142 results about "Satellite payload" patented technology

The invention relates to the technical field of soil pollution identification, and discloses a soil heavy metal pollution identification system. A multispectral remote sensing sensing module of the system obtains surface reflectance data and soil in-situ spectral data through a satellite load and a vehicle-mounted mobile platform respectively, and the surface reflectance data and the soil in-situ spectral data are processed by a heterogeneous data fusion gateway to generate multiband spectral response signals. In the pollution risk assessment module, a spatial distribution analysis unit outputs a heavy metal spatial distribution map, a migration risk prediction unit generates a pollution migration probability cloud map in combination with meteorological and hydrological data, and a pollution threshold defining unit outputs a soil remediation safety threshold. In the treatment decision execution module, an in-situ remediation execution unit adjusts passivator injection parameters, a pollution source management and control unit regulates pollution source blocking equipment and collects monitoring signals, and a three-dimensional dynamic early warning platform generates a comprehensive pollution risk index. According to the system, the cooperative operation of soil heavy metal pollution identification, evaluation and treatment is realized.

The invention provides a satellite resource dynamic allocation method under a cloud-native hybrid cloud architecture, and the method comprises the steps: packaging satellite load resources and cloud resources through a containerization technology, so as to form a unified virtual resource pool; constructing a deep learning model, predicting resource demands of each beam coverage area in a future time period based on satellite task historical data and real-time demands, and generating a resource matching scheme; a reinforcement learning algorithm is adopted to dynamically adjust the beam radius, channel allocation and time slot scheduling so as to match the real-time load change of cloud resources; according to the method, a satellite and cloud digital twin model is constructed, a scheduling strategy is simulated and predicted based on a resource matching scheme through the satellite and cloud digital twin model, a resource state is mirrored in real time, and a strategy library is updated according to simulation feedback data of the satellite and cloud digital twin model, so that multi-satellite task automatic recombination is realized. The invention further provides a satellite resource dynamic allocation system under the cloud and native hybrid cloud architecture and a computer storage medium. According to the method, three-dimensional cooperation of dynamic resource pooling, intelligent prediction and elastic scheduling is realized, and the problem that satellite task response time, resource utilization rate and safety cannot be achieved at the same time can be effectively solved.

According to the satellite-borne software on-orbit reconstruction method and system supporting interface multiplexing, the working mode of a communication interface is expanded and designed, compatibility of normal data communication and a software reconstruction function is achieved, a set of complete load software on-orbit processing flow is provided, and the compatibility between the normal data communication and the software reconstruction function is improved. A load software reconstruction function is realized under the condition that large-scale development and modification are not carried out, so that satellite software in-orbit reconstruction is not limited to reconstruction of satellite service platform software. The method supports satellite-borne software parameter modification, dynamic library updating, software version replacement and multi-stage reconstruction, supports interface reuse, does not need a load to have a special code reconstruction channel, saves resources, simplifies design, and improves the flexibility, safety and reliability of the satellite load.

The invention discloses a rapid calculation method for the coverage rate of a constellation over-the-ground target area. Aiming at the problems that the number of satellites is large, the coverage rate calculation amount is large, and the calculation precision is low, the calculation method capable of rapidly positioning related satellites, rapidly calculating the coverage rate and keeping high precision is designed. Firstly, satellite orbit recursion is carried out, and satellites related to a target area are rapidly positioned based on a dichotomy. Secondly, calculating a beam coverage area of a satellite to the ground according to a satellite load type; and finally, abstracting the beam coverage area into a planar polygon, calculating an intersection of the satellite-to-ground beam coverage strip polygon and the ground target area polygon, and quickly calculating the coverage rate of the satellite to the ground target area. Aiming at the problems that the number of satellites is large, the coverage rate calculation amount is large, and the calculation precision is low, related satellites can be rapidly positioned, the coverage rate can be rapidly calculated, and the high precision is kept.

The present application discloses a communication device and a communication method. The communication method includes: determining whether there exists a current need to decide at least one target beam to determine whether to receive a satellite payload communication signal from a satellite payload by the at least one target beam; and determining whether a current satellite trajectory information is expired to decide whether to generate a current satellite trajectory information estimate. The user terminal controls its antenna to communicate with the satellite payload.

The invention relates to the technical field of system program storage of a controller, in particular to a satellite-borne dual-system program storage method and device capable of sharing a nonvolatile storage space. According to the technical scheme, the method comprises the following steps of: dividing a storage space of the nonvolatile memory into a first system program area, a second system program area and a sharing reserved area; the satellite-borne dual-system program storage can be upgraded independently, the program of the opposite side does not need to be compiled or adjusted again, the upgrading complexity and the testing cost are reduced, the dual-system program is solidified in a non-rewritable area, and the anti-radiation capacity is high; the shared reserved area is a dynamic allocation space during dual-system upgrading, storage waste caused by a traditional partition mode is avoided, and the requirement for flexibility of program version iteration is met; the first system directly runs in a non-volatile storage area, executable codes cannot be changed during system execution, and it is guaranteed that the satellite load basic communication function is not interrupted by the space irradiation environment; and the dual-system storage adapts to different hardware platforms.

The invention discloses a self-locking pulse instruction control startup and shutdown circuit for a satellite. The circuit comprises an auxiliary power supply sub-circuit, an input surge current suppression sub-circuit, a pulse signal startup / shutdown sub-circuit and a signal self-locking sub-circuit, the auxiliary power supply sub-circuit generates auxiliary power supply voltage and supplies the auxiliary power supply voltage to the signal self-locking sub-circuit; the input surge current suppression sub-circuit carries out surge current suppression on an external input primary bus power supply; the pulse signal startup sub-circuit receives an external pulse type startup instruction signal and transmits the external pulse type startup instruction signal to the signal self-locking sub-circuit; the pulse signal shutdown sub-circuit receives an external pulse type shutdown instruction signal and transmits the external pulse type shutdown instruction signal to the signal self-locking sub-circuit; and the signal self-locking sub-circuit receives the pulse-type power-on instruction signal or the pulse-type power-off instruction signal to realize a circuit self-locking function so as to control the on-off state of the input surge current suppression sub-circuit to the post-stage secondary power supply circuit. The on-off frequency is increased, the mechanical resistance is good, and the radiation-proof design of the satellite load secondary power supply single machine is facilitated.

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.

The invention provides an information interaction system and method for a satellite load and an on-satellite computer, and relates to the technical field of satellite communication, and the system comprises a satellite communication transmitting end and a satellite communication receiving end. The satellite communication sending end is used for filling field values in a plurality of fixed fields to obtain a request message, the plurality of fixed fields comprise a message type, a message serial number, a CRC field and a data field, and the data field comprises an effective data value and filling bytes used for supplementing the length of the field; the satellite communication receiving end is used for analyzing the received request message, filling a plurality of fixed fields with field values according to the message type of the request message to obtain a first response message representing that the request message is successfully responded or a second response message representing that the request message is failed to be responded, and sending the first response message and the second response message to the satellite communication receiving end; and returning the first response message or the second response message to the satellite communication sending end. In the instruction transmission process of the satellite load, a balance point is found between the reliability and the transmission speed.

The invention provides a beam hopping control method, electronic equipment, a storage medium and a program product, and the method comprises the steps that a satellite load receives a transparent forwarding signal sent by a base station and corresponding beam control information, the beam control information is sent earlier than the transparent forwarding signal, and the beam control information is used for the satellite load to carry out beam hopping control; the satellite load determines the effective moment of the beam control information according to the transparent forwarding signal and the local frame header moment of the satellite load, and the effective moment of the beam control information is synchronous with the transparent forwarding signal. Under the condition that the base station is not required to synchronously send the transparent forwarding signal and the corresponding beam control information, the satellite load can determine the effective moment of the beam control information according to the transparent forwarding signal sent by the base station and the local frame header moment of the satellite load, so that the effective moment of the beam control information is synchronized with the transparent forwarding signal; therefore, accurate and efficient control of the satellite load hopping beam can be realized.

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 provides a three-step-shaped load nested satellite configuration. The three-step-shaped load nested satellite configuration comprises a satellite configuration body, a satellite load, an antenna and a solar cell array, the front Z surface of the satellite configuration body is a ground surface, a first pair of ground steps, a second pair of ground steps and a third pair of ground steps are sequentially arranged on the ground surface, and the heights of the first pair of ground steps, the second pair of ground steps and the third pair of ground steps in the front Z direction are different; the front Z face of the first pair of ground steps, the front Z face of the second pair of ground steps and the front Z face of the third pair of ground steps are all used for installing satellite loads and / or antennas, and the solar cell arrays are located on the positive Y face and the negative Y face of the satellite configuration body. According to the invention, factors such as satellite envelope and centroid constraint, multi-load integration, multiple to-ground front ends and antennas are comprehensively considered, a three-step load nested satellite configuration is designed, the problems that a single satellite carries multiple large-size to-ground loads and the space of the antennas to the ground is insufficient are solved, and meanwhile, the envelope and centroid constraint of carrying is met.

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 invention belongs to the technical field of spacecraft solar wing sailboard drive, and provides a new sailboard drive mechanism, which includes an azimuth rotation mechanism and a pitch rotation mechanism symmetrically installed on both sides of the azimuth rotation mechanism. The present invention adopts a structural form of one azimuth axis and two pitch axes, and the two pitch axis motion mechanisms are symmetrically distributed on both sides of the azimuth axis motion mechanism. Under the premise of driving the solar wing sailboard to rotate, it is possible to realize the connection between the upper cabin and the lower cabin of the entire satellite payload and keep the main structure of the entire satellite relatively fixed. The azimuth rotation mechanism and the pitch rotation mechanism are both designed with effective mechanical limit structures to ensure the normal operation of the equipment. The azimuth rotation mechanism adopts a symmetrical installation method of the drive component, the angle measurement component and the middle column. The drive component drives the azimuth axis system and the angle measurement component to work through the transmission method of the active small gear → the middle large gear → the passive small gear. Not only is the transmission efficiency high, but also a large wiring space is left in the middle of the entire sailboard drive mechanism.

The invention provides an imaging satellite load and working mode decision-making method for silent target verification, and belongs to the technical field of earth observation satellite task planning and multi-satellite collaborative observation. The method comprises the following steps: firstly, predicting an escape area range of a target according to the silence moment and position of the target and the heading speed direction of the target, and calculating a top-crossing imaging satellite set in the escape area range in an escape time range; secondly, screening an imaging satellite set according to environment information such as day time and weather of a target predicted escape area; and finally, according to the breadth width constraint condition and the identification and discrimination capability constraint condition, determining a breadth width range and a resolution range, and determining specific satellite load parameters and working modes for imaging verification. The method can solve the load type and working mode optimization decision problem when the imaging reconnaissance satellite carries out silent target verification, and has the characteristics of advancement and practicability.

The present invention relates to a gridded intelligent fusion method and system for sea surface wind fields based on multi-source satellite payloads. The method comprises: constructing a deep neural network model and combining the advantages of the D-Matrix statistical algorithm for medium and low wind speed inversion to obtain MWRI sea surface wind speed products for the entire wind speed range; performing spatiotemporal matching processing between multi-source satellite data and an EC background field to obtain the data source for the fusion analysis period; combining the EC background field with the wind speed, divergence, vorticity, and second-order derivative terms of wind speed at each point in the fused wind field to obtain a cost function; obtaining the gradient terms of each cost function within the cost function based on the cost function and summing them to obtain the function gradient; and obtaining the final fused wind field based on the cost function and the function gradient. The present invention achieves efficient fusion of sea surface wind field data from multi-source satellite payloads, and can improve the accuracy and spatiotemporal resolution of sea surface wind field data.

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.

The invention relates to a remote sensing satellite observation result judgment method oriented to multi-factor influence. The method comprises the following steps: satellite load classification and task acquisition; satellite detection decision: according to the satellite task parameters, the observed target state, the environmental influence factors and the decision probability table, probability quantitative decision is carried out, and a satellite detection decision result is generated; data downloading judgment is carried out; target processing identification judgment: generating a target processing identification judgment result according to satellite and ground system parameters, a data transmission error rate, observed target characteristics and the like; and observation result generation: generating a target observation result according to a target identification processing result in combination with processing identification time, satellite load positioning errors and the like, and sending the target observation result to an information receiver. According to the method, the influence of different load types and different factors on target detection can be comprehensively considered, and meanwhile, a probability thinking method in the game theory is used for reference, so that rapid judgment of observation of the target by remote sensing satellites of different load types in a simulation deduction process is realized.

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.

The present invention discloses a method, device, medium, and system for autonomous power consumption optimization of a transit satellite payload. These methods, which pertain to the field of satellite technology, include an autonomous entry / exit decision process, which rapidly determines the entry / exit status of a satellite payload by calculating distance. This process adapts to the impact of changes in orbital altitude after a satellite orbit change. The transit payload autonomously calculates the satellite's exit and entry delays, and, in conjunction with the satellite's energy management unit, enables autonomous shutdown of the transit payload while it is operating outside the country and autonomous startup before entering the country, thus saving energy consumed by the transit payload during standby operation outside the country. The present invention can address the issue of satellite energy shortages and promote satellite development and application.

The application discloses a low-orbit satellite load autonomous operation system and relates to the technical field of satellite communication. The application adopts a three-layer modular architecture of a resource allocation layer, a load control layer and an application service layer, constructs a three-dimensional function system of "task autonomous decomposition-resource dynamic scheduling-fault prediction fault-tolerant processing", and realizes an "resource-control-application" end-to-end autonomous closed loop. The resource allocation layer optimizes resource scheduling through link management and route management, the load control layer realizes load independent control and fault self-recovery, and the application service layer completes task autonomous planning and whole-process execution. The application can improve communication capacity and link stability, significantly reduce ground operation and maintenance pressure, enhance system reliability and task flexibility, provide on-orbit verification data for load component selection and redundancy design, and is suitable for large-scale low-orbit constellation engineering practice.

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.

The present invention provides a universal satellite payload energy constraint verification method and apparatus. The method comprises: dividing the satellite operating time into different satellite sub-periods; configuring satellite payload action condition results according to each of the divided satellite sub-periods; and performing constraint item verification within each satellite sub-period based on the configured payload action condition results within each satellite sub-period. The universal satellite payload energy constraint verification method and apparatus provided by the present invention can complete satellite payload energy constraint verification using simple judgment logic.

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 present invention relates to the field of aerospace technology, and particularly relates to a satellite payload anti-radiation device made of an aluminum-tantalum metal composite material, comprising: an electronics box including a bottom plate and a main structure skeleton; side plates covering the outer side surfaces of the main structure skeleton; a top cover plate covering the top of the main structure skeleton; and a printed circuit board assembly installed inside the main structure skeleton; wherein the side plates and the top cover plate are respectively rolled from aluminum-tantalum composite laminated plates; and the bottom plate and the main structure skeleton of the electronics box are integrally formed by engraving and milling an aluminum ingot. The satellite payload anti-radiation device made of the aluminum-tantalum metal composite material provided by the present invention, compared with the satellite payload anti-radiation device made of traditional 2A12 aluminum alloy, can improve the anti-radiation ability while ensuring sufficient structural strength and good anti-mechanical ability under the condition of the same areal density.

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.