272 results about "Flight system" patented technology

The invention discloses a power station photovoltaic field area automatic inspection unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicle inspection, and the unmanned aerial vehicle comprises the following components: a meteorological self-adaptive intelligent inspection flight system, a power supply module, a rotor wing device and a communication module; the power supply module is used for providing power support for each component of the unmanned aerial vehicle; the communication module is used for realizing data interaction between the unmanned aerial vehicle and the ground control station and between the unmanned aerial vehicle and the photovoltaic field area monitoring equipment; by carrying the meteorological self-adaptive intelligent inspection flight integrated system, meteorological conditions of a photovoltaic field area can be perceived and analyzed in real time, and an inspection path and a flight attitude are dynamically optimized according to the meteorological conditions, so that the unmanned aerial vehicle can preferentially inspect an area where a problem is most likely to occur, and the inspection efficiency is remarkably improved; meanwhile, the unmanned aerial vehicle can keep stable flight under complex meteorological conditions such as strong wind, flight accidents are avoided, and the accuracy of inspection data is ensured.

The present invention relates to a digital accompanying flight system for a launch vehicle based on real-time telemetry data, and a method. The system comprises a ballistic simulation model, a propulsion simulation model, a mass simulation model, an aerodynamics simulation model, an environment simulation model, a timing model, and a trigger correction model. The ballistic simulation model, the propulsion simulation model, the mass simulation model, the aerodynamics simulation model, and the environment simulation model synchronously perform simulation. On the basis of a preset flight sequence and real-time telemetry data, the timing model determines, at each simulation step length, whether a key timing action has occurred, and simulates the key timing action by adopting a discrete event message. On the basis of telemetry data of a launch vehicle which is obtained in real time, the trigger correction model determines whether the ballistic simulation model needs to be corrected, and when correction is needed, sends a correction message to the ballistic simulation model.

The invention provides a comprehensive test bench for an aircraft system, and relates to the technical field of equipment testing. Platform function support is provided through the simulation flight system, the comprehensive control and test auxiliary system, the data acquisition analysis system, the software test system, the airborne system integration module and the fault injection system. Through a platform I / O resource pool, a simulation power supply and distribution system, a test network, a reflection memory network and a wiring and tandem system, different aircraft system test benches are cooperated to carry out a linkage comprehensive experiment. According to the invention, the building of the aircraft system comprehensive test bench is realized among the power device system test bench, the atmospheric inertial navigation system test bench, the passenger cabin information system test bench, the copper bird test bench and the iron bird test bench, so that the linkage test operation requirement is met.

The invention provides a method and a system for generating deviation guide information in an approaching landing section of an aircraft and a readable storage medium, and the method comprises the steps: S1, real image collection and processing: capturing an outboard environment image through an airborne visual sensor, and extracting key feature points of a target landing airport runway; s2, virtual image generation: based on the airport three-dimensional high-precision map, generating an approach glide image under a visual angle of a virtual camera; s3, image feature registration: carrying out spatial alignment on the key feature points of the runway in the real image and the key feature points of the runway in the virtual image; the pixel deviation of the runway center point in the real image and the virtual image is calculated, glide guidance is provided for a pilot or is directly input into an automatic flight system.The method can be used for the aircraft in the approaching landing section, the enhanced outboard visual display is provided for the pilot in the cockpit based on the equivalent ILS deviation guidance method, and the visual guidance effect is improved. And providing approaching glide deviation guide information.

Disclosed in the present invention is an unmanned aerial vehicle flight trajectory anomaly tracing method based on a fusion clustering algorithm. A hierarchical clustering algorithm is applied to classify and organize complex and sensitive spatio-temporal data features to identify a potential anomaly point; then, weights of various data features obtained by using a Lasso regression algorithm are used to calculate the sum of products of the potential anomaly point and the weights of the various data features; a system detects an anomaly point in a flight trajectory of an unmanned aerial vehicle to ensure flight safety and stability; the anomaly point is confirmed; and the system instantly calls an improved KD tree algorithm to quickly notify nearest on-duty personnel to go to the site, thereby comprehensively inspecting and thoroughly verifying factors interfering with the normal flight of the unmanned aerial vehicle, quickly and accurately processing anomaly conditions of the flight of the unmanned aerial vehicle, ensuring the flight safety and data integrity of the unmanned aerial vehicle, and providing reliable guarantee and support for a flight system of the unmanned aerial vehicle.

There is provided a method performed by a configuration unit, the configuration unit being communicatively coupled to a communication network and an Uncrewed Aerial System, UAS, the UAS including an Uncrewed Aerial Vehicle, UAV, and a UAV controller, UAV-C, the method comprising: receiving, for each of a plurality of UAV service suppliers, USS, information specifying a service area of that USS; obtaining UAS specific information, wherein the UAS specific information comprises a UAV registration area, a USS service requirement, or a combination thereof; and determining a mapping of the UAS specific information to one or more of the plurality of USSs based on the received USS information and the obtained UAS specific information.

The present invention relates to an on-board redundant controller and standby aviation sensors in-flight reconfigurable autonomous flight system, which includes UAV, primary autopilot module, secondary autopilot module and switching module. The primary autopilot module and secondary autopilot module are equipped with first aviation sensing module and second aviation sensing module. The primary autopilot module produces response signal according to the request signal produced by the secondary autopilot module. When the first response signal is no longer produced by the primary autopilot module for a preset time, the first switching module switches controls of the flight control module from the primary autopilot module to the secondary autopilot module, and the secondary autopilot module uses the aviation data of the second aviation sensing module to provide flight control signals to the flight control module.

The invention relates to an unmanned helicopter suspension anti-swing method and system, belongs to the technical field of unmanned aerial vehicle control, and solves the problems that an existing unmanned aerial vehicle suspension flight system is high in dependence on load mass, limited in application range and low in control precision during control. The method comprises the following steps: respectively obtaining three-axis attitude motion information of a detacher adapter plate and three-axis attitude motion information of a hanging box; on the basis of the three-axis attitude motion information of the detacher adapter plate and the three-axis attitude motion information of the hanging box, calculating to obtain swing data of the hanging box relative to the detacher adapter plate; based on the swing data, calculating to obtain an anti-swing horizontal acceleration; and based on the anti-swing horizontal acceleration, calculating to obtain an anti-swing angle output by the anti-swing controller, and inputting the anti-swing angle and the current attitude angle and the target attitude angle of the unmanned helicopter into an attitude controller to control the unmanned helicopter. The swing is quickly eliminated, the flight stability is improved, the dependence on specific conditions is reduced, and the system adaptability and reliability are enhanced.

The invention relates to an intelligent flight system and method, through integrated control of a terminal transportation module, an aircraft module, a terminal interaction module, a communication module, a path planning module and a safety monitoring module, deep fusion of aircraft-level reliability, intelligent cluster scheduling and a green energy technology is realized, and unmanned intelligent flight driving is realized. Wherein the terminal transportation module has two modes, one mode serves users of high-rise buildings and is provided with independent vertical transportation equipment and parking aprons, and the other mode is provided with independent information verification rooms and parking aprons and is applied to users in mountainous areas, independent areas and the like.

The invention belongs to the field of flight network and channel planning, particularly relates to a ground network point and air channel planning method for urban low-altitude traffic, and aims to solve the problems that in an urban traffic scene, flight of a large number of aircrafts is difficult to manage in a standardized manner, and flight trajectories intersect randomly to easily cause aircraft conflicts in a dense flight scene. The method comprises the following steps: setting a plurality of aircraft flight ground base stations based on a honeycomb structure; determining an initial website and an end website; acquiring a website flight path through a path approximation selection algorithm; an air channel planning path is formed by the starting point-initial network point of the aircraft, the network point flight path and the ending network point-ending point of the aircraft; and carrying out flight height layering according to the flight direction in the branch flight path. The air traffic flight system solves the problems that the flight of a large number of aircrafts is difficult to standardize and the flight tracks are crossed randomly to easily cause aircraft conflicts, and is high in flight efficiency, high in flight safety and convenient to manage.

The invention discloses an intelligent liquid supplementing and sampling system and method of a microorganism sampler and an unmanned flight system. A control module controls a sampling liquid pump to inject sampling liquid in a sampling liquid bottle into a wet-wall cyclone type sampler by a preset liquid injection amount and suspends the sampling liquid pump; the control module controls the fan to inject air into the wet-wall cyclone sampler for sampling, and adjusts the rotating speed of the fan in real time according to the flow detected by the sampling flow sensor, so that the sampling flow is maintained in a preset flow range; in the sampling process, the temperature sensor is used for detecting the temperature of the current air environment in real time per second, the humidity sensor is used for synchronously detecting the humidity of the current air environment in real time per second, and the control module is used for substituting the current temperature and the current humidity into a one-second sampling liquid evaporation capacity fitting function. And calculating the evaporation capacity of the sampling liquid in one second in the current temperature and humidity environment, controlling the working liquid supplementing time of the sampling liquid pump, and injecting the sampling liquid into the wet-wall cyclone type sampler to realize intelligent real-time liquid supplementing.

Systems, computer readable medium and methods for fully autonomous drone flight are disclosed. Example methods include taking off, navigating in accordance with a flight plan, and navigating the autonomous drone to land. The autonomous drone performs flight plans with only an initial command for the autonomous drone to fly and, in some examples, an indication of a landing space such as an open hand presented under the autonomous drone. After an initial fly command, the autonomous drone is not controlled by a remote-control device and does not receive any additional commands to complete the flight plan. The autonomous drone enters a lower energy state while flying where the wireless connections are turned off since the autonomous drone does not respond to commands during flight.

The invention discloses a control method of a flight height layer change mode and an automatic flight system, which can ideally change a set value of a vertical speed threshold value in the flight height layer change mode according to the requirements of the vertical speed threshold value in different scenes. The control method includes selectively setting respective different vertical speed thresholds during climbing and descending in a flight altitude level change mode according to a double-shot or single-shot signal acquired from the engine.

The invention discloses a safety interval calculation method for an unmanned aerial vehicle and a manned aircraft, and relates to the technical field of aviation safety. The safe interval calculation method comprises the following steps: step 1, firstly obtaining the length, wingspan and height of a first target, then obtaining the length, wingspan and height of a second target, marking the first target as a mass point at the moment, and making up for an error caused by volume loss when the first target is regarded as the mass point. A new collision model is used for carrying out quantitative analysis on the collision probability of a manned aerial vehicle and an unmanned aerial vehicle so as to find the relation between the flight interval and the collision probability and calibrate a reasonable safety interval, and the requirement of the safety interval with a fixed value for the airspace cost is high. Therefore, the dynamic safety interval is found by adopting interval division iterative calculation, and a more flexible dynamic safety interval between the unmanned aerial vehicle and the manned vehicle is given on the basis, so that the construction of a fusion flight system is accelerated.

The invention discloses a method for modeling and verifying civil aircraft automatic flight system mode conversion based on a SysML language, and the method comprises the steps: firstly analyzing the key problems of high-level abstraction, hierarchical design, mode conversion logic and priority features in formalized modeling oriented to the field in detail, and constructing a meta-model for flight control mode design and conversion; secondly, expanding the formalized modeling language SysML based on the provided meta-model, and encoding the formalized modeling language SysML into a SysML profile file with a specific field; and then designing in an automatic flight system mode conversion modeling project of a certain type of civil aircraft by using an expanded SysMLprofile, and verifying the safety and correctness of the model by adopting an NUSMV. The invention provides a relatively complete and unified model building thought in the related fields of the automatic flight system, and can effectively ensure the system design quality and improve the system development efficiency and safety.

The invention discloses an electric flight system, which is characterized by comprising an electric vertical take-off and landing aircraft, a transportation flat car and a transportation track, the transportation flat car runs on the transportation track and is used for enabling the electric vertical take-off and landing aircraft to take off or land and charging the electric vertical take-off and landing aircraft during landing and parking; or when the electric vertical take-off and landing aircraft takes off, the electric vertical take-off and landing aircraft carries the transportation flat car to fly away from the transportation track. The transportation flat car is arranged on the off-line platform, the eVTOL can directly fall onto the transportation flat car to be charged when falling, the transportation flat car conveys the fallen eVTOL to the off-line position, the charging problem is solved, and parking management can be facilitated.

The invention belongs to the technical field of flight systems, and particularly relates to a six-rotor unmanned aerial vehicle accurate flight system with positioning and navigation functions, which comprises a multi-source positioning sensing module, a dynamic weight fusion module and a self-adaptive trajectory control module, the multi-source positioning sensing module is integrated with a double-antenna RTK-GNSS unit, a triple-redundancy IMU unit, a laser radar SLAM unit, a visual anchor point identification unit and a pipeline electromagnetic detection unit and can collect air-ground-underground multi-dimensional positioning signals at the same time, and each unit is provided with a signal preprocessing sub-module which can perform noise reduction and abnormal value elimination on original signals; the dynamic weight fusion module is internally provided with a signal confidence evaluation model and a scene pre-judgment sub-module, and the signal confidence evaluation model can calculate the confidence value of each positioning unit in real time. According to the system, through multi-module cooperative linkage, the full-scene positioning precision is greatly improved, and the positioning limitation of a traditional unmanned aerial vehicle is effectively solved.

The invention relates to a high-overload electric steering engine fault monitoring method, belongs to the technical field of electric steering engines, and solves the problems that a steering engine fault monitoring method in the prior art is large in calculation amount, poor in real-time performance, incapable of being flexibly configured and incapable of performing self-locking monitoring. Comprising the following steps that a high-overload electric steering engine is powered on; after the steering engine controller is initialized, acquiring quick-start section data; wherein the quick start section data is data from the initialization of a steering engine controller to the completion of the initialization of a flight system, and comprises rudder feedback information; after the flight system is initialized, quick-start section data are extracted, and then self-locking monitoring is carried out; the clamping stagnation state of each channel control surface is monitored based on the rudder instruction information and the rudder feedback information of each channel control surface; wherein the rudder instruction information is expected position information, and the rudder feedback information is actual position information. And fault monitoring of the high-overload electric steering engine is realized.

The invention discloses a dynamic modeling and analysis method for a gull-wing morphing aircraft in the technical field of flight system control. The dynamic modeling and analysis method comprises the following steps: S1, calculating aerodynamic force and torque borne by the aircraft according to a three-dimensional lift line theory; s2, establishing a multi-body dynamic model through a quasi-Lagrange equation; s3, analyzing the aerodynamic characteristics of the aircraft according to the calculation result of the experiment; s4, analyzing the kinematics characteristics of the aircraft according to the calculation result of the experiment; and S5, adjusting the wing configuration according to the analysis result, so that the aircraft keeps stable flight. The method solves the problem that a traditional variant aircraft is not matched in performance at different flight stages, especially is large in lift force loss under the low-speed condition.

The invention discloses an over-driven flight system teleoperation planning method based on a MINCO trajectory, and relates to the field of flight system trajectory planning. The problems that efficiency is reduced due to non-uniqueness, caused by redundancy characteristics, of inverse kinematics of a system during teleoperation of an overdrive vector rotor flight system in the prior art, and the process of seeking optimal solutions of multiple planned feasible solutions is complex in planning, long in consumed time and incapable of guaranteeing tracking precision are solved. According to the method, the waypoint of the trajectory and the time parameterization trajectory are directly utilized, the energy consumption of the system, the stability of the trajectory and the obstacle avoidance characteristic serve as optimization targets, the quasi-Newton method is used for accelerating convergence to the optimal solution, and the optimal trajectory is obtained to guarantee the tracking precision of the follow-up tracking process. The method is mainly used for trajectory planning of the teleoperation system.

The invention relates to the field of unmanned aerial vehicle autonomous flight control and intelligent decision making, and discloses an unmanned aerial vehicle anti-disturbance flight system and method based on multi-source fusion perception. The system comprises an airborne system and a ground system, wherein the airborne system carries a visual, ultrasonic and inertial three-source module, a fusion calculation module in data connection with the three-source module, a robust control module in data connection with the fusion calculation module, and a degradation decision module in data connection with the fusion calculation module and the robust control module. The anti-disturbance capability of the operation of the unmanned aerial vehicle in the forest fire prevention process is improved, and reliable sensing support is provided for autonomous flight and task execution of the unmanned aerial vehicle.

The invention discloses a laser etching dust extraction flight following system and a control method, and relates to the technical field of thin film solar cell manufacturing. The following system comprises a focusing dust extraction module, a following driving module, a cooperative control unit and a negative pressure dynamic adjusting module. The cooperative control unit comprises a following PLC controller and a motion control card, the following PLC controller synchronously obtains path planning information from a galvanometer flight system of a laser beam and generates a displacement instruction, and the displacement instruction is sent to a following driving module through the motion control card; and the following driving module and a galvanometer scanning module of the galvanometer flight system are synchronously triggered, and the following driving module moves according to the displacement instruction and controls the center of the dust extraction cover body and the etching point of the laser beam to coaxially move in a following manner. The method is low in dust removal efficiency and series resistance, good in parameter stability, low in equipment maintenance cost and suitable for processing large-size thin film batteries such as perovskite and cadmium telluride.

Systems, computer readable medium and methods for fully autonomous drone flight are disclosed. Example methods include taking off, navigating in accordance with a flight plan, and navigating the autonomous drone to land. The autonomous drone performs flight plans with only an initial command for the autonomous drone to fly and, in some examples, an indication of a landing space such as an open hand presented under the autonomous drone. After an initial fly command, the autonomous drone is not controlled by a remote-control device and does not receive any additional commands to complete the flight plan. The autonomous drone enters a lower energy state while flying where the wireless connections are turned off since the autonomous drone does not respond to commands during flight.

A flying vehicle is disclosed with a plurality of projectile systems that each contains a projectile for projecting at another flying device. The flying vehicle can include a control system, a flight system in communication with the control system for enabling the flying vehicle to fly, a first projectile system in communication with the control system and a second projectile system in communication with the control system. The control system determines, based on a characteristic of a target flying vehicle, whether to implement a first mode utilizing the first projectile system or a second mode utilizing the second projectile system to capture the target flying vehicle.

A flying vehicle is disclosed with a plurality of projectile systems that each contains a projectile for projecting at another flying device. The flying vehicle can include a control system, a flight system in communication with the control system for enabling the flying vehicle to fly, a first projectile system in communication with the control system and a second projectile system in communication with the control system. The control system determines, based on a characteristic of a target flying vehicle, whether to implement a first mode utilizing the first projectile system or a second mode utilizing the second projectile system to capture the target flying vehicle.

A disclosed device allows a person to fly. A disclosed wearable flight system includes a plurality of propulsion assemblies including a left-hand propulsion assembly configured to be worn on a user's left hand and / or forearm and a right-hand propulsion assembly configured to be worn on a user's right hand and / or forearm. A further embodiment includes a body propulsion device that is configured to provide a net force along an axis defining a net body propulsion vector and a support device configured to support a user's waist or torso. The support device is configured to hold a user's body relative to the body propulsion device such that a line extending between center the of the user's head and the center of the user's waist extends, relative to the orientation of the net body propulsion vector during use, by a body propulsion elevation angle that is greater than zero.

The invention discloses an airborne environment monitoring and obstacle early warning system and an implementation method, and relates to the field of civil aviation auxiliary flight systems, the airborne environment monitoring and obstacle early warning system comprises hardware composition modules including a foresight sensing module, a lateral camera module, a millimeter wave radar system, an airborne computing platform, a cockpit display system and a positioning and attitude sensing module; the data synchronization and coordinate conversion module aligns all sensor data to an aircraft body coordinate system; the sensing algorithm module comprises a sensor data acquisition and preprocessing module, a feature extraction module, a coordinate conversion to BEV coordinate system module, a feature fusion module, a target detection module, an attitude correction module, an early warning logic module and a parameter configuration module; and the state adaptation module dynamically adjusts the perception strategy based on the flight stage. The method has the advantages that the sensing ability of the aircraft to the surrounding environment in the sliding and flying process is improved, a pilot is assisted in recognizing obstacles, and collision accidents are prevented.

The invention discloses an unmanned aerial vehicle road intelligent cruise system based on internal signals, and relates to the field of unmanned aerial vehicle cruise. When an unmanned aerial vehicle performs road inspection, data information around an inspection road is obtained by using a laser radar sensor and a camera, and the obtained two different data are fused; more comprehensive and more accurate perception of the environment is realized so as to improve the environment perception precision of a subsequent built-in map chip, the current position of the unmanned aerial vehicle on the inspection road is acquired by using a scene matching mode, and during path planning, an unmanned aerial vehicle autonomous flight system masters regional map information, so that the path planning efficiency is improved. In this way, inspection can be intelligently completed without external signals, the problem that the unmanned aerial vehicle is difficult to complete road inspection work due to the fact that the unmanned aerial vehicle gets lost in a district with weak satellite signals and dark light can be avoided, the unmanned aerial vehicle inspection can achieve a better effect, and the practicability of the unmanned aerial vehicle is further improved.

To make it possible to further improve the safety of operation of a remotely steered flying object.SOLUTION: An operation system supports or manages the operation of manned flying objects with pilots on board that fly in a predetermined airspace area and remotely steered unmanned flying objects that fly in an airspace area that is at least partially shared with that of the manned flying objects. The operation system includes: a flying object information acquisition unit that can acquire aircraft type information on a plurality of flying objects including the manned flying objects and the unmanned flying objects; and an integrated information generation unit that generates integrated information including the aircraft type information on the plurality of flying objects. The operation system transmits the integrated information to the plurality of flying objects or a remote steering device that remotely steers the unmanned flying objects.SELECTED DRAWING: Figure 1

The invention discloses an unmanned aerial vehicle multi-aircraft cooperative dynamic path planning method, which comprises the steps of 1, establishing a multi-aircraft cooperative flight system model comprising an unmanned aerial vehicle individual model and a flight environment model, 2, collecting real-time environment information, 3, carrying out distributed cooperative decision making and path planning, 4, carrying out dynamic adjustment and anti-collision control, and 5, carrying out unmanned aerial vehicle multi-aircraft cooperative dynamic path planning. 5, multi-unmanned aerial vehicle cooperative flight control is carried out, and a flight control instruction of each unmanned aerial vehicle is generated according to the adjusted path; the multi-unmanned aerial vehicle cooperative flight system has the beneficial effects that the multi-unmanned aerial vehicle cooperative flight system model is based on a distributed control architecture, model integration is realized through three steps of data acquisition, information fusion and strategy generation, real-time data sharing among unmanned aerial vehicles is realized, when a certain unmanned aerial vehicle detects a dynamic obstacle, collective path re-planning can be triggered, and the dynamic obstacle can be detected by the unmanned aerial vehicle. And the formation stability is kept while multiple machines avoid obstacles.