6 results about "Link margin" patented technology

This invention relates to the field of electronic digital data processing and digital information transmission technology, specifically to a cloud-based intelligent data processing system for multiple nodes. The system includes a data preprocessing unit, a topology-aware scheduling engine, a graph neural network device, and a task execution unit. The data preprocessing unit extracts the temporal dependencies and logical associations of the input data stream to generate a directed acyclic graph (DAG). The topology-aware scheduling engine maps the graph to the physical network topology and calculates link bandwidth margin and congestion status. The graph neural network device jointly encodes node computational load and edge link status to output a task allocation strategy. The task execution unit schedules strongly dependent tasks to adjacent nodes with sufficient link margin and idle computing power according to the strategy, and dynamically migrates tasks to alternative path nodes based on link packet loss rate during execution. This invention reduces data transmission latency across switches in multi-node cascading and avoids node computing power idleness caused by local link congestion.

The application relates to a satellite link dynamic regulation device and method, which comprises an upper layer policy scheduler, a middle layer predictor and a lower layer real-time controller. The upper layer policy scheduler acquires a link state prediction result output by the middle layer predictor and a current link state reported by the lower layer real-time controller, selects an initial strategy, a dynamic regulation strategy or a recovery normal communication strategy according to a task demand, and issues a link parameter configuration instruction. The middle layer predictor uses a pre-trained random forest model to perform link state prediction based on an input feature set extracted in a historical sliding window. The lower layer real-time controller executes transmission power and modulation and coding scheme adjustment according to the instruction, performs emergency regulation when link margin abnormality occurs, and gradually adjusts to a normal communication mode after link recovery. Through the application, dynamic prediction and rapid self-adaptive regulation of a satellite link can be realized.

The data flow design method for flexible information processing of remote sensing constellations belongs to the field of spacecraft system overall design technology. This method first calculates the data rate of different types of data content, including: (1) calculating the original image data rate based on detector size, quantity, and imaging frame rate; (2) calculating the small area windowing data rate based on window size and windowing data frame rate; (3) calculating the target point's adjacent area slice data rate based on threshold crossing rate; and (4) calculating the target trajectory information data rate based on single target trajectory information and target quantity. Then, the data transmission content is flexibly configured, and information overlap strategies at different levels are formulated. This enables dual-satellite information fusion for target positioning and tracking tasks under different link transmission capacity constraints. For randomly triggered multi-target tracking tasks, the data transmission content is adaptively adjusted according to link margin, enabling dual-satellite positioning and tracking under different levels of information fusion processing conditions.

The application provides a UCIe-based flow control method, an artificial intelligence chip and a storage medium. The UCIe-based flow control method is suitable for a first core particle and a second core particle. The first core particle communicates with the second core particle. The first core particle comprises a receiving end data buffer. The UCIe-based flow control method comprises the following steps: reading, by the first core particle, an initial reserved link margin corresponding to the receiving end data buffer; reading, by the first core particle, a plurality of register configuration values and a plurality of reserved depths corresponding to the receiving end data buffer; obtaining, by the first core particle, a remaining available depth of the receiving end data buffer; and comparing, by the first core particle, the remaining available depth of the receiving end data buffer with the plurality of register configuration values to determine whether to select one of the plurality of reserved depths to calculate a current credit value.

The invention relates to a comprehensive optimization layout design and rapid verification method for a spacecraft antenna, and aims to solve the problems that in traditional spacecraft development, in order to verify the performance and layout rationality of various antennas, a whole device electromagnetic compatibility special test needs to be organized and implemented, so that the model development period is prolonged, and the test expenditure is high. The method provided by the invention comprises the following steps: [S1] carrying out frequency domain electromagnetic compatibility analysis according to the working frequency of a radio frequency single machine on a spacecraft, and finding out a potential interference frequency; (S2) carrying out isolation analysis among the antennas to obtain an isolation matrix among all transmitting and receiving antennas, and optimizing the antenna layout based on the matrix; (S3) carrying out directional diagram simulation on the antenna with obvious shielding in the beam view field; and (S4) calculating the link margin of the communication system according to the shielding directional diagram simulation result in combination with the on-orbit task attitude of the spacecraft, and if the task requirement is not met, carrying out iterative optimization adjustment on the antenna position and the installation angle until the radiation characteristic of the adjusted antenna meets the requirement.

The application relates to a free space optical communication link simulation analysis method and an interface system, and relates to the technical field of optical communication. In order to solve the problems in the prior art, the free space optical communication link simulation analysis method comprises the following steps: determining a link type, determining a transceiving terminal, configuring a transceiving terminal parameter, configuring a link parameter, calculating a transceiving terminal gain, calculating a pointing loss, calculating a channel transmission loss, calculating a link margin, and displaying a calculation result. A model covers deep space, near earth and inter-satellite link scenes, and link performance is quantitatively evaluated through a formula. The free space optical communication link simulation interface system comprises the following modules: link selection, data input, link budget, visual analysis and output, supports parameter configuration, real-time calculation and chart display, and can generate a standardized report. The scheme solves the problems of insufficient parameter coverage and poor interactivity of a traditional method, realizes the integration of "configuration-calculation-analysis", and improves link design optimization efficiency and user experience.