58 results about "Satellite payload" patented technology

The invention belongs to the technical field of spaceflight electronic integrated circuits, and particularly relates to a satellite load FPGA configuration data error correction method and system capable of resisting single event upset, in particular to a bit-symbol double-layer error correction method of RS decoding operator error correction based on finite field algebra cascading on the basis of two-out-of-three majority voting logic. Single-particle independent upset and multi-copy common-mode failure can be corrected at the same time, and the problem of traditional TMR error locking is solved. Meanwhile, when configuration data are written into a nonvolatile memory, a cross-sector space staggered and dispersed storage mechanism is introduced, symbols in the same RS code word are separated as far as possible in physical positions, and therefore aggregated physical damage is converted into dispersed symbol-level errors.

Methods, systems, and apparatus, including computer programs encoded on computer-storage media, for ground system techniques to support flexible reconfigurable satellite payload operation. In some implementations, a satellite communication network is managed to operate in a first configuration. The satellite communication network includes a satellite having a payload that enables dynamic reconfiguration of carriers within a beam. A reconfiguration event is detected, and in response, a second configuration is determined for the satellite communication network. The second configuration differs from the first configuration in at least one of a set of carriers used for the beams or an assignment of the carriers to gateways. The satellite network is managed to operate in the second configuration, including at least one of (i) changing to a second set of carriers for the beams of the satellite or (ii) changing to a second assignment of the carriers to the gateways.

The invention discloses a SysML-based satellite constellation architecture modeling method and system and a storage medium, and the method comprises the steps: analyzing a satellite constellation system strategy scene and a target described by a natural language, and building a satellite constellation architecture system layer model by using a SysML language; based on a system capability demand model in the constructed system layer model, building the system layer model by combining an RFLP (Restriction Fragment Length Polymorphism) method and a SysML (Systematic Modeling Language); analyzing designed functions in the constructed system layer model through a system forward design method, and respectively establishing a satellite platform model and a satellite load model by using an RFLP (Restriction Fragment Length Polymorphism) method and an SysML (SysML) modeling language; and extracting parameters from the constructed satellite parameter model, platform parameter model and load parameter model to carry out orbit design, and establishing a satellite orbit model by using an SysML language. According to the method, comprehensive and visual modeling of the satellite constellation from a macroscopic system to a microcosmic component is realized, the standardization, consistency and understandability of the model are greatly improved, and the modeling efficiency is improved.

A combined satellite and mobile weather forecasting system may include a satellite payload having a plurality of sensors configured to capture atmospheric and environmental data including atmospheric radiances and vertical soundings and a receiver for receiving data from other satellites. The satellite payload may also include a processing unit configured to condense the captured atmospheric and environmental data and the received data from other satellites into initialization data to generate a weather forecast. The satellite payload may include a transmission device configured to communicate with a mobile cellular device and to transmit the initialization data. The mobile cellular device may be configured to receive the initialization data from the transmission device of the satellite payload to generate the weather forecast using the initialization data.

The invention discloses a satellite vibration suppression system and method, a storage medium and a computer program product. The system comprises a passive vibration isolation module used for isolating first vibration generated by satellite vibration source equipment; the active suppression module is used for counteracting second vibration generated by the satellite vibration source equipment; wherein the second vibration is residual vibration except the first vibration isolated by the passive vibration isolation module, and the vibration frequency of the first vibration is higher than that of the second vibration. The technical problem that the effective load performance of a satellite is limited due to the fact that a traditional single passive or active vibration suppression method cannot effectively cover broadband vibration from high frequency to low frequency is solved.

This invention relates to a ground-based analog frequency conversion system for satellite payloads and its implementation method. The system includes: a filtering and coupling module for receiving high-frequency signals in the Q and V bands and splitting them into a coupling signal and a main signal, which are then transmitted to a detector module and a limiter, respectively. The detector module detects the power of the coupling signal at different temperatures and feeds it back to the control module. The limiter limits the maximum strength of the main signal to protect the low-noise amplifier (LNO). The LNO amplifies the main signal and reduces noise. A phase-locked loop (PLL) and frequency conversion module down-converts the high-frequency signal to an intermediate-frequency (IF) signal. An IF filtering and amplification module suppresses spurious interference and amplifies the IF signal. A temperature compensation module and a gain control module adjust the attenuation value to achieve temperature compensation and ensure that the IF output signal strength meets preset requirements. All modules are integrated using micro-assembly technology. This system can reduce the power consumption and cost of satellite launch and communication.

The present application relates to a kind of satellite load observation attitude control and data transmission, orbit control autonomous intelligent planning system and method, the system includes mission guide module, attitude control module, orbit control module and data transmission module;The attitude control module includes several thrusters for satellite attitude control, the orbit control module is used for satellite autonomous orbit control calculation, and carries out satellite orbit control, the data transmission module is used for satellite autonomous data transmission calculation, and satellite data is transmitted to ground;The mission guide module is in system control core, executes load observation task implementation strategy, according to priority reasonably arrange satellite's working time sequence, so that the satellite is intelligently switched between attitude control and data transmission to ground, orbit control, controls satellite autonomous intelligent operation in orbit.Autonomous intelligent planning, autonomous data transmission calculation, autonomous orbit control calculation are beneficial.

The invention discloses a satellite load design method based on communication demand space-time characteristic analysis. The method comprises the following steps: carrying out space-time characteristic analysis on communication demands of different industries; integrating the time-space characteristic analysis results of the communication requirements of the industries to obtain the time-space characteristic analysis result of the overall communication requirements; based on the communication service providing capability of the existing satellite and the time-space characteristic analysis result of the overall communication demand, determining an area in which the communication demand is not satisfied; determining the number of satellites to be designed according to the total number of unsatisfied communication requirements; and determining the beam coverage range, beam coverage intensity and beam coverage shape of the to-be-designed satellite according to the area and the unsatisfied degree of the communication demand thereof. By applying the method, the rationality and effectiveness of a satellite load design scheme can be further improved, so that the satellite to be designed can better meet communication requirements.

A method for setting a calibration signal power, the method including: transmitting a calibration-modulated wave (CMW) signal at a frequency slot; receiving a power measurement of the CMW signal; calculating a calibration correction factor for the frequency slot based on the power measurement; and adjusting a transmission power of the CMW signal at the frequency slot based on the calibration correction factor. A method for switching over a control channel and a voice channel from an old sub-band to a new-sub-band, the method including: switching over control channel and voice channel among multiple GW components and satellite payload; predicting switchover time to reduce control channel and voice channel outage time during switchover.

This invention provides a method, apparatus, electronic device, and storage medium for calculating cloud judgment parameters. The method includes: determining the satellite position vector, solar vector, and satellite attitude matrix in the cloud judgment time inertial frame based on the time interval between the current time and the cloud judgment time; calculating the position information of the ground imaging point corresponding to each pixel after the time interval based on the satellite payload installation information, pixel line-of-sight information, and the satellite position vector and satellite attitude matrix in the cloud judgment time inertial frame; and calculating the cloud judgment parameters for each ground imaging point based on the position information of the ground imaging point corresponding to each pixel after the time interval and the solar vector in the cloud judgment time inertial frame. The cloud judgment parameters include at least one of the following: satellite zenith angle, solar zenith angle, geographic latitude and longitude, and relative azimuth angle. This solution can provide cloud judgment parameters for the cloud judgment process of satellite payloads.

This invention discloses a fault feedback and planning strategy iterative repair method for high-orbit satellite collaborative mission execution. This method determines whether a fault warning is triggered based on fused features and dynamic thresholds. A closed-loop framework of "fault diagnosis - impact assessment - planning correction - verification iteration" is constructed. The diagnosis stage employs a hybrid diagnostic method combining deep learning and rule-based reasoning. The impact assessment stage establishes a quantitative assessment model based on task priority and resource reserves to determine the degree of fault impact. The planning correction stage introduces a dynamic resource reallocation algorithm to adjust the satellite payload operating mode and inter-satellite link topology based on the assessment results. The verification iteration stage uses digital twin technology to construct a simulation environment to verify the effectiveness of the correction strategy. Furthermore, an iterative optimization mechanism for the strategy library based on case-based reasoning and reinforcement learning is established. The strategy library is iteratively optimized using reinforcement learning algorithms to form an adaptive fault response strategy library, thereby improving the efficiency of the system's anti-interference capability evolution.

The application discloses a garbage collection method and device of a satellite-borne solid state disk, a storage medium and equipment, and relates to the technical field of satellite remote sensing. The method comprises the following steps: acquiring the directly writable capacity, the to-be-recovered capacity and the capacity management threshold of the solid state disk of the satellite payload after the execution of the current task, and determining whether the solid state disk meets the capacity requirement; if the capacity requirement is not met, data is deleted, and the to-be-recovered capacity is re-acquired; according to the re-acquired to-be-recovered capacity, the garbage collection operation of the solid state disk is controlled to be executed by the satellite payload, and it is determined whether the garbage collection operation of the solid state disk is overdue; if the garbage collection operation is overdue, first telemetry information is sent to a ground terminal, wherein the ground terminal is used to determine whether the garbage collection operation is overdue and affects the execution of the next task according to the first telemetry information; if the garbage collection operation is overdue and affects the execution of the next task, it is determined that the garbage collection operation of the solid state disk is executed before the execution of the next task. The application controls the satellite-borne solid state disk to execute the garbage collection deterministically.

The application discloses a satellite load installation and adjustment method based on photogrammetry and facing flexible support, and belongs to the technical field of spaceflight assembly. The method comprises the following steps: S1, flexible support pre-compression simulation; S2, installing flexible support; S3, photogrammetry preparation; S4, performing photogrammetry; S5, generating measurement results; S6, post-processing of the measurement results; and S7, targeted installation and adjustment. The method has the advantages that the measured object is not contacted in the measurement process, and the flexible support is not deformed; the measurement speed is high, the precision is high, the operation is convenient, the relative distance of each measurement point relative to the reference plane can be obtained, the flexible support can be adjusted according to the measurement results, and the surface precision of the optical load connected with the flexible support is effectively improved.

The application discloses a satellite quantum communication system and method based on hour-level quantum storage, wherein the system comprises: a quantum communication satellite payload end for generating entangled photon pairs, which are independently sent to corresponding satellite ground stations; two satellite ground stations for obtaining symmetric keys from the entangled photon pairs, and performing information encryption and quantum communication by using the symmetric keys; specifically, the weather is monitored, and it is judged whether the entangled photons can effectively pass through; if yes, the transit satellite is tracked, the entangled photons are received and measured by a measurement module to obtain the symmetric keys; if not, a UAV is started, the entangled photons are received and stored in the hour-level quantum storage module, after the satellite transits, the UAV returns to the satellite ground station, the entangled information in the quantum storage is read and measured to obtain the symmetric keys. The application can effectively improve the real-time performance and security of quantum key distribution.

The application provides a kind of imaging satellite load and working mode decision method for silent target investigation, belongs to the technical field of earth observation satellite mission planning, multi-satellite cooperative observation.The method first estimates the target escape area range according to the time, position and target heading speed direction of the target silence, calculates the over-the-top imaging satellite set in the escape time range, the escape area range;Second, according to the time, weather and other environmental information of the target predicted escape area, the imaging satellite set is screened;Finally, according to the width and length constraint conditions and identification ability constraint conditions, the width and length range and resolution range are determined, and the specific satellite load parameters and working mode for imaging investigation are determined.The method can solve the problem of load type and working mode optimization decision of imaging reconnaissance satellite for silent target investigation, and has the characteristics of advancement and practicality.

The application belongs to the technical field of aerospace electronic integrated circuits, and particularly relates to a satellite load FPGA configuration data error correction method and system resisting single event upsets, a double-layer error correction method of "bit-symbol" based on RS decoding operator error correction of a finite field algebra on the basis of a "two out of three" majority voting logic, which can correct single particle independent upsets and multiple copy common mode failures at the same time, and solve the traditional TMR error locking problem. Meanwhile, when configuration data is written into a non-volatile memory, a cross-sector spatial staggered dispersion storage mechanism is introduced, so that the symbols in the same RS code word are separated as much as possible in the physical position, so as to convert the aggregation physical damage into dispersed symbol level errors.

The present disclosure relates to the technical field of spacecraft load, in particular to a satellite load efficiency evaluation method, device, equipment and readable storage medium, the method comprises: calculating the signal-to-clutter ratio of a target in each frame of a sequence image of a target life cycle under different cloud parameters, counting the proportion of the signal-to-clutter ratio of the target in the target life cycle exceeding a threshold value as target detection availability, analyzing the analytical relationship between the target detection availability and different cloud parameters, establishing an availability model, and evaluating satellite load efficiency by using the availability model, which can effectively shorten the efficiency evaluation time of typical satellite loads in the field of remote sensing.

This disclosure relates to a flat-panel satellite, including a cabin. The cabin is generally a flat rectangular body. The cabin includes a first, second, third, fourth, fifth, and sixth cabin panel that are detachably arranged to form a compartment. Different functional systems are respectively installed on the first, second, third, fourth, fifth, and sixth cabin panels. These functional systems include: a payload antenna system, with the payload antenna integrated on the outer side of the first cabin panel; and a platform control system, located inside the cabin and integrated on the inner side of the second cabin panel. This disclosure eliminates the complex support structure of traditional flat-panel satellite payload antennas by making the cabin panels detachably connected and integrating the payload antenna onto one of the cabin panels. The modular design reduces the integration difficulty of the flat-panel satellite, shortens the production cycle, and reduces testing workload and costs.

The application provides a kind of high-reliability parallel running method of aerospace SPARC multi-core processor, and the multi-core processor chip includes at least two processor cores, and all processor cores of the multi-core processor chip are independently running and performing inter-core notification and synchronization;Multi-processor state register monitors the running state of processor core and activates multi-core running.The application independently deploys multiple software modules on multiple processor cores for parallel computing, breaking through the traditional aerospace single-core processor software design mode, so that the software can adapt to large-scale software, multi-module integration, high real-time and high reliability requirements.At the same time, the application expands the supporting technology related to aerospace multi-core processor, including multi-core loading, inter-core interrupt, peripheral management, data sharing area, inter-core dynamic monitoring, etc., which has great value for the development of comprehensive electronic, integrated control and health management aerospace software in the field of satellite payload software.

The embodiment of the application discloses a satellite network data sending method. The method comprises the following steps: acquiring satellite payload data packets; establishing data frames corresponding to the satellite payload data packets, wherein the data frames comprise first signal-to-noise ratio data frames, second signal-to-noise ratio data frames and third signal-to-noise ratio data frames; sending the data frames to a receiving end; and processing the data frames to obtain the satellite payload data packets. The working point ranges of the first signal-to-noise ratio data frames, the second signal-to-noise ratio data frames and the third signal-to-noise ratio data frames are greater than or equal to-15 dB and less than-10 dB, greater than or equal to-10 dB and less than 0 dB, and greater than or equal to 0 dB and less than 20 dB. The first signal-to-noise ratio data frames comprise a plurality of sub-first signal-to-noise ratio data frames, and the frame length of the sub-first signal-to-noise ratio data frames is the same as that of the second signal-to-noise ratio data frames and the third signal-to-noise ratio data frames. The unique code field of the frame header of the first signal-to-noise ratio data frames, the unique code field of the frame header of the second signal-to-noise ratio data frames and the unique code field of the frame header of the third signal-to-noise ratio data frames are selected from a pseudo-random sequence set.

The application provides a satellite payload cabin moment of inertia measurement method and system based on a moment measurement device, the method comprising placing a satellite in an assembled state on the moment measurement device, rotating the payload cabin and collecting the rotational torque corresponding to the rotation of the payload cabin during the sliding stop phase, obtaining the real-time angular acceleration of the payload cabin, and calculating the moment of inertia in combination with the relationship between the rotational torque and the real-time angular acceleration. The system comprises a moment measurement module, a rotational speed collection module and a data calculation module, which are respectively used for bearing the satellite and measuring the rotational torque, measuring the real-time rotational angular velocity, calculating the angular acceleration and the moment of inertia. The method and system do not need to disassemble the payload cabin, are simple, efficient and high-precision, can avoid the influence of disassembly on the assembly precision of components, and are suitable for the moment of inertia measurement of satellite payload cabins and other single bodies, single machines or systems containing rotating components.

This invention provides an automated testing and interpretation system and method for the downlink radio frequency performance of regenerative processing payloads on communication satellites, including a hardware platform and a control unit. The hardware platform is used to construct a satellite-to-ground radio frequency link and supports remote control. The control unit carries main control software to control the hardware platform to perform the following functions: loading and executing predefined test sequences to initiate the test process; sending remote control commands to set the satellite payload status via power supply control equipment or requesting command permissions from the satellite platform; receiving and parsing satellite telemetry to confirm whether the status meets the requirements; remotely controlling general-purpose test instruments to perform automatic testing, acquiring test data, and automatically interpreting and recording it based on predefined templates; and automatically storing remote control commands, telemetry data, and test data in a time sequence to a database. Thus, this invention achieves one-click automated testing and interpretation of the downlink radio frequency performance of satellite processing payloads, improving efficiency, reducing cost and error rate, and possessing versatility and scalability.

The invention provides a dynamic simulation method for a ground equipment pointing satellite load angle, and belongs to the field of spaceflight measurement and control. The method comprises the following steps: calculating an expected azimuth angle and a pitch angle of a ground device pointing to a to-be-simulated satellite; setting geodetic system coordinates of the initial high point and the height of the initial high point relative to the movement horizontal plane of ground equipment, and fixing a satellite load at the initial high point; calculating northeast sky system coordinates of the ground equipment relative to the satellite load under the condition of meeting the movement speed and range limitation; and converting the northeast sky system coordinate of the ground equipment relative to the satellite load into a geodetic system coordinate, and obtaining a motion track of the ground equipment. According to the invention, the satellite load static arrangement avoids the limitation of the mounting capability and endurance of the unmanned aerial vehicle, and the application scene is expanded; the motion trail of ground equipment is calculated in real time based on geometric constraints, the azimuth angle and pitch angle pointing to a fixed load are ensured to be consistent with the expected angle of an on-orbit satellite, and the limitation that static simulation cannot reflect the dynamic change of the angle is broken through.

The application discloses a kind of spaceborne high-interception-probability high-precision positioning system and method, system includes ultra-wideband wide-angle scanning main array, multiple ultra-wideband reconfigurable digitization auxiliary array, super large instantaneous bandwidth measurement module, wideband frequency conversion and high-resolution acquisition module, reconfiguration control module and high-precision positioning processing module.The application realizes S~Ku instantaneous full-band reconnaissance processing and high-precision positioning, and greatly reduces the burden of transmission bus and computing processing resource.The application is suitable for comprehensive multi-functional software-defined satellite payload system, realizes ultra-large instantaneous bandwidth and super-high-interception-probability reception in electronic reconnaissance task, and carries out high-precision direction finding positioning to target.Effective reduction of the transmission bus pressure and computational complexity of back-end high-performance processing equipment improves C-SWaP performance, and has important military significance and economic value.

The invention discloses a method, a device and equipment for judging the application technology maturity of an ocean microwave product, relates to the technical field of ocean microwave remote sensing satellites, and is used for solving the problem that the application technology maturity of the ocean microwave product cannot be accurately and effectively judged in the prior art. Comprising the following steps: establishing a plurality of application technology maturity levels of the marine microwave product; setting inspection elements and weight factors of each maturity level in the plurality of maturity levels; calculating an application technology maturity index based on the inspection elements and the weight factors, and calculating to obtain a target maturity index through a weighted summation mode; and determining the target application technology maturity of the marine microwave product according to a comparison result of the target maturity index and a preset threshold value, and judging the development level of the application technology by using a dynamic threshold value. According to the technical scheme provided by the invention, the application technology maturity of the marine microwave product can be accurately and effectively judged, and a basis is provided for design and index optimization of a satellite payload.

The application provides a low-orbit constellation system-oriented system model construction method and system simulation method, and belongs to the field of low-orbit constellation system simulation and performance evaluation.The construction method performs lightweight simulation modeling on functional entities of a space section, a ground section, an application section and an environment section, the model constructed by the space section comprises a constellation configuration model, an attitude and orbit control subsystem model and a satellite payload model, the ground section comprises a main gateway station model and a secondary gateway station model, a large-scale terminal model is constructed in the application section, the environment section comprises a satellite-ground microwave channel submodel and an inter-satellite laser channel submodel, and model interaction design is performed to form an integrated model architecture of satellite-ground integration.The application guarantees the modeling accuracy of functional entities, simultaneously meets the lightweight demand of simulation modeling, reduces the complexity of system modeling, balances the relationship between model accuracy and lightweight, and simulates, verifies and evaluates the correctness, rationality and effectiveness of the architecture design of the constellation system.

Non-terrestrial cellular communication infrastructure. This infrastructure (1) comprises: an IP / MPLS transport network (3) including a satellite network (20) and a terrestrial network, connected by a feed link; a 5G NTN network (2), including a base station disaggregated on either side of an F1 interface, associating an edge unit (RU, DU) in the payload of a satellite (21) connected to an edge router (210) of the satellite network, and a ground unit (CU) connected to a ground router (260) of the terrestrial network; the transport network establishing a path between the ground router and the edge router; and a control center (50) for managing a configuration of transport network resources. Figure for the abstract: Figure 2

The application provides a method for quickly positioning a beam pointing direction of a communication satellite antenna in a production line, comprising the following steps: selecting three non-collinear observation points in the space in the approximate main lobe area of a satellite payload antenna, using a measurement horn test to obtain three polar coordinates and corresponding gains; substituting the data into an equation to solve a satellite payload antenna beam pointing angle; using the solved pointing angle to calculate an amplitude error; if the calculation amplitude error accuracy is not within a set error range, continuously narrowing the area within the last collected area range, collecting angle and gain data of three non-collinear observation points, and repeatedly calculating the pointing angle until the accuracy requirement is met. The method has the advantages that the collected area can be continuously narrowed for iterative correction, and the technical problems of long iteration time and poor batch consistency of the existing algorithm can be solved.

This invention provides a vehicle-mounted wireless communication performance testing device for low-Earth orbit satellite payloads, belonging to the field of communication performance testing technology. It solves the technical problem that existing signal detection devices have complex installation methods, reducing installation efficiency. The device includes a mounting base, a first limiting plate slidably connected to one side of the mounting base, and a second limiting plate slidably connected to the other side of the mounting base. A communication signal detector is placed on the mounting base. A top encapsulation plate is rotatably connected to the top of the first limiting plate, and a limiting component is provided at the top of the second limiting plate. One end of the top encapsulation plate engages with the limiting component for limiting. This invention improves the installation efficiency of the testing device and allows for adjustments based on the size and model of the communication signal detector, thus improving adaptability.

The invention relates to a long-distance retrograde orbit satellite load layout structure and a satellite assembly. The long-distance retrograde orbit satellite load layout structure comprises a satellite body, a satellite-borne atomic clock, a satellite-ground or inter-satellite link measurement and communication load, a space observation camera, a laser communication test load, a laser ranging time difference measurement load and a space scientific detection load, wherein the satellite-borne atomic clock is mounted on the inner side surface of the satellite body in a heat conduction manner; the satellite-ground or inter-satellite link measurement and communication load comprises an in-satellite transmitting assembly and an out-satellite antenna, the in-satellite transmitting assembly is installed on the inner side face of the satellite body in a heat conduction mode, and the out-satellite antenna is installed on the outer side face of the satellite body in a heat insulation mode. The space observation camera is installed on the outer side of the satellite body. The laser communication test loads are installed on the inner side and the outer side of the satellite body. The laser ranging time difference measurement load is thermally mounted on the inner side surface of the satellite body; space scientific detection loads are installed on the inner side face and the outer side face of the satellite body. And through reasonable load layout, low-energy-consumption orbit injection of the DRO satellite can be realized.