94 results about "Constellation" patented technology

A computer-implemented method is provided for acquiring a set of x unique tracking constellations in a predefined 3D space, each constellation for a corresponding wearable tracking device used to track a wearer in a 3D environment. Each unique tracking constellation includes a predefined number n tracking objects. A set of y discrete available locations is defined for locating the tracking objects within the predefined 3D space. A minimum number m of tracking objects is defined, wherein the minimum number is less than or equal to the predefined number n of tracking objects. For each unique tracking constellation, a unique discrete available location from the set of y discrete available locations is assigned to each tracking object of the tracking constellation to acquire the unique tracking constellation. The assigned location for any minimum number m of tracking objects in each unique tracking constellation is unique within the set of x unique tracking constellations.

The application relates to the technical field of satellite laser communication. The application discloses an intersatellite laser communication in-orbit calibration method, device, satellite and system, which can realize parallel initiation and cooperative execution of multi-satellite calibration tasks and improve the networking efficiency of a large-scale constellation. The method comprises the following steps: acquiring visible state information of each satellite in an intersatellite laser communication system; based on the visible state information of all satellites in the intersatellite laser communication system, performing calibration processing on all satellites in the intersatellite laser communication system in a parallel calibration mode to obtain a first final calibration result; judging whether all satellites complete calibration based on the first final calibration result to obtain a first judgment result; in the case that the first judgment result is that not all satellites complete calibration, performing calibration processing on all uncalibrated satellites in a cooperative calibration mode to obtain a second final calibration result; and the second final calibration result is used for reflecting that all satellites have completed calibration.

The application provides a GNSS / inter-satellite link distributed cooperative real-time orbit determination method and device for a mega constellation, first, each satellite in a cluster performs preliminary orbit determination based on local GNSS observation data and IMU data to obtain preliminary determination results of each satellite in the cluster; then, a cluster head satellite collects the preliminary determination results to determine relative orbit parameters in the cluster; then, a backbone node collects the relative orbit parameters to determine a regional absolute orbit reference; a global anchor satellite determines unified constellation orbit parameters; finally, according to the regional absolute orbit reference and the unified constellation orbit parameters, orbit determination results of each satellite are determined. Through a three-level hierarchical cooperative architecture, the application disperses data processing and determination tasks to different level nodes, avoids data processing bottlenecks of a central node and communication link congestion problems in centralized technology, reduces complex interaction between nodes and inter-satellite link resource occupation in a thousand-star level scale in traditional distributed technology, and shortens iteration convergence time.

The application relates to a multi-star cooperative planning method based on multiple decision-making master stars, and steps are as follows: when a constellation receives a multi-point burst task, multiple decision-making master stars are triggered to be formed according to master star generation rules, the multiple decision-making master stars correspond to different task sets, priority evaluation and parallel bidding are carried out, and candidate observation resources are determined according to bidding information of member stars; the decision-making master stars perform consistency pricing according to observation quality, observation time and execution cost of the candidate observation resources; the decision-making master stars perform whole-network synchronization on task information, candidate observation resources and corresponding prices of each decision-making master star; the multiple decision-making master stars generate a resource pre-scheduling scheme by adopting a parameterized multi-task conflict resolution model according to global task priority distribution and candidate resource price distribution; the multiple decision-making master stars score the pre-scheduling schemes generated by the multiple decision-making master stars according to predetermined rules, then perform whole-network synchronization on the pre-scheduling schemes and corresponding scores, and take the pre-scheduling scheme with the highest score as a final planning result.

A communication method and a communication apparatus, relating to the technical field of communications. In the method, an access network device sends first information and indication information to a terminal, wherein the first information indicates a first constellation pattern set, the indication information indicates a first constellation pattern in a second constellation pattern set, and the second constellation pattern set comprises the first constellation pattern set; and the terminal determines the first constellation pattern on the basis of the first information and the indication information. Because channel conditions of a plurality of sub-resources corresponding to one codeword are stable within a certain time period, the access network device may select, on the basis of the channel conditions of the plurality of sub-resources, the second constellation pattern set from an initial constellation pattern set corresponding to the codeword, and indicate a constellation pattern in the second constellation pattern set. Thus, the described solution can reduce the indication overhead of a constellation pattern.

This application relates to the field of intelligent aerospace technology and discloses a satellite autonomy method driven by embodied intelligent agents, applicable to subsatellites belonging to an in-orbit constellation. It constructs a multi-agent framework comprising multiple autonomous intelligent agents, including at least a resource assessment agent and a resource optimization agent. In response to a resource assessment command regarding the target mission, the method acquires the subsatellite's in-orbit operating parameters. The resource assessment agent is invoked to perform resource assessment based on the in-orbit operating parameters, obtaining the mission resource assessment result, which is then fed back to the in-orbit constellation. If mission feasibility indicates that the subsatellite can execute the target mission, the method acquires a single-satellite mission plan fed back by the in-orbit constellation. The resource optimization agent is invoked to optimize resource allocation based on the single-satellite mission plan, obtaining a mission operation plan. Its beneficial effects are that it improves the intelligence level of subsatellites in remote sensing observation missions and enhances the satellite's in-orbit autonomy.

A method, system, product, equipment, and storage medium for autonomous control of the satellite's semi-major axis based on energy constraints are disclosed. Belonging to the field of on-orbit satellite orbit control, this invention solves the problem that existing technologies rely on manual ground planning and command uploading, making it difficult to meet the needs of efficient autonomous orbit control for large-scale constellations. The method involves acquiring the satellite's real-time position and velocity, calculating the corresponding orbit control discrimination parameters, combining a bilateral semi-major axis threshold orbit control strategy to obtain the required orbit control quantities, acquiring the current solar phase angle and satellite orbit parameters, calculating the shadow area initiation phase, and the start time of control. Based on the required orbit control quantities and the energy constraints of a single orbit control operation, the planned orbit control duration parameters are calculated. The start time and planned orbit control duration parameters are used as orbit control execution parameters to achieve autonomous control of the satellite's semi-major axis.

The application relates to a design method of a moon global positioning constellation based on a lunar space DRO reference orbit, wherein the initial orbit state and the orbit period of any DRO reference orbit in a DRO reference orbit to be deployed are determined based on the initial phase of the DRO reference orbit; the initial orbit state of any satellite to be deployed on the initial phase of the DRO reference orbit is determined based on the orbit state corresponding to the target phase; the orbit period of the any satellite is determined based on the orbit period of the any DRO reference orbit; the target orbit state corresponding to the any satellite is obtained based on the orbit period of the any satellite and the initial orbit state of the any satellite; and the moon global positioning constellation under a four-body model is constructed based on the target orbit state corresponding to each satellite. The moon global positioning constellation constructed by the application has higher stability and higher moon surface coverage capacity compared with the existing near-moon constellation.

Systems and methods are described for connecting with LEO satellites while reducing emissions toward GEO satellite communications. A system to implement the instant techniques may include a system comprised of a user communications equipment and a LEO constellation. The user equipment (“UE”) may comprise a communications modem and an active antenna unit with a transmit and receive beamformer. In further implementations, the UE may include additional receive only beamformers. The LEO constellation can have a regenerative payload or bent pipe, and can include orbits at different altitudes. Methods as described herein may include a procedure by which the user equipment and LEO satellite work together to identify candidate serving satellites, and select the one that allows to meet the power density requirements to avoid interfering with the GEO satellites.

The application relates to a rotation error correction method of a distributed autonomous navigation constellation, and comprises the following steps: S1, each satellite calculates the orbit plane orientation error of the satellite in orbit and distributes the result to all visible satellites in the constellation in real time; S2, each satellite fits a local constellation rotation quantity according to the orbit plane orientation error of the satellite and the collected orbit plane orientation error; S3, each satellite determines a virtual satellite orbit observation quantity according to the local constellation rotation quantity of the satellite; S4, each satellite constructs a conditional constraint equation of virtual observation according to the virtual satellite orbit observation quantity and the second type of non-singularity orbit root number; and S5, each satellite solves the satellite orbit through filtering according to the conditional constraint equation of virtual observation, so that the overall rotation effect of the constellation is inhibited and corrected. The application can inhibit the rotation effect of the constellation, improve the distributed autonomous orbit determination precision of the satellite, does not increase the inter-satellite data interaction communication pressure, and can stably maintain the constellation configuration for a long time.

The application discloses a kind of multi-star multi-station space-ground communication window timing planning methods based on constraint driving time grid, comprising: based on the satellite orbit parameters of the constellation to be studied, ground station position parameters, combined with constraint condition configuration, carry out visibility calculation, generate the visible time window of each ground station and each satellite, combined with the number of each ground station antenna, obtain the visible time window based on antenna granularity;According to the grid interval of constraint driving, carry out grid index calculation and persist for each visible time window;Two-stage window timing planning is carried out to all visible time windows in constellation, in the first stage, carry out continuity preliminary selection, by traversing all visible time windows, successively execute multidimensional conflict detection and constraint verification, obtain preliminary selection result;In the second stage, traverse the preliminary selection result of each satellite, carry out recursive candidate filling to the gap position between adjacent time windows, to maximize the filling communication gap;Output scheduling scheme and evaluation index.

This provides a real-time kinematic (RTK) solution for mobile devices with multi-constellation, multi-frequency (MCMF) capabilities, where a single base station may have a baseline much farther than that of a traditional base station. To achieve this, the embodiment addresses atmospheric effect differences between the rover and the base station when the GNSS positioning of the mobile device (rover) is fixed, thereby allowing the determination of individual tropospheric delay errors at the base station. The embodiment can utilize additional satellite measurements that are not available without RTK correction, and can also use orbital clock correction for these additional satellite measurements.

This invention provides a low-Earth orbit (LEO) satellite cross-layer reliability constraint system and method. The system includes a rate adaptive controller, which comprises a fine-grained rate adjustment module and a reliability constraint decision module working collaboratively. The fine-grained rate adjustment module achieves fine-grained continuous adjustment of the transmission rate by allocating non-uniform transmission probabilities to constellation symbols and dynamically adjusting the shaping entropy under a fixed basic modulation and coding format. The reliability constraint decision module is used to statistically model the physical layer decoding reliability and evaluate its statistical confidence level based on the cumulative distribution function of decoding success under different modulation and coding schemes. This invention achieves fine-grained continuous adjustment of the transmission rate through probabilistic shaping technology and introduces a reliability constraint mechanism based on decoding statistical characteristics, thereby improving the throughput and link stability of LEO satellite-to-ground communication under dynamic channels.

This invention discloses a method, apparatus, device, and storage medium for satellite-rocket coordinated mission planning. The method determines constellation configuration parameters based on the performance requirements of the current satellite-rocket coordinated mission and satellite resources. The constellation is then divided into several subsets based on these parameters, with each subset corresponding to a certain number of launch missions. Based on the number of launch vehicles and support positions at each launch site, each subset is allocated to each launch site according to a preset ratio. A preliminary deployment plan is generated based on the launch vehicle selection, launch site planning, and launch window planning at each launch site. The preliminary deployment plan is then used to verify whether the current launch resources meet the constraints. If they do, the current satellite-rocket coordinated mission is executed; otherwise, the constellation configuration parameters are redefined. This method achieves efficient coordination in satellite-rocket coordinated mission planning through a dynamic closed-loop optimization mechanism, improving resource utilization and ensuring mission feasibility under timeliness, launch window, and support position constraints.

This invention discloses a method for analyzing the configuration stability of a high-precision space measurement constellation based on decoupled state transition tensors, belonging to the field of space technology. The method involves: decoupling the influence of different perturbations on configuration stability; establishing a mapping relationship between the spacecraft's orbital state and configuration stability indices; substituting the obtained orbital state transition tensor expression for perturbation decoupling into the method to obtain the state transition tensor expression for the configuration stability indices; analyzing and obtaining the influence of different perturbations on configuration stability, thereby supporting the optimization of the high-precision space measurement constellation configuration, improving the performance of the high-precision space measurement constellation system, and increasing detection accuracy. This invention has the advantages of high accuracy and high efficiency in analyzing the configuration stability of high-precision space measurement constellations, which is beneficial for the rapid iterative optimization of high-precision space measurement constellation configurations and for improving the stability and detection performance of high-precision space measurement constellation configurations.

The application discloses a high-precision time offset autonomous calculation method and system based on satellite speed v and gravity acceleration g. By establishing a closed correlation between the gravity field strength and the orbital speed, the traditional multi-parameter relativistic time correction model is simplified to a closed-form calculation depending on only two in-orbit measurable physical quantities, without the need for input of orbital radius, universal gravitational constant, earth mass, external ephemeris, etc. The application has outstanding originality, simple calculation, strong autonomy and reliable precision, can realize a daily cumulative time error of less than 1 ns, is suitable for low-orbit satellites, navigation satellites, constellation systems and various high-reliability time service scenarios, has a wide application range and high industrial value, and can significantly improve the autonomous time service capability of a spacecraft and the stability of a time system.

This invention proposes a satellite-ground collaborative mission management method for Earth observation space cloud services, belonging to the field of satellite application and management technology. This method first identifies three main roles in satellite-ground collaborative mission management; secondly, it selects a management mode based on the urgency and complexity of the needs; then, it generates mission plans and instructions for the remote sensing satellite constellation and telemetry and control station network, and executes the missions; finally, after mission execution, data is received through the space edge cloud service center and the ground station network, thereby achieving management under a cloud architecture. This method overcomes the shortcomings of existing methods, such as difficulty in coordinating satellite-ground missions, difficulty in coordinating multiple types of users, and slow data transmission speeds. It improves the collaborative management performance of remote sensing satellite missions under a satellite-ground integrated system and can meet the application requirements of rapid, accurate, and comprehensive remote sensing satellite mission planning and management.

This invention belongs to the field of low-Earth orbit remote sensing satellite technology and provides a method and system for inter-satellite phase design based on sensor field-of-view matching. The method includes: observation and positioning to obtain the characterization of inter-satellite phase design input variables; calculating the upper and lower limits of the inter-satellite phase difference based on the characterization of the inter-satellite phase design input variables; determining the range of inter-satellite phase difference values; and outputting the phase difference. This invention solves the problem of field-of-view matching during satellite relay, improving the accuracy of relays. It further considers satellite sensor field-of-view matching when satellites have a cooperative relationship, making the problem more targeted to specific scenarios. It is applicable to applications such as Earth remote sensing observation and space debris observation, and is suitable for various sensors, including optical and microwave sensors. It can provide direct guidance for the design of various specific constellation schemes with inter-satellite relay cooperation.

Communication systems are described that use signal constellations, which have unequally spaced (i.e. ‘geometrically’ shaped) points. In many embodiments, the communication systems use specific geometric constellations that are capacity optimized at a specific SNR, over the Rayleigh fading channel. In addition, ranges within which the constellation points of a capacity optimized constellation can be perturbed and are still likely to achieve a given percentage of the optimal capacity increase compared to a constellation that maximizes dmin, are also described. Capacity measures that are used in the selection of the location of constellation points include, but are not limited to, parallel decode (PD) capacity and joint capacity.

This application relates to a MIMO detection device and a receiving device. The device includes: an LR module, an MMSE-SIC module, and an LSD module; the LR module is used to receive a first channel matrix from a noise whitening device and decompose the first channel matrix using the LLL algorithm to obtain a second channel matrix; the MMSE-SIC module is used to determine the constellation coordinates of the transmitted data as hard-determined points based on the second channel matrix and the received data from the noise whitening device; the LSD module is used to calculate, through tree search, a first minimum Euclidean distance value when all bits in the transmitted data are positive bits, and a second minimum Euclidean distance value when all bits in the transmitted data are negative bits, based on the hard-determined points; the LSD module is also used to determine the log-likelihood ratio of the transmitted data based on the first minimum Euclidean distance value and the second minimum Euclidean distance value. The receiving device includes this device.

The application discloses a kind of NGSO constellation to GSO earth station lumped interference determination method and system, belong to satellite communication and radio electromagnetic compatibility analysis technical field, method includes: acquisition NGSO constellation and GSO earth station core parameter;Analysis orbit parameter determines reference satellite position plane, conversion geocentric angle and divide coarse grid;Iterate coarse grid and deduce whole constellation satellite three-dimensional position;Calculate link angle and screen collinear interference satellite, mark initial CIR;Satellite position probability density function is constructed, and the total interference probability that initial CIR is integrated is obtained;Compare threshold probability and optimize CIR range;Subdivide final CIR into fine grid, calculate each point lumped interference and probability;Local cumulative distribution curve is constructed, and interference determination is completed by comparing with protection limit value.The application is combined with physical geometric constraint and probability density distribution theory, greatly reduce the amount of calculation, guarantee determination accuracy and compliance, applicable to spectrum coordination, satellite network declaration and other engineering scenarios.

The application provides a network RTK differential correction number generation method based on Beidou and low-orbit constellation fusion, which comprises data acquisition, receiving pseudorange observation values and carrier phase observation values of Beidou satellite navigation system satellites and low-orbit constellation satellites through a ground reference station receiver simultaneously; constructing a joint observation model of Beidou satellite navigation system and low-orbit constellation, and using an extended Kalman filtering algorithm to estimate receiver clock difference and system bias between the two systems in real time; adaptive weighted differential correction number calculation, calculating pseudorange differential correction numbers of Beidou satellites and low-orbit satellites respectively based on the estimated system bias; correction number broadcasting, dynamically determining the effective duration of the differential correction number of the low-orbit satellite according to the orbit height of the low-orbit satellite, and encoding the correction numbers of the Beidou satellites and the low-orbit satellites into RTCM text format to broadcast to the user end; the user end receives the correction numbers, corrects the local Beidou satellite and low-orbit satellite observation values, performs joint RTK solving, and verifies and confirms ambiguity fixing.

The application provides a simulation method and system for navigation satellite inter-satellite link observation data, and belongs to the field of navigation satellite inter-satellite link data simulation. The method first acquires constellation configuration parameters and dynamic parameter configurations, and performs orbit integration to generate position parameters and velocity parameters of all navigation satellites in the constellation; then, according to the position parameters and the velocity parameters, clock difference polynomial coefficients and corresponding reference time, the inter-satellite geometric distance between any two satellites and satellite clock difference parameters are calculated; zero value parameters of any two satellites are simulated, and error parameters changing with direction and combined values of random noise of any two satellites are simulated; finally, according to the inter-satellite geometric distance, the satellite clock difference parameters, the zero value parameters and the error parameters changing with direction and the combined values of random noise, an inter-satellite observation data simulation equation of any two satellites in the constellation is constructed. The simulation accuracy and precision of the satellite inter-satellite link are improved.

This invention discloses a dynamic clustering method for space-based distributed collaborative detection. First, based on dynamically changing mission requirements and target status, a dynamic clustering algorithm optimized for collaborative detection performance is designed to cluster satellites within the constellation. Then, using the comprehensive capabilities of nodes as a crucial basis for node star election and cluster structure maintenance, a multi-factor weighted dynamic edge node star selection algorithm is designed, ultimately achieving a hierarchical, ordered, distributed collaborative architecture of "constellation-cluster-single star". This invention can reduce the information propagation cost within the constellation and improve information collaboration and mission execution efficiency.

The application discloses a deep space exploration constellation system integrated simulation verification method and belongs to the technical field of spaceflight digitized simulation verification. The method comprises the following steps: acquiring a constellation system digitized design model; constructing a standardized message bus taking a CSV file as a carrier, and bidirectionally connecting the digitized design model with a plurality of external professional simulation tools; extracting design parameters from the digitized design model and packaging the design parameters into a first CSV file, and transmitting the first CSV file to the external simulation tools; listening to the message bus to acquire a second CSV file output by the external simulation tools, and analyzing simulation result data; automatically writing the simulation result data back to the digitized design model, and triggering automatic updating of corresponding design parameters; repeating the above steps until the simulation result data meets preset verification conditions or optimization targets, and generating a simulation verification report. The application realizes bidirectional closed-loop iteration between a design model and a simulation model, and improves the automation level of constellation system design verification.

The present disclosure provides an NLP-based remote sensing constellation intelligent scheduling system, method, device, electronic equipment and medium. The system is composed of a medium orbit / high orbit relay satellite and a low orbit satellite as a control node: the relay satellite is built-in with a generative large model NLP, which can directly receive and semantically analyze the task request sent by the terminal in natural language, and generate a multi-satellite cooperative task pipeline scheduling strategy in real time; then through the inter-satellite link, the target low-orbit satellite is distributed in milliseconds, driving each satellite to execute the corresponding sub-task in order and return the intermediate or final result; after completing the sub-task, the low-orbit satellite forwards the execution result data to the next satellite in the pipeline or directly sends it back to the control satellite, and finally the control satellite feeds back the summary result to the user terminal at one time. Without the intervention of the ground station, the system realizes the natural language driving of "user-relay satellite-remote sensing constellation" end-to-end, on-orbit real-time closed-loop scheduling, and significantly reduces the task response delay.

This invention relates to the field of remote sensing data processing technology, specifically to a satellite-ground integrated distributed processing method for remote sensing constellation data, comprising the following steps: S1: acquiring raw remote sensing images in orbit; S2: performing data preprocessing on the raw remote sensing data, including radiometric calibration, sensor correction, and geometric coarse correction; S3: performing rapid region segmentation and ground feature classification and initial screening; S4: making task coordination and distribution decisions based on the confidence level C and type Type of each initially screened target; S5: data encapsulation and downlink, encapsulating the data to be transmitted back to the ground; S6: ground system reception, receiving the data packets transmitted from satellite; S7: the ground system distributes the data to the corresponding dedicated processing algorithm for final image interpretation and processing based on the data information. This invention creatively designs a "coarse screening-distribution" satellite-ground collaborative processing flow and a multi-level processing architecture of "main satellite distribution-constellation system-ground fine interpretation".

The application relates to a star ceiling control method, a star ceiling control device, a star ceiling control equipment and a storage medium, and belongs to the star ceiling field, wherein the star ceiling control method comprises the following steps: in response to a control instruction, the control instruction is analyzed, and a lamp effect configuration is updated; and a lamp effect is generated according to the analyzed instruction and is executed. The star ceiling control method of the application realizes wireless and intelligent lamp effect regulation and control of the star ceiling through Bluetooth (BLE) and light voice control, has special effects such as constellations and meteors, supports flexible adaptation of 256 / 512 lamp beads, and realizes binding of special effects and custom instructions.

The invention relates generally to the radio navigation field and may be applied to design of Global Navigation Satellite System (GNSS) Receivers, and particularly of GNSS GPS (USA), Galileo (EU), Glonass (Russia), Beidou (China), QZSS (Japan), IRNSS (India), and augmentation systems SBAS (different states). In the invention, the function of generating various PRN codes is repositioned from numerous tracking channels of multi-frequency, multi-constellation GNSS receiver to a shared PRN code generator unit, which serves in series all tracking channels. Such centralization of the PRN codes generation function enables a significant complexity reduction when the GNSS receiver includes a great number of tracking channels. A sufficient speed performance of the shared PRN code generator is achieved due to transfer of the PRN code lines from the shared PRN code generator to the receiver tracking channels via a dedicated parallel bus. Speed performance requirements to the dedicated parallel bus of the shared PRN code generator is kept moderate by a special number of symbols choice of PRN code lines thus providing uniformity of tracking channels requests to get new code lines. Use of several alternate means of PRN code lines forming: PRN Code ROM, PRN Code RAM, LFSR-based and one-shot PRN code generators—permits choosing optimal generation means for each type of GNSS signals.