42 results about "Mission management" patented technology

The invention provides a multi-satellite parallel data transmission resource scheduling method based on a genetic algorithm, and belongs to the technical field of ground task management and control of spaceflight earth observation satellites. The method comprises the steps that historical data transmission resource use rules of all satellites are mined, and data transmission resource use rule models of all the satellites are established; in a data transmission resource scheduling process, each satellite generates a corresponding resource demand set according to a data transmission timeliness requirement, a priority degree and a data transmission resource use rule model of an important task, conflict resolution is carried out on a conflicting resource use demand set by utilizing a genetic algorithm, and a data transmission resource scheduling result is obtained through a multi-round parallel resource matching and conflict resolution process. The multi-satellite data transmission resource planning scheme is obtained, large-scale satellite data transmission resource scheduling is achieved, the large-scale remote sensing satellite group resource use efficiency is effectively improved, and the implementation rate of reconnaissance tasks is improved. According to the method, the data transmission resource distribution income among multiple satellites can be comprehensively planned, and the intelligent scheduling capability level of large-scale remote sensing satellite group resources can be effectively improved.

The invention relates to the technical field of deep sea test task management, in particular to a deep sea test task scheduling and management method based on multi-platform collaboration, comprising the following steps: S1, generating an environmental adaptability task priority list; s2, generating a multi-platform interface configuration scheme based on the priority list in S1; s3, constructing a space-time conflict probability model, and outputting an obstacle avoidance path and a resource allocation strategy; s4, generating a data link topological graph; and S5, calculating a deep sea test efficiency index, and optimizing a subsequent test task priority list. According to the method, intelligent scheduling and efficient execution of deep sea test tasks are realized through task priority dynamic optimization, space-time conflict prediction, data link adaptive regulation and control and efficiency index feedback optimization, and the stability of multi-platform collaborative operation, the communication reliability and the resource utilization rate are improved.

The invention provides a task processing method of a low-orbit quantum satellite and a satellite task management system. The method comprises the following steps: a task center performs task comprehensive sorting according to a task trigger type of a first key generation task corresponding to each ground station and a task trigger type of at least one second key generation task to obtain a task sorting result, and receives task arrangement information sent by an operation and control center, and performing instruction conversion on the task arrangement information to obtain control instructions corresponding to the ground stations, and sending the control instructions to the corresponding ground stations, so that the ground stations communicate with the low-orbit quantum satellites according to execution time indicated in the control instructions and generate quantum keys. According to the invention, two different triggering mechanisms based on the business key demand and based on the key pool stock are provided, the emergency business demand peak is quickly responded while the daily key supplement is satisfied, and different key demands faced by different ground stations are solved by ensuring the key to be updated and supplemented in time.

The invention relates to a satellite task management method and system and a computer readable medium. The method comprises the steps that an on-satellite storage instruction of a satellite is updated according to a first management and control instruction; combining at least one task sub-module stored by the satellite into a task template according to the on-satellite storage instruction; inserting the task template into a corresponding position of the task queue according to the task priority and / or the task execution time of the task template; traversing a task target from a target library pre-stored in the satellite, and executing the task in the task queue according to the task target; in the process of executing the task in the task queue, in response to the received second management and control instruction, modifying task parameters of the task according to the second management and control instruction; monitoring the operation condition of the load single machine on the satellite, and managing tasks in the task queue corresponding to the load single machine according to the operation condition; wherein the first management and control instruction and the second management and control instruction are transmitted from the ground uplink and / or between satellites. The intelligent degree of the satellite task management mode is improved.

The embodiment of the invention provides a low-orbit giant constellation resource management and control method, device and equipment and a medium, and relates to the technical field of low-orbit giant constellation system architecture design. The method comprises the following steps: dividing a constellation operation sky domain into a plurality of sky domain partitions according to a C-60 molecular structure, dividing satellites in each satellite cluster into a main satellite and a plurality of auxiliary satellites at each operation moment, generating a satellite cluster division table of each satellite, and formulating a management rule base, and each satellite operates in orbit according to the stored management rule base and the satellite cluster division table. A low-orbit giant constellation is uniformly divided into a plurality of satellite clusters without omission according to a C-60 molecular structure, so that the pressure of a ground centralized management and control center is relieved, constellation resource management and control and task management distributed deployment are realized, meanwhile, a satellite cluster division table is determined, the in-orbit calculation amount of a satellite is reduced, the task response speed is increased, and the task management efficiency is improved. The method is suitable for the satellite detection task of the low-orbit giant constellation on the time-sensitive moving target.

The invention relates to an emergency response-oriented multi-satellite collaborative observation task distributed planning method, which comprises the following steps of: modeling a plurality of satellites into an intelligent agent with an autonomous decision-making capability, and realizing task broadcasting, bidding and confirmation between a task manager and an executor by adopting an improved contract network protocol. By constructing a multi-factor dynamic evaluation function and comprehensively considering the task emergency degree, the observation feasibility, the resource state and the task conflict probability, intelligent bidding distribution of the observation sub-tasks is realized. A task conflict game diagram mechanism is introduced, the problem of multi-satellite bidding conflict is effectively solved, and the task scheduling fairness and the resource utilization rate are improved. The method has communication topology sensing and local task re-planning functions, supports adaptive recovery under the condition of node failure or communication interruption, and improves the system robustness and the task completion rate. The method has the advantages of being fast in task response, high in scheduling efficiency, high in distributed autonomy and the like, and is suitable for collaborative planning requirements of a multi-satellite system in emergency response.

Systems, devices, methods, and computer-readable media for space vehicle sensor management. A method includes receiving, at a mission operations center (MOC), respective regional requests from respective regional schedulers, the respective regional requests indicating mission windows (MWs) and corresponding sensors to be operated in associated MWs, receiving, at the MOC, respective sensor plans from corresponding space vehicle operation centers (SVOCs), each sensor plan indicating MWs for which a given sensor is unavailable, generating, based on the regional requests and the sensor plans, a MW apportionment for each regional scheduler, the MW apportionment indicating MWs and corresponding sensors that a user associated with the regional scheduler has authorization to command the sensor, and providing the MW apportionment for the regional scheduler to the regional scheduler.

A system includes avionics line-replaceable units (LRUs); a mission manager including application programming interfaces (API); a processing device; and a memory storing one or more machine readable instructions causing the system to: communicatively couple the mission manager to external avionics services via a data gateway to receive updated mission conditions at the mission manager; register one of the avionics LRUs with one of the mission manager APIs; receive, at the mission manager, updated mission conditions from the external avionics services via the data gateway; provide one or more of the one or more updated mission conditions to the registered avionics LRU based on one or more of an updated mission plan and an unexpected update to the mission condition; and control one or more aircraft systems based on one or more of the updated mission plan and the unexpected update to the mission condition.

A mission management compute device is configured to assign each mission from a plurality of missions to an operator from a plurality of operators. Each operator from the plurality of operators is uniquely associated with at least two unmanned vehicles from a plurality of unmanned vehicles. A plurality of ground control compute devices is operatively coupled to the mission management compute device. Each ground control compute device from the plurality of ground control compute devices is uniquely associated with an operator from the plurality of operators and the at least two unmanned vehicles uniquely associated with that operator. The mission management compute device is configured to automatically determine that an operator from the plurality of operators cannot perform a mission from the at least two missions associated with that operator and automatically reassign the mission that cannot be performed by the operator in response.

The present invention discloses a quadrotor unmanned aerial vehicle (UAV) obstacle avoidance system based on adaptive nonlinear model predictive control, the system comprising a ground mission management system, a sensing system, an adaptive nonlinear model predictive obstacle avoidance system, and a power system. The present invention also discloses a quadrotor unmanned aerial vehicle (UAV) obstacle avoidance method based on adaptive nonlinear model predictive control, the method comprising the following steps: step 1, obtaining UAV target trajectory information and obstacle information; step 2, obtaining the UAV's real-time status; step 3, obtaining control instructions based on the information in steps 1 and 2. The quadrotor unmanned aerial vehicle (UAV) obstacle avoidance method based on adaptive nonlinear model predictive control provided by the present invention can simultaneously solve the two major problems of fault handling and obstacle avoidance in quadrotor unmanned aerial vehicle flight control, and significantly improve flight performance.

This application discloses a method, apparatus, device, and medium for testing and verifying a mission management computer for unmanned aerial vehicles (UAVs), relating to the field of testing and verification technology. The method includes: loading an embedded binary program into the storage space of a first simulation node; after the testing and verification system is started and initialized based on the embedded binary program, acquiring simulation stimulus data through a physical entity node and transmitting it to the first simulation node via a target communication middleware; using the first simulation node to drive the embedded binary program to generate UAV control commands based on the simulation stimulus data, and sending them to a second simulation node via the target communication middleware, so that the second simulation node can feed back simulation status data of the target UAV to the first simulation node; processing the data through the first simulation node to obtain new simulation stimulus data, and then jumping to the step of driving the embedded binary program to generate UAV control commands, until the program execution is complete, thereby ending the testing and verification of the mission management computer.

Described provides a device, method, apparatus and readable storage medium for control function relocation, where the apparatus according to an embodiment includes processor coupled with memory storing computer program codes, for causing the first device to: determine, for a first task performed by a first task control function (TCF), that the first TCF to be replaced by a second TCF, wherein the first TCF and the second TCF are managed by mission management (MM); and send, to the first TCF, a first synchronization request comprising information of the second TCF, for requesting the first TCF to send task execution (TE) information to the second TCF, wherein the TE information comprises execution information of the first task performed by the first TCF. As a result, relocation from o-TCF to n-TCF is realized.

1. The name of the design product: the space mission management graphical user interface of electronic equipment. 2. The use of the design product: for electronic equipment. 3. The design points of the design product: the interface content of the graphical user interface. 4. The picture or photo that best shows the design points: the front view. 5. The use of the graphical user interface: the design graphical user interface is used for space mission management. 6. Other circumstances that need to be explained: the "x" in the front view interface represents replaceable text and / or numbers.

We propose a transport task management system that can complete priority transport tasks in the shortest possible time and execute transport tasks efficiently. [Solution] When a priority transport task arises, from among the robots 41-44 currently executing transport tasks with lower priority than the priority transport task, and the robots 41-44 that are on standby, the robot 41-44 that can reach the source of the priority transport task (manufacturing location 31-34) in the shortest time while being able to transport the items of the priority transport task is selected, and the priority task is assigned to this robot 41-44. Then, information about the priority transport task is output to the assigned robot 41-44. This minimizes the time required to complete the priority transport task and allows for efficient operation and management of the robots 41-44 performing the transport tasks.

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.

A high-fidelity visual simulation system and method for landmark navigation in deep space exploration. The high-fidelity visual simulation system includes a mission management and visualization subsystem, a 3D mesh editing and optimization subsystem, an environment configuration and update subsystem, a visual image rendering subsystem, and a data input / output subsystem. It is applied in the preliminary design and verification process of the deep space exploration visual navigation system, can provide high-quality simulation images for the whole stage, realize precise pinpoint landing in Mars exploration through the obtained simulation images, can render images of most deep space celestial bodies, and has expandability and adaptability to various deep space exploration tasks.

A refuse collection system is provided. The refuse collection system includes refuse collection drones and a service manager. The refuse collection drones are configured to retrieve refuse from a customer and deposit the refuse in a refuse depot. The service manager includes processing circuitry. The processing configured to obtain refuse production data associated with the customer. The processing circuitry is further configured to create, based on the refuse production data, a model of refuse collection requirements of the customer. The processing circuitry is further configured to predict, based on the model, a predicted collection date and time at which the customer will next require refuse collection. The processing circuitry is further configured to dispatch at least one of the refuse collection drones to collect refuse from the customer based on the predicted collection date and time.

A mission management compute device is configured to assign each mission from a plurality of missions to an operator from a plurality of operators. Each operator from the plurality of operators is uniquely associated with at least two unmanned vehicles from a plurality of unmanned vehicles. A plurality of ground control compute devices is operatively coupled to the mission management compute device. Each ground control compute device from the plurality of ground control compute devices is uniquely associated with an operator from the plurality of operators and the at least two unmanned vehicles uniquely associated with that operator. The mission management compute device is configured to automatically determine that an operator from the plurality of operators cannot perform a mission from the at least two missions associated with that operator and automatically reassign the mission that cannot be performed by the operator in response.

The invention provides an unmanned aerial vehicle deployment honeycomb system, and relates to the technical field of unmanned aerial vehicle transceiving. S1, a basic adaptation module, wherein the basic adaptation module comprises an unmanned aerial vehicle storage assembly and an unmanned aerial vehicle automatic charging assembly; s2, a flight control module, wherein the flight control module comprises an unmanned aerial vehicle take-off and landing guide assembly, a path planning assembly and a trajectory tracking assembly; s3, a data processing module, wherein the data processing module comprises a task management component, a data transmission component and an information real-time processing component; data of the position of the unmanned aerial vehicle is transmitted to the trajectory tracking assembly through the visual identification positioning device and the positioning system, the trajectory tracking assembly obtains various data of the unmanned aerial vehicle in flight in real time through the kinematics parameter acquisition unit, and when path deviation occurs, deviation signals are fed back to the path planning assembly, and the path planning assembly plans the path. The trajectory tracking assembly and the path planning are matched with each other, so that closed-loop cooperative operation from deviation detection to path correction to tracking execution can be completed.

A storage apparatus stores existing data including data relating to management of an instrument and data on actual records of the instrument, information on path structure of the existing data, mission information relating to a task in the facility operation, and information on the path structure of the mission information. An arithmetic operation apparatus extracts information on data meanings of terms contained in the existing data based on the existing data and the path structure of the existing data, and generates information of the degree of association between the plurality of terms. The arithmetic operation apparatus generates mission management information based on mission information, the path structure of the mission information, and the information on the degree of association between the terms, the mission management information including information on a meaning of each of a plurality of tasks relating to facility operation and chronological information on the plurality of tasks.

The present application relates to systems and methods for processing function selection. In an example method, a mission management function obtains a list of processing function identifiers (IDs) indicative of at least one processing function connect to a service controller, the mission management function selects one or more selected processing functions from the at least one processing function for the service controller, the mission management function sends one or more selected processing function IDs of the one or more selected processing functions to the service controller.

An apparatus, method, apparatus, and readable storage medium are described for controlling function relocation wherein, according to one embodiment, the apparatus includes a processor coupled with a memory storing computer program code, in one embodiment, a system includes computer program code to cause a first device to perform the following: for a first task executed by a first task control function (TCF), determining that the first TCF is to be replaced by a second TCF, where the first TCF and the second TCF are managed by mission management (MM), and for a second task executed by the first TCF, determining that the first TCF is to be replaced by the second TCF, where the first TCF and the second TCF are managed by the MM. And transmitting, to the first TCF, a first synchronization request including information of the second TCF for requesting the first TCF to transmit task execution (TE) information to the second TCF, the TE information including execution information of the first task executed by the first TCF. Therefore, the relocation from the o-TCF to the n-TCF is realized.

The invention relates to a remote test system and method for cabin ecology. The system comprises a cloud service platform and at least one test bench deployed at a remote position. The cloud service platform is provided with a web service module, a business logic module, a data storage module and a remote scheduling module. A user remotely creates a test task through the web interface, the cloud service platform performs task management and authority verification, the cloud service platform issues the task to the corresponding rack for execution, and finally, the state and the result are returned to the web interface in real time. According to the invention, the physical space limitation can be broken, the test efficiency and the cooperation capability are improved, the cross-region test cost is reduced, and the method is suitable for the whole-process remote test of the distributed cockpit system.

This invention relates to the field of satellite communication technology, and more particularly to an intelligent optimization method, system, server, and storage medium for satellite communication missions. The method designs the initial communication link structure based on mission requirements, dynamically optimizes the link layout by calculating inter-satellite and satellite-to-ground distances in real time, improving transmission efficiency and stability. It introduces an intelligent mission management module, combined with system control algorithms, to monitor link status and achieve adaptive allocation of resources such as bandwidth and power, enhancing multi-mission collaboration capabilities. Integration testing of the link structure and management module is conducted by simulating a real orbital environment, and the optimal interconnection path is deployed based on the test results, ensuring the reliability and robustness of the system in practical applications. This method significantly improves the resource utilization, link reliability, and overall performance of satellite communication.

A system and method are provided for automated pre-launch and post-launch inspection of space launch vehicles and associated launch infrastructure using coordinated swarms of unmanned aerial vehicles (UAVs). In one implementation, multiple autonomous UAVs equipped with multi-modal sensors and protective design features execute coordinated inspection patterns under control of a mission management system that adapts to environmental conditions and enforces safety constraints. Sensor data are processed to detect and classify anomalies, generate inspection reports, and store results for trending analysis and predictive maintenance.

An integrated electronic warfare system for unmanned aerial vehicles includes an equipment integrated integration module, a platform integrated coordination module, a system integrated control module and a system integrated application module. The platform integrated integration module integrates universal interfaces, universal payloads and universal antennas to realize the integrated integration of a single unmanned aerial vehicle platform; the platform integrated coordination module includes high-altitude long-flight UAVs, medium-altitude long-flight UAVs, medium-low-altitude long-flight UAVs and vertical take-off and landing UAVs to achieve full coverage of airspace at 20,000 meters and below; the system integrated control module includes flight management equipment, mission management equipment and platform management equipment to realize hierarchical combat command, layered intelligence processing and distributed confrontation; the system integrated application module includes a peacetime-wartime combination mode, a soft-hard combination mode, a true-false combination mode and a far-near combination mode to realize multi-dimensional, multi-means and multi-mode electronic warfare.

A mission management system for a heavy-duty vehicle, including processing circuitry configured to: receive a request for a transport mission; identify one or more available routes; identify, along said one or more available routes, energy supply stations which are suitable for re-supplying energy to the heavy-duty vehicle and which have available un-booked time slots for such re-supplying of energy; determine, for at least one available un-booked time slot of at least one of the identified energy supply stations, a probability of missing that time slot due to the heavy-duty vehicle arriving late to the energy supply station;select, based on the determined probability, a route and an energy re-supply plan associated thereto, for the heavy-duty vehicle for accomplishing said transport mission; and present the selected route and associated energy re-supply plan to a user interface and / or provide the selected route and associated energy re-supply plan for storage in a memory.

A mission management compute device is configured to assign each mission from a plurality of missions to an operator from a plurality of operators. Each operator from the plurality of operators is uniquely associated with at least two unmanned vehicles from a plurality of unmanned vehicles. A plurality of ground control compute devices is operatively coupled to the mission management compute device. Each ground control compute device from the plurality of ground control compute devices is uniquely associated with an operator from the plurality of operators and the at least two unmanned vehicles uniquely associated with that operator. The mission management compute device is configured to automatically determine that an operator from the plurality of operators cannot perform a mission from the at least two missions associated with that operator and automatically reassign the mission that cannot be performed by the operator in response.

1. Name of the product in this design: Spaceborne Electronic Platform. 2. Application of this design: This design is used to realize satellite mission management, attitude and orbit control calculation and management, power control and management, thermal control management, data processing, telemetry and control and data transmission management. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: 3D view 1.