at the cognitive end.

This invention discloses an integrated design method for the configuration, deployment, and maintenance of heterogeneous constellations for Earth coverage. The method includes: conducting mission and resource analysis to determine direct constraints, calculating indirect constraints, and constructing a candidate satellite pool; employing a genetic algorithm, with the optimization objective of minimizing the total constellation cost, and combining direct and indirect constraints, to solve for the optimal number of sub-constellations and their configuration parameters hierarchically and stepwise, obtaining the optimal number of sub-constellations and their configuration parameters; configuration parameters include inclination angle, semi-major axis, number of orbital planes, right ascension set of ascending nodes, number of satellites per orbit, and satellite selection; for each sub-constellation, determining the deployment scheme for each orbital plane; and for each sub-constellation, determining the maintenance scheme for each orbital plane. This invention's method encompasses configuration design, deployment scheme design, and maintenance scheme design, realizing the full-process design and comprehensive performance optimization of heterogeneous constellations for Earth coverage.

The invention provides a satellite service coverage period calculation method and apparatus, and an electronic device. The method comprises the steps of determining a first quantitative relationship between an off-axis angle and a target angle according to a tetrahedron spatial geometrical relationship formed by a projection point of user equipment on an orbital plane coordinate system, a geocentric position, a target satellite position and a user equipment position; the target angle is the difference between the target satellite latitude argument at the initial moment of the target time period and the instantaneous projection included angle of the user equipment on the orbital plane; determining the maximum value of the target angle when the user equipment is under the target satellite service coverage condition according to the first quantitative relationship between the off-axis angle and the target angle, the second quantitative relationship between the target satellite latitude argument and the target angle and the constraint condition of the maximum off-axis angle of the target satellite; and determining a time boundary of the user equipment under the coverage of the target satellite service in the target time period according to the maximum value of the target angle. By converting the maximum off-axis angle constraint of the satellite beam into the constraint of the satellite latitude argument, the satellite service coverage time period can be quickly obtained.

The invention discloses a method for quickly calculating a transit time window of a Walker constellation to a ground area. According to the method, for rapid calculation of the transit time of a ground area, firstly, given time range information, constellation orbit information and ground area information are obtained, secondly, the intersection situation of an orbit surface and the ground area is analyzed, time windows where transit events possibly occur on satellites are screened, and then the transit time of the ground area is calculated according to the characteristic that Walker constellation satellites are evenly distributed on the orbit surface. And quickly calculating the satellite orbit position in the potential transit time window, and finally judging that the sub-satellite point is inside and outside the area to obtain the transit time window. According to the method, the intersection condition of the orbital plane and the ground area is analyzed, and the characteristic that the Walker constellation is uniformly distributed on the orbital plane is combined, so that the time window of the satellite passing the ground area can be quickly calculated. The method has the advantages that (1) the calculation efficiency is remarkably improved; and (2) the method is suitable for large-scale Walker satellite constellations.