142 results about "Flight system" patented technology

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.

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.

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 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.

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.

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

This invention provides a method, apparatus, and medium for implementing a multi-UAV formation flight system, relating to the field of UAV formation flight technology. The ground station and multiple UAVs are networked together. Multiple UAVs are grouped by a task management thread. Based on the grouping, tasks are distributed to the UAVs in real time, and feedback on the UAV execution results is obtained in real time. Based on the feedback information, the task management thread is triggered to distribute tasks to the next group of UAVs in real time. While ensuring real-time task distribution, UAV collisions can be avoided. The takeoff and landing process is streamlined, preventing UAVs from being misplaced and collisions during takeoff.

The invention provides a multi-unmanned aerial vehicle formation flight system implementation method and device and a medium, and relates to the technical field of unmanned aerial vehicle formation flight, a networking mode is adopted between a ground station and a plurality of unmanned aerial vehicles, the plurality of unmanned aerial vehicles are grouped through a task management thread, tasks of the unmanned aerial vehicles can be sequentially distributed in real time according to the grouping condition, and the unmanned aerial vehicle formation flight efficiency is improved. The feedback of the execution result of the unmanned aerial vehicle is obtained in real time, the task management thread is triggered according to the feedback information to perform real-time task distribution on the next group of corresponding unmanned aerial vehicles, and the collision of the unmanned aerial vehicles, the flow of the takeoff and landing process, the misplacement of the unmanned aerial vehicles and the collision of the takeoff process can be avoided under the condition of ensuring the real-time task distribution.

A mode sequencer circuitry for a time-of-flight system, the time-of-flight system including at least an imaging unit and an illumination unit, the imaging unit having a data bus interface for transmitting data to an application processor over a data bus.

The invention relates to the technical field of unmanned aerial vehicles, and discloses an unmanned aerial vehicle and a flight system.The unmanned aerial vehicle comprises a shell, propellers, a heating part, a heat dissipation part and a vehicle arm assembly; one end of the arm assembly is connected to the shell, and the other end of the arm assembly is provided with a propeller; a containing cavity is formed in the machine shell, the heat dissipation piece and the heating piece are arranged in the containing cavity, and the heat dissipation piece is close to or makes contact with the heating piece. An air inlet channel is formed in one end of the machine arm assembly, and an air inlet end opening of the air inlet channel is located below the propeller and located in a rotating area of the propeller; an air outlet end opening of the air inlet channel communicates with the containing cavity, and an air outlet is formed in the containing cavity. According to the unmanned aerial vehicle, the air inlet channel is formed in one end of the vehicle arm assembly, the air inlet port of the air inlet channel is located below the propeller and located in the rotation area of the propeller, the rotation area of the propeller can not be overlapped with the shell, waste of the lift force of the propeller is avoided, and the flight efficiency and the endurance time of the unmanned aerial vehicle can be improved.

This application relates to an air control system, an aircraft air control method, an aircraft, and a flight system. The air control system includes an oxygen supply module, an air exchange module, a pressure regulation module, a detection module, and a control module. The oxygen supply module includes an oxygen reservoir, an oxygen electronically controlled valve, and an oxygen pipe. The air exchange module includes an airflow control component for regulating the airflow introduced from outside the cockpit to the indoor air outlet. The pressure regulation module is used to regulate the cabin pressure. The detection module includes an oxygen concentration detector and a cabin pressure detector. The control module is configured to control at least one of the oxygen electronically controlled valve, the pressure regulation module, and the airflow control component based on the oxygen concentration and cabin pressure. The air control system of this application can reduce the complexity of the system and, at the same time, can adaptively adjust in various scenarios, improving the accuracy and comfort of oxygen supply.

The utility model discloses a fire point detection and fire extinguishing device for an open pit coal mine. The fire point detection and fire extinguishing device comprises a flight system, a fire point identification system and a fire extinguishing system, a fire point can be extinguished through the arranged fire extinguishing system, a dry powder storage box is arranged on the fire extinguishing system, dry powder in the dry powder storage box is released through mutual staggered matching between an inner plate and a spray head in the dry powder storage box, and meanwhile, a booster pump is arranged on the dry powder storage box; dry powder can be quickly sprayed out through the arranged booster pump, and the purpose of quickly extinguishing fire is achieved; meanwhile, through mutual cooperation of the fire extinguishing system, the flight system and the fire point recognition system, integration from fire point recognition to fire point disappearance can be achieved, the defect of intermediate space caused by a traditional fire extinguishing mode can be effectively overcome, the fire extinguishing efficiency can be improved to the maximum extent, and losses are reduced.

The application discloses a microbial sampler intelligent liquid supplementing sampling system and method 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 sampler by a preset liquid injection amount and pauses the sampling liquid pump; the control module controls an air blower to inject air into the wet-wall cyclone sampler for sampling, and adjusts the rotating speed of the air blower in real time according to the flow detected by a sampling flow sensor, so that the sampling flow is maintained within a preset flow range; during the sampling process, a temperature sensor is used for detecting the temperature of the current air environment in real time every second, a humidity sensor is used for synchronously detecting the humidity of the current air environment in real time every second, and the control module is used for substituting the current temperature and the current humidity into a one-second sampling liquid evaporation amount fitting function, calculating the one-second sampling liquid evaporation amount under the current temperature and humidity environment, and controlling the sampling liquid pump to work for a liquid supplementing time, so that the sampling liquid is injected into the wet-wall cyclone sampler to realize intelligent real-time liquid supplementing.

An active throttle assembly 100 is disclosed. The active throttle assembly comprises a linear motor 120, the linear motor comprising a linearly extending track 124 and a carriage 122. The active throttle assembly further comprises a grip 110, wherein the grip is affixed to the carriage. A controller 140 is configured to control a current or voltage provided by a power supply to at least one of the linearly extending track or the carriage in order to control movement of the carriage with respect to the linearly extending track. A detector 130 configured to measure at least one of a kinematic variable of the grip or a force applied to the grip. The controller may provide haptic feedback to a user of the throttle assembly to indicate an operating condition of an engine of a vehicle containing the active throttle assembly and may be used as part of a fly by wire system.

The invention relates to a wearable flight system, that is, an apparatus for enabling an individual to fly. A wearable flight system (10) for a user comprises a right hand propulsion unit (14), a left hand propulsion unit (16), and a body support structure (18) for being worn on the user's body. The wearable flight system (10) further comprises a right support arm (20) extending from the body support structure (18) to the right hand propulsion unit (14) and connected to the body support structure (18) by a right rotational joint (101) comprising a resilient member; and a left support arm (22) extending from the body support structure (18) to the left hand propulsion unit (16) and connected to the body support structure (18) by a left rotational joint (103) comprising a resilient member.

The utility model discloses an unmanned plane landing anti -thrust device belongs to unmanned plane technical field, the device is in the abdomen of large fixed wing unmanned plane, including anti -thrust board and two groups of drive adjusting mechanism, the anti -thrust board is paddle formula arc structure, and the bottom surface is equipped with longitudinal fairing and is made with carbon fiber composite material, and the angle on the board is equipped with pressure sensor, drive adjusting mechanism contains support, connection hanging cylinder, drive assembly, axle seat, connecting seat and connecting rod assembly, can drive anti -thrust board and realize 0 degree 90 degree angle adjustment, and sensor feedback signal reaches controller, and controller receives unmanned plane flight system landing information and controls motor, forms closed loop control. The device utilizes the airflow to generate the reverse thrust and shortens the brake distance, and the anti -thrust board is horizontal when not working and does not influence the flight, and is light in weight, and the adjustment is accurate, and is convenient to maintain, is applicable to the safe landing of large fixed wing unmanned plane.

The present invention provides an unmanned aerial vehicle (100) comprising: a flight system (4) for producing thrust to manoeuvre the unmanned aerial vehicle (100). The flight system (4) comprises: one or more flight rotors (42) defining a plane passing through each flight rotor and a thrust direction generally perpendicular to the plane; and one or more electric motor (44) for driving the one or more flight rotors (42). The unmanned aerial vehicle (100) further comprises: a cargo area for coupling to or receiving a load (200); and a load system (6) for providing thrust additional to the thrust provided by the flight system (4) to thereby lift a load attached to the connection point. The load system (6) comprises: a first gas turbine propulsion system; and a controller configured to control the flight system (4) and load system (6).

The utility model provides a fuel conveying device and a flight system. The fuel conveying device comprises a control device, an oil pump and an oil storage device. Wherein the control device is connected with the oil pump, the oil pump is connected with an aircraft oil tank through a first oil way, and a three-way valve is further arranged on the first oil way; the oil pump is further connected with the oil storage device through a second oil way. The control device is used for controlling the oil pump to rotate forwards and controlling the three-way valve to be powered off, and air in the first oil way and air in the second oil way are exhausted. The control device is used for controlling the oil pump to rotate forwards and controlling the three-way valve to be powered on, and refueling is conducted on the aircraft oil tank from the oil storage device. The control device is further used for controlling the oil pump to rotate reversely and controlling the three-way valve to be powered on, and oil is pumped from the aircraft oil tank to the oil storage device. According to the invention, manual operation is reduced, and the working efficiency is improved.

The application provides an airplane system comprehensive test bench, and relates to the technical field of equipment testing; the application provides platform function support through simulation of a flight system, comprehensive control and test auxiliary systems, data acquisition and analysis systems, software test systems, airborne system integration modules and a fault injection system, and realizes linkage comprehensive experiments with different airplane system test benches through a platform I / O resource pool, a simulation power supply and distribution system, a test network, a reflective memory network and a wiring and junction system; the application realizes the erection of the airplane system comprehensive test bench between a power device system test bench, an atmospheric inertial navigation system test bench, a passenger cabin information system test bench, a copper bird test bench and an iron bird test bench, thereby meeting the linkage test operation requirements.

Multi-body flight system (10), comprising: a primary missile (1); a plurality of secondary missiles (2), each of which can be coupled to the primary missile (1) via a carrying and release system (11) to produce a launch configuration and can be triggered by the primary missile (1) in flight to produce an operational configuration; and a control system (4) which is designed to release the secondary missiles (2) from the launch configuration of the primary missile (1) during deployment as a function of mission specifications and to allow the primary missile (1) and the released secondary missiles (2) to assume the deployment configuration; wherein the primary missile (1) and the secondary missiles (2) are each designed as guided missiles; wherein the control system (4) comprises a control device (3) of the primary missile (1) and a control device (3) of each of the secondary missiles (2) for individually controlling the missiles (1, 2); wherein the primary missile (1) and the secondary missiles (2) each have a drive which are jointly designed to drive the multi-body flight system as a single guided missile.

An installation device for flight-launch system integration is located between an aircraft wing and an engine and used for system integration of an aircraft and the engine, and is characterized by comprising at least three supporting rods, one ends of the at least three supporting rods are installed on the aircraft, the other ends of the at least three supporting rods are provided with the engine, and the supporting rods are arranged on the aircraft wing. Two of the at least three supporting rods are positioned behind the course and one of the at least three supporting rods other than the two supporting rods is positioned in front of the course in the course of the aircraft. Therefore, a three-point supporting integrated configuration mode is used for replacing a traditional large frame, the weight of the aircraft can be reduced, the economical efficiency can be improved, the maintenance space of a flying launch structure, equipment and pipelines can be enlarged, and the flying launch design difficulty is greatly reduced.

An uncrewed aerial system (UAS) is configured to measure one or more atmospheric conditions in a stationary position or during vertical movement through the Earth's lower atmosphere. The UAS has a fuselage with a longitudinal fuselage axis that intersects a vertical reference axis in a non-orthogonal relationship, a plurality of arms, a plurality of motorized rotors supported by a corresponding one of the plurality of arms, and an air sampling module. The air sampling module includes an air scoop with an intake having an intake opening and a longitudinal intake axis that extends through the intake, and a sensor chamber connected to the intake on a first end and having a discharge on a second end. The sensor chamber has a longitudinal sensor chamber axis that extends from the first end to the second end. The longitudinal sensor chamber axis is angularly offset from the longitudinal intake axis by a scoop intake angle. The air sampling module further includes one or more sensors located in the sensor chamber and a fan located in the sensor chamber proximate the discharge.

1.The name of the design product: the unmanned aerial vehicle automatic flight system graphical user interface of electronic equipment. 2.The use of the design product: the design product is an electronic device. 3.The design points of the design product: the interface content of the graphical user interface in the screen. 4.The picture or photo that best indicates the design points: the front view. 5.The design contains colors. 6.The electronic equipment is of conventional design, and the rear view, left view, right view, top view and bottom view are omitted. 7.The use of the graphical user interface: the design product is used to display various data of the unmanned aerial vehicle automatic flight system. 8.The human-computer interaction mode of the graphical user interface: in the front view, after clicking the “aircraft control” button, the interface change state diagram is displayed; the gray block coverage area in the front view and the interface change state diagram is a variable part, and XX in the interface is replaceable text.

The invention relates to the field of unmanned aerial vehicle anomaly diagnosis, in particular to an unmanned aerial vehicle anomaly diagnosis method and system based on multi-modal data fusion. The method comprises the following steps: acquiring multi-modal sensor data of an unmanned aerial vehicle, analyzing dust characteristics in a current environment in real time according to the multi-modal sensor data of the unmanned aerial vehicle, and generating a basic dust risk parameter set; flight state parameters of the unmanned aerial vehicle are obtained, the flight state parameters of the unmanned aerial vehicle serve as dynamic correction factors and are dynamically fused with the basic dust risk parameter set, and a dynamic dust risk influence parameter set is generated; based on this, analyzing the influence degree of dynamic dust on the flight safety of the unmanned aerial vehicle, and generating a comprehensive dynamic risk level of the unmanned aerial vehicle; on the basis, the current dust risk composition condition is diagnosed, and an unmanned aerial vehicle abnormity diagnosis report is generated. In the unmanned aerial vehicle abnormity diagnosis process, the flight system can be effectively supported to carry out prospective self-adaptive decision making, and serious potential safety hazards are avoided.

The invention discloses an operation type cross-medium sailing robot which comprises a flight system, an underwater propelling system and a rope-driven mechanical arm, the flight system comprises a machine body, and rotor wing assemblies and foot stools are installed at the four corners of the machine body; the underwater propelling system comprises a first underwater propeller, a second underwater propeller and a third underwater propeller which are installed on the fuselage, the propelling directions of the first underwater propeller, the second underwater propeller and the third underwater propeller are perpendicular to one another in pairs, and the axis of one of the propellers is parallel to the lifting direction of the fuselage; the rope-driven mechanical arm comprises a driving device and a mechanical arm assembly connected with the driving device, and the driving device is installed at the bottom of the machine body and used for driving the mechanical arm assembly. Through cooperative work of the flight system and the underwater propulsion system, seamless switching between the air environment and the underwater environment is achieved, and the application scene and the operation capability of the unmanned aerial vehicle are remarkably expanded.

An apparatus and method for mounting a payload to a flight system. The apparatus includes a first arm, a second arm, a first member, a second member, and at least four attachment interfaces, attached to at least the payload and the flight system.

The utility model relates to the technical field of unmanned aerial vehicles, and discloses an unmanned aerial vehicle and a flight system, and the unmanned aerial vehicle comprises a vehicle body, a first camera module, a second camera module and a third camera module. The vehicle body is provided with a first part and a second part in the first direction, the first direction is the flight advancing direction of the unmanned aerial vehicle, and the first part is located in front of the second part; the first camera module is arranged on the first part of the machine body and located on the first side. The second camera module is arranged on the first part of the machine body and located on the second side, the first side and the second side are oppositely arranged in the second direction, and the second direction is perpendicular to the first direction; the third camera module is arranged on the first part of the machine body and located between the first side and the second side, and the first camera module, the second camera module and the third camera module are distributed in a triangular mode. Through the above structure, the unmanned aerial vehicle can reduce stereo matching ambiguity, improve depth measurement precision, solve the disadvantage of failure of a binocular method in a specific scene, and realize omnibearing multi-view perception coverage.

A multi-rotor aircraft arm is designed as a fold-able fixed-wing aircraft, which comprises a multi-rotor flight system, a folded fixed-wing flight system, a cabin (10), a chassis, etc. Multi-rotor aircraft arm which the cabin is connected with both sides also is a folded fixed-wing (2). The chassis includes the frame (1), the rotor flight system and the ground walking system. The top of the machine adopts an inflatable low cost parachute, the bottom adopts an anti-fall safety facility, the wing is provided with an anti-collision radar, and the front is provided with a micro laser ranging radar, and the use is safe and reliable. The structure of the invention adopts carbon fiber material, which makes the weight light. The aircraft has the characteristics of reasonable structure, shrinkage and folding, small volume, light weight, high controllability, low cost, safety and reliability, and high intelligence degree.