19 results about "Mission operations" patented technology

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.

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

A host satellite comprises a first memory segment for storing a mission operation lookup table having at least one mission operation identifier associated with mission parameter constraints, a target object type and object detection model parameters associated with the target object type. A first sensor provides satellite sensor data that represents orbital mission characteristics. A second sensor captures images. A mission operation selector is responsive to the orbital mission characteristics and the mission parameter constraints for selecting the at least one mission operation identifier. An object detector is responsive to the captured images and the object detection model parameters associated with the selected mission operation identifier for detecting objects from the captured images. An analytics generator is responsive to the detected objects, the orbital mission characteristics, and the mission operation identifier for creating a mission analytics packet. A communication interface transfers the mission analytics packet to the client terminal.

Method (300) implemented by one or more processors, the method comprising: Identifying (302) metadata for each of a plurality of mission actions for an industrial environment; Reproducing (304), in a map surface for the industrial environment, a first subset of mission actions with first graphic features, wherein the reproduction of the first subset of mission actions with the first graphic features is performed in response to a determination that appropriate metadata for each of the mission actions of the first subset matches one or more first criteria; Reproduce (306), in the map surface for the industrial environment and together with the first subset of mission actions, a second subset of mission actions with second graphic features, wherein the reproduction of the second subset of mission actions with the second graphic features is performed in response to a determination that appropriate metadata for each of the mission actions of the second subset matches one or more second criteria, the first criteria differ from the second criteria, and where the first graphic features are visually distinct from the second graphic features; Receiving (308) a selection, via the map surface for the industrial environment, of a given mission action of the first subgroup or the second subgroup; and in response to receiving the selection, adding the given mission action to a predefined robot mission or incorporating the given mission action into a new robot mission.

The invention provides an unmanned aerial vehicle task graphical arrangement and management system, which analyzes a task component model through a task graphical arrangement module, combines and arranges task components displayed in a graphical manner through dragging and connecting a visual interaction mode, displays the task components in the graphical manner, and performs visual deployment and operation management on tasks. A task model file is generated, a task deployment management module generates operation instructions corresponding to task installation, loading, starting, stopping and deleting operation controls according to user operations in the task model file, and a task operation management module receives and responds to the operation instructions sent by the task deployment management module, analyzes an unmanned aerial vehicle task description model and sends the unmanned aerial vehicle task description model to the task deployment management module. The execution result sent by each task component is received in real time, and the interface is called to control installation, loading, starting, stopping, deleting and receiving of the execution result according to the switching logic between the task components in the task component model, so that the problem that in the prior art, complex steps are needed to be put into use is solved.

With the continuous development and improvement of modern technology levels, in the aspect of maritime warfare, many factors in the marine environment are intricate. Based on the guarantee requirements of the ship mission for the marine environment, combined with the influence of marine environmental factors on the mission operations of the ship platform and the effectiveness of weapons and equipment, the research problem of realizing the visualization of relevant auxiliary decision-making information by evaluating the impact of marine environmental factors is urgently to be solved. The present invention is a marine environment effectiveness evaluation system based on the front-end and back-end separation technology. The overall system adopts a front-end and back-end separation design, combines a marine environment effectiveness quantification evaluation model, realizes the calculation of the impact indicators of marine environmental elements on the effectiveness of the ship platform, and outputs and displays the quantification evaluation results of the marine environment effectiveness of the ship platform and the marine environment field information.

The invention discloses a single-person low-altitude aircraft based on a distributed power and intelligent attitude stabilizing system and a control method, and relates to the technical field of aviation flight, the single-person low-altitude aircraft comprises a central bearing unit, a control unit and a control unit, the central bearing unit is constructed into a rigid backpack structure conforming to a human body back curve; a distributed propulsion system includes; the pair of main lift ducted fans are symmetrically and pivotally mounted on two sides of the central bearing unit, and ducted nozzles of the main lift ducted fans can be controlled to perform vector deflection; the multiple auxiliary stabilizing ducted fans are installed on the adjustable exoskeleton supports corresponding to the four limbs of the user respectively, the multiple fans disperse propulsive force to the back and the four limbs, a real-time adjusting algorithm is matched, the body balance problem in the flying process is effectively solved, and the user can keep the stable posture without continuously and finely adjusting the limbs. By means of the design, the two hands of an operator can be naturally liberated in the flying process, and the device can be used for executing task operations such as shooting and detection.

This invention discloses a multi-functional landing gear with load-bearing capacity, belonging to the field of multi-rotor unmanned aerial vehicle (UAV) technology. It includes: a landing gear mainboard, a first connecting assembly, a second connecting assembly, a payload bay, and a support member. The first connecting assembly includes a first connecting member disposed on the landing gear mainboard and a first mating member disposed on the UAV. The second connecting assembly includes a second connecting member disposed below the landing gear mainboard and a second mating member disposed on top of the payload bay, with the payload bay located below the landing gear mainboard. The support member is connected to the lower part of the landing gear mainboard via an angle adjustment device. The support member is configured as a telescopic structure, allowing adjustment of its length via the telescopic structure. The angle adjustment device allows adjustment of the angle between the support member and the landing gear mainboard. This invention enables rapid replacement of landing gear with different loads according to mission site requirements, reducing the number of UAV types carried during multi-mission operations and improving transportation efficiency.

A system and apparatus for determining the best course of action at any particular point inflight. The system determines current aircraft configuration against an expected aircraft configuration to detect configuration errors, and then utilizes configuration errors and error trends to manage aircraft configuration and mission operation. The system may divert the aircraft to the best available landing sites or reconfigure the aircraft to resolve configuration errors. In an emergency the system may safely land the aircraft.

Aspects relate to system and methods for determining a user specific mission operational performance, using machine-learning processes. An exemplary system includes a computing device configured to perform operations including receiving user-input structured data from at least a user device, receiving observed structured data related to the user and a mission performance metric, inputting the user-input structured data and the observed structured data to a machine-learning model, generating a user performance metric as a function of the machine-learning model, receiving a deterministic mission operational performance metric, disaggregating a deterministic user performance metric as a function of the deterministic mission operation performance metric and the mission performance metric, inputting training data to a machine-learning algorithm, where the training data includes the user-input structured data and the observed structured data correlated to the deterministic user performance metric, and training the machine-learning model as a function of the machine-learning algorithm and the training data.

The invention discloses a dynamic reconstruction device and method for a micro-nano small satellite electronic system. The scheme comprises two parts: one part is a task-oriented hardware dynamic reconstruction technology, FPGA hardware reconstruction is realized through a configuration center and configuration node reconstruction technology, and on-orbit tasks and function upgrading, correction of software and hardware errors, adaptation to different environment adjustment functions and the like can be completed; and 2, on the basis of a software dynamic reconstruction technology of an operating system, an embedded real-time multi-task operating system kernel module is utilized, micro-restart-based operating system self-healing and on-orbit software dynamic upgrading are included, and task-level dynamic upgrading and self-repairing are realized. According to the scheme, flexible configuration and dynamic reconstruction of the micro-nano satellite electronic system are achieved, and the reliability of in-orbit operation of the micro-nano satellite electronic system is guaranteed.

The invention discloses a fire-extinguishing aircraft-oriented task state indicating system, which judges that a fire-extinguishing aircraft executes power-on, ground self-inspection, ground maintenance, ground water injection, water drawing, medicament injection and water-throwing fire-extinguishing task operations by receiving a fire-extinguishing task state signal output by a fire-extinguishing system. And the current task state information is displayed on the multifunctional display window of the display in a message bar message form according to the fire extinguishing task state judgment result. According to the invention, fire extinguishing task state indications dispersed everywhere in a cockpit are intensively displayed on the multifunctional display window of the display in the main visual angle range of the unit, so that the operation steps of the unit are effectively reduced, and the workload of the unit is reduced; based on aircraft operation parameters, real-time operation state data indication of the fire extinguishing system is provided, state changes of the fire extinguishing system are indicated in a message, data and graphic mode, and the task scene sensing capacity of a unit is improved.

The embodiment of the invention provides a system for maintaining task operation continuity, and the system comprises a server which is in communication coupling with a first computer device and a second computer device. The server is configured to: monitor individual operating states of a first computer device and a second computer device, where the first computer device and the second computer device are individually deployed with at least a first task in a Docker form, and the first task is assigned to be run by the first computer device; and in response to determining that the first computer device cannot normally operate, assigning the first task to a normally operating second computer device to operate through the distributed architecture. Therefore, the task can be transferred to another computer device which normally runs to continue to run through the distributed architecture, so that the effect of maintaining the continuity of task operation is achieved. The invention further relates to a method for maintaining task operation continuity.

The utility model provides an atmosphere data acquisition control system for a general aviation aircraft, and aims to solve the problem of poor compatibility caused by the fact that the conventional atmosphere data acquisition system for the general aviation aircraft cannot integrate various types of meteorological detection equipment. The system comprises a main module, user interface equipment, an external interface and a task operation table. The main module comprises a data acquisition and processing module, a data storage module, an exchange module and an atmosphere data analysis module. According to the utility model, by integrating a plurality of external devices with different functions and using a specific data processing and analyzing mode, centralized control and unified data processing of the plurality of external devices are realized, and the problems of independent operation and poor compatibility of the existing atmospheric data acquisition system of the general aviation aircraft are solved; and meanwhile, due to the modular design, the convenience of installation, maintenance and use of external equipment is improved, and good expansion capacity is achieved so as to meet various operation requirements.

The present invention discloses a flight inspection method and system based on an intelligent unmanned aerial vehicle, relating to the technical field of unmanned aerial vehicle inspection, including: establishing a remote control and telemetry link and a data link between the unmanned aerial vehicle and the ground control station, evaluating the task requirements of the unmanned aerial vehicle, and determining and testing and verifying the required minimum endurance time; obtaining the unmanned aerial vehicle status data through the remote control and telemetry link, and transmitting the unmanned aerial vehicle status data to the ground control station, and the ground control station calculates the flight trajectory according to the obtained unmanned aerial vehicle status data; the ground control sends a flight control instruction to the unmanned aerial vehicle and sends a task operation instruction to the mission payload system; the unmanned aerial vehicle executes the received flight control instruction and task operation instruction, and feeds back the execution status and task data to the ground control station through the data link, continuously monitoring and recording the flight status and task data. The present invention can continuously collect data, transmit data in real time, and does not require multiple collections, improving the inspection work efficiency.

Aspects of the subject disclosure may include, for example, a device having a processing system including a processor; and a memory that stores executable instructions that, when executed by the processing system, facilitate performance of operations including: receiving a path of a threat vehicle; calculating a closest approach distance based on a current position of a drone and the path of the threat vehicle; determining that the closest approach distance is within a threshold; and sending a command to the drone to descend to a safe altitude. Other embodiments are disclosed.

A method of processing instructions at a processing unit having a parallel processing engine. During a mission cycle, a first set of mission operand values is processed in accordance with a mission instruction at a first processing instance to generate a first mission output. In parallel, a second set of mission operand values is processed in accordance with the mission instruction at a second processing instance to generate a second mission output. During a test cycle, a first set of test operand values is processed in accordance with a test instruction at the first processing instance to generate a first test output, and in parallel, a second set of test operand values is processed in accordance with the test instruction at the second processing instance to generate a second test output, where the first set of test operand values is the same as the second set of test operand values. The first test output and the second test output are compared and a fault signal is raised if the compared test outputs do not match.

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.