9 results about "Mission operations" patented technology

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 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 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.