135 results about "Airplane mode" patented technology

The invention discloses an automatic control method of a four-power-source tiltable aircraft, relates to the technical field of flight control of tiltable aircrafts, is realized based on a PX4 flight control system, and is suitable for a tiltable aircraft provided with four independent tiltable power sources and corresponding tilting execution mechanisms. According to the method, through configuration of a tilting angle control module, a power distribution module and a full-stage flight logic scheduling module, full-stage automatic control of vertical take-off and landing, suspension, horizontal take-off, fixed-point horizontal flight, automatic cruise, one-key return flight, fixed-angle flight, power source fault handling and the like is achieved. Smooth transition of all flight modes is achieved, the stability of the attitude, the height and the position of the tiltable aircraft in different flight stages is maintained, meanwhile, the functions of automatic obstacle avoidance, fault emergency and the like are integrated, flight safety is guaranteed, flight stability and applicability are improved, and the method can be widely applied to various tiltable aircraft operation scenes.

The invention discloses an unmanned aerial vehicle formation flight control method and device, an unmanned aerial vehicle and a storage medium. The method comprises the steps that formation parameters, flight task instruction data and flight state data of other unmanned aerial vehicles in a formation are acquired or updated; judging a control mode according to the flight task instruction data, wherein the control mode comprises at least one of the following modes: a normal control enabling and conventional flight mode, a calculation mode, a suspended hovering mode or a disintegration mode; according to the judgment result of the control mode, based on an L1 guide algorithm of self-adaptive track tracking, fusing unmanned aerial vehicle spacing control logic and / or formation control logic of formation dynamic adjustment to obtain a control instruction of an expected track and / or attitude, and executing the control instruction; and circularly executing the steps to ensure the continuity and dynamic adaptability of the unmanned aerial vehicle and the formation flight thereof. According to the scheme, a completely decentralized distributed control architecture is adopted, and a fault-tolerant mechanism is matched, so that the reliability and survivability of the formation system are remarkably improved.

The invention discloses an unmanned aerial vehicle anti-wind disturbance controller and a control method, and belongs to the technical field of unmanned aerial vehicle flight control. The method runs on an independent processing module which is connected in series between a main flight controller and an electronic speed regulator of the unmanned aerial vehicle, a dynamic reference is constructed by collecting motor current in real time, deviation is calculated, and wind disturbance equivalent disturbance torque is estimated in a prospective mode through a third-order linear extended state observer (LESO) with bandwidth parameterization design; in combination with a'user operation state + flight mode 'two-dimensional intelligent decision compensation strategy, a'look-ahead wind resistance + attitude backup' dual-redundancy channel is matched, so that the wind disturbance is compensated in advance, and the flight stability in a complex scene is ensured. A corresponding controller adopts a standardized independent hardware design, the adaptability is high, the integration cost is low, and the method can be widely applied to high-precision operation scenes of various multi-rotor unmanned aerial vehicles.

Aspects presented herein may enable a tracking device to disable its transmitter based on determining whether the wireless device is within the vicinity or a threshold distance of an airport and / or based on information or measurements obtained from its modem receiver. In one aspect, a wireless device detects whether the wireless device is within a threshold distance of a target location or whether the wireless device is airborne. The wireless device disables a transmitter of the wireless device based on detecting that the wireless device is within the threshold distance of the target location or that the wireless device is airborne.

The invention discloses an air-ground power multiplexing hovercar adopting electric wheel angle modules. The air-ground power multiplexing hovercar integrates electric wheels, a suspension system, a steering system, a car body and a support system. The hovercar has the dual-mode function of a land mode and a flight mode, and switching between the land mode and the flight mode is completed through cooperative work of the electric wheels, the steering system and the support system. Wherein the electric wheels and the steering system both adopt high-integration power multiplexing design, that is, a land mode and a flight mode multiplex the same set of execution motor and planetary gear train, so that the problems that too many actuators are introduced due to switching of the flight mode and the dual modes, the light weight level is low due to miscellaneous equipment, and the power consumption is low are solved to a great extent. And the problem of low-efficiency carrying of invalid loads caused by two sets of independent power is solved. The electric wheel angle module of the hovercar adopts a modular design and is also suitable for four-wheel, six-wheel and other multi-axle vehicle frameworks, and proper electric wheel angle modules can be matched and mounted according to vehicle performance requirements.

A flight mode transitioning device, method and system configured to facilitate transitioning between vertical flight mode and horizontal flight mode in a vertical take-off and landing (VTOL) aircraft, the device comprising at least one actuator mediated member capable of limiting the movement the aircraft wing so as to enable both forward fight and vertical flight.

The invention provides a multi-duct cooperative ground effect aircraft control method, and relates to the technical field of ground effect aircraft control, and the method comprises the steps: collecting flight parameters in real time, including aircraft attitude parameters, environmental parameters and / or duct operation parameters; matching a current flight mode according to the flight parameters, and calling a corresponding duct group according to a flight mode demand; based on a six-degree-of-freedom kinetic model and a ground effect lift force formula, calculating the total thrust and torque demand of the ground effect aircraft in combination with a flight mode, and calculating the optimal thrust output and angle parameters of each duct group by controlling a distribution matrix; and controlling the flight state of the ground effect aircraft according to the optimal thrust output and angle parameters of each duct group, and continuously collecting the flight parameters. The problem that in the prior art, the flight state of the ground effect aircraft is difficult to accurately control according to different flight mode working conditions under the three environments of water, land and air is solved.

The invention discloses a flight control method and system for a vertical take-off and landing tilting quad-rotor unmanned aerial vehicle, and aims to solve the technical problem of poor time-varying adaptability of a control system in a nacelle tilting transition stage. According to the method, in a rotor wing flight mode and a nacelle tilting transition mode, attitude angle deviation, deviation change rate and flight speed of the unmanned aerial vehicle are obtained in real time, a fuzzy inference engine is adopted to dynamically output basic control quantity based on a predefined rule base, and a final control instruction is generated in combination with pneumatic feed-forward compensation quantity based on speed to drive a pneumatic control surface. According to the method, fuzzy intelligent decision making and feed-forward dynamic compensation are fused, the limitation that traditional control depends on an accurate model is broken through, the control precision and adaptability of a transition stage are remarkably improved, overshoot is effectively restrained, the adjusting time is shortened, the robustness of a system under model parameter changes and external interference is enhanced, and the system reliability is improved. And a reliable technical guarantee is provided for full-mode flight of the tilt-rotor unmanned aerial vehicle.

The invention discloses a flight trajectory prediction method and system based on airspace information perception, and the method comprises the steps: obtaining historical aircraft trajectory information, and carrying out the multi-scale flight trajectory segmentation based on downsampling; carrying out aircraft flight mode correlation graph calculation on the aircraft trajectory information of different scales; performing high-order tensor graph neural network construction based on the flight mode correlation graph, and fusing trajectory information of different airplanes in the same airspace; acquiring historical wind speed and wind direction information, and fusing the wind speed and wind direction information with the aircraft trajectory information; and fusing the fusion results according to different scales, and outputting a predicted future aircraft trajectory. According to the method, sufficient information interaction of different airplanes in the same airspace can be ensured, and meanwhile, extra peripheral wind speed and direction information is fused as auxiliary features, so that the flight path is accurately predicted.

The present invention belongs to the field of aircrafts. Disclosed is a method for reducing the energy consumption of an aircraft, which method is applied to an aircraft and is used for controlling the aircraft to automatically align with an incoming wind direction, wherein flight modes of the aircraft include a vertical take-off and landing mode, a cruise mode and a transition mode. The method comprises: S1, providing a control system; and S2, providing a control apparatus, wherein the control system comprises a flight control module and a control module, and the control apparatus may send different instructions to the flight control module for controlling an aircraft to automatically align with an incoming wind direction.

This invention discloses a method for tiltrotor blade modal identification, belonging to the field of tiltrotor dynamics technology. It addresses the problem of being unable to measure blade modes under incoming flow conditions. The invention proposes a complete wind tunnel testing method, from blade control matrix calibration and empty hub adjustment to tiltrotor blade modal frequency identification and damping identification tests. This invention comprehensively considers wind tunnel testing methods for tiltrotor aircraft under different flight modes and under incoming flow conditions, solving the problem of conducting tiltrotor blade modal identification tests under wind tunnel conditions with incoming flow. Furthermore, by binding hydraulic cylinder excitation triggering with data acquisition system variables, it solves the problem of simultaneously acquiring hydraulic cylinder excitation frequency, displacement, and blade profile load, further improving the accuracy of blade modal identification and providing a technical approach for measuring the dynamic characteristics of tiltrotor blades.

The invention discloses an auxiliary control method and system for an autorotorcraft in the flight process, and relates to the technical field of the auxiliary control method for the autorotorcraft, and the remaining flight paths of the autorotorcraft are determined according to the flight path and the current position of the autorotorcraft. And determining a current flight state of the autorotorcraft according to each current flight parameter and flight mode of the autorotorcraft, and determining a first auxiliary control mode of the autorotorcraft in the remaining flight areas according to the current flight state, the plurality of flight routes of the remaining flight areas and the corresponding real-time weather events. Determining a flight influence factor from the identification of the flight event; and determining a second auxiliary control mode of the autorotorcraft in the next remaining flight area according to the flight influence factor, the plurality of flight routes of the next remaining flight area and the abnormal signal of the autorotorcraft, thereby improving the accuracy of the second auxiliary control mode of the autorotorcraft in the next remaining flight area.

This application discloses a method, device, electronic device, medium, and product for controlling a three-axis gimbal of a UAV. The method includes: upon receiving a control command from the UAV's three-axis gimbal, acquiring the UAV's flight status information and the current gimbal control mode; performing attitude calculation based on the flight status information to obtain the actual physical angles of each axis of the three-axis gimbal; calculating the angular deviation between each axis of the three-axis gimbal and the target angle specified in the control command based on the actual physical angles of each axis; determining the target control mode to be activated based on the angular deviation and the target angle; and when the target control mode differs from the current gimbal control mode, performing corresponding control on the three-axis gimbal based on the target control mode and the target angle. This method enables refined and adaptive control based on the gimbal's real-time attitude deviation, improving the accuracy and flexibility of control, without relying on switching the gimbal control based on the overall flight mode of the UAV.

The invention provides an unmanned aerial vehicle mode switching control method and system, and relates to the technical field of mode switching control, and the method comprises the steps: constructing a flight scene vector, and carrying out the fitness evaluation; if the flight mode adaptation coefficient is smaller than or equal to the flight mode adaptation threshold value, generating a mode switching decision; switching accident suppression compensation adjustment is carried out on the mode switching decision according to the flight scene vector; loss constraint optimization is carried out on the switching adjustment first group according to the switching loss evaluation model; and a switching propagation constraint condition is introduced, propagation optimization is carried out, a switching optimization strategy is obtained, and mode switching control is carried out on the unmanned aerial vehicle. According to the method and the device, the technical problem that the flight safety of the unmanned aerial vehicle is affected due to the fact that the unmanned aerial vehicle mode switching lacks fine control and is easy to cause instability at the switching moment in the prior art is solved, the flight scene vector is constructed and the mode switching decision is made based on the fitness evaluation, the stability of the unmanned aerial vehicle mode switching is improved, and the flight safety of the unmanned aerial vehicle is improved. Therefore, the flight safety is improved.

A multi-monocopter system is provided, including a plurality of monocopters. Each monocopter includes: a flight controller, disposed on a housing member, operable to control a flight of the monocopter in an individual flight mode and a flight of the plurality of monocopters collectively in a cooperative flight mode; a wing member; a thrust unit; and a magnetic connector coupled to the housing member. The magnetic connector is configured to be connectable to corresponding magnetic connectors of other monocopters of the plurality of monocopters via a magnetic force to operate in the cooperative flight mode. When in the cooperative flight mode during flight, the flight controller is operable to control a rotational speed of the plurality of monocopters collectively to produce a centrifugal force that exceeds the magnetic force for separating the plurality of monocopters connected via the magnetic force to convert the cooperative flight mode to the individual flight mode.

The invention relates to the technical field of aircraft power control, and discloses an artificial intelligence optimized vertical fixed wing power control method and system, and the method comprises the steps: obtaining the original airspeed data of an airspeed sensor, the ground speed data of a global positioning system and the acceleration data of an inertial measurement unit, and generating the ground speed of an aircraft based on the data fusion. Under the low-wind-speed condition, the ground speed of the aircraft is used as the reference airspeed, the difference between the original airspeed data of the airspeed sensor and the reference airspeed is continuously compared, and the sliding average value of the difference is calculated. When the sliding average value continuously exceeds the preset tolerance range, the method can identify that the airspeed sensor has continuous calibration drift. And then, according to the identified continuous calibration drift, performing real-time compensation on original airspeed data of an airspeed sensor to obtain calibrated airspeed data, and inputting the calibrated airspeed data into flight mode switching judgment logic to trigger an action instruction of a tilting mechanism.

The invention discloses a tilting rotorcraft vibration reduction system and method based on magnetorheological dampers, and relates to the field of wing vibration reduction. The central control module carries out flight mode recognition and vibration type judgment according to the signal data, adopts a fuzzy PID algorithm to carry out damping force parameter optimization and converts the damping force parameter into a control instruction; the magnetorheological damper execution module adjusts damping force according to the control instruction; the energy recovery module converts vibration mechanical energy into electric energy and stores the electric energy; the state feedback module collects a vibration reduction effect signal after vibration suppression, then the vibration reduction rate is determined through the central control module, and whether the vibration reduction rate is lower than a preset vibration reduction rate threshold value or not is judged; and if yes, the damping force parameter is corrected, the energy recovery efficiency is monitored, and if the energy recovery efficiency is lower than preset efficiency, the transmission ratio parameter is corrected, so that continuous vibration reduction and energy recovery in the whole flight process are achieved. The tilting rotorcraft can solve the problems that the tilting rotorcraft is slow in vibration reduction response, poor in effect and incapable of recycling energy in multiple flight modes.

An aircraft control method, and an aircraft, a manipulation device and a computer-readable storage medium. The method comprises: when it is detected that an aircraft has been switched from a first flight mode to a second flight mode, determining a target control strategy (S101); and then controlling the aircraft on the basis of the target control strategy (S102), wherein the target control strategy is used for controlling the aircraft to smoothly transition to the second flight mode. By means of the method, sudden attitude tumbling of an aircraft or erroneous operations caused by delayed user response can be avoided, thereby improving safety.

A example method includes accessing request data for a request for an available aircraft to fly, wherein the request is from a user device associated with a user; computing an identifier of an aircraft of a fleet of aircraft to fulfill the request, the aircraft being operable in an uncrewed flight mode compliant with a first flight standard or in a crewed flight mode compliant with a second flight standard, the first flight standard corresponding to regulations for beyond-visual-line-of-sight uncrewed flight and the second flight standard corresponding to regulations for crewed flight; based on the request data and the identified aircraft, computing routing data for the identified aircraft that identifies a planned route for the aircraft; and based on the routing data, selectively causing the aircraft to operate in the uncrewed flight mode or in the crewed flight mode for at least a portion of the planned route.

A hybrid air motor aircraft capable of long distance flight by efficient operation of an engine and a battery and capable of reducing discomfort by reducing noise according to a flight environment. The hybrid air motor aircraft includes an engine and a generator, a battery and a drive motor electrically connected to the generator, a first propeller connected to the drive motor and a second propeller connected to the generator through a clutch, and a controller that controls driving of the engine, the clutch, and the drive motor based on flight factors including at least one of a flight mode of the hybrid air motor aircraft, a required power, a battery charge level, and a surrounding flight environment.

The invention provides a multi-mode adaptive switching control method for an unmanned aerial vehicle and the unmanned aerial vehicle. The method comprises the following steps: collecting flight parameter information of the unmanned aerial vehicle through a multi-source sensor; the flight mode of the aircraft is judged in real time based on the flight parameter information and a dynamic threshold value, wherein the dynamic threshold value is a threshold value dynamically adjusted through a machine learning algorithm according to the flight parameter information; if it is detected that the flight mode of the aircraft is switched, rotor wing thrust and fixed wing lift force are distributed based on a transition factor of a nonlinear function, and corresponding rotor wing rotating speed and fixed wing control plane deflection angle are calculated and output based on a gain scheduling mechanism. Through the scheme, the thrust and lift force in the flight process of the aircraft can be reasonably distributed, the stability and adaptability of modal switching control are improved, and safe and reliable flight is guaranteed.

The invention discloses a flying wall-climbing system and method for bridge crack detection, and belongs to the technical field of bridge detection. The system comprises a flight module, a wall climbing module, an image acquisition module and a control module, wherein the flight module adopts a four-rotor system to realize large-range rapid inspection; the wall climbing module generates negative pressure adsorption force through reverse rotation of a propeller, so that equipment is tightly attached to the surface of a bridge for fine detection; the image acquisition module is provided with a high-definition camera and a crack sensor, and crack parameters are accurately measured; the control module coordinates the switching between the flight mode and the wall-climbing mode. When the equipment works, a crack area is globally scanned and positioned through the flight mode, then the wall-climbing mode is switched to carry out close-range fine detection, and data is returned in real time through the wireless transmission module. According to the invention, the problems of low efficiency, limited coverage range and insufficient precision of a traditional detection method are solved, and high efficiency, precision and automation of bridge crack detection are realized.

The application discloses a risk identification method and an electronic device, and relates to the field of information security, and comprises the following steps: when the electronic device receives a user operation of setting a specific scene, for example, setting call forwarding, setting a do-not-disturb mode or setting a flight mode, acquiring first information, performing risk identification according to the first information, and outputting risk warning information in the case that it is determined that there is a risk operation. The first information comprises at least one of telephone number information and environment information in the specific scene. The electronic device may face or be suffering from network risk operations, property losses, information leakage and other problems when setting the specific scene. In the scheme, when the user sets the specific scene, the electronic device acquires the telephone number information and / or the environment information in the specific scene to perform risk identification to determine whether there is a risk operation in setting the specific scene, and timely performs risk warning in the case that it is determined that there is a risk operation, thereby improving the safety of the user in using the electronic device.

The invention relates to a hovercar and a pedal device thereof. The pedal device comprises a first pedal mechanism and a second pedal mechanism. The first pedal mechanism is used for controlling power output when working in the ground mode, and the first pedal mechanism is used for controlling yaw angle output in the first direction when working in the flight mode. The second pedal mechanism is used for controlling braking force output when working in the ground mode, the second pedal mechanism is used for controlling yaw angle output in the second direction when working in the flight mode, and the second direction is opposite to the first direction. According to the hovercar and the pedal device thereof, the pedal device can be adaptively adjusted to the ground mode or the flight mode according to the working mode of the hovercar, and the function suitable for different working modes of the hovercar is achieved. Therefore, the consistency with a traditional automobile control mode can be kept, and the requirement for flight control can be met. And the pedal device integrates various control functions, the structure of the device is simplified, the production cost is reduced, and meanwhile control can be facilitated.

The control method for a drone with multiple degrees of freedom flight modes according to the present invention includes: a fuselage section equipped with a battery, the forward direction of which is set as the x-axis; multiple rotors, four or more arranged around the fuselage section, each rotor having its rotation axis aligned in the z-axis direction; an x-axis tilting mechanism section for tilting the multiple rotors about axes parallel to the x-axis; a y-axis tilting mechanism section for tilting the multiple rotors about axes parallel to the y-axis; a first drive motor section for driving the y-axis tilting mechanism section; a second drive motor section for driving the x-axis tilting mechanism section; and a control section for controlling the first rotor, the second rotor, the third rotor, the fourth rotor, the first drive motor section, and the second drive motor section to realize multiple flight modes.

This invention belongs to the field of aircraft and discloses a method for reducing the energy consumption of aircraft. It is applied to aircraft to control the aircraft to automatically align with the incoming wind direction. The flight modes of the aircraft include vertical take-off and landing mode, cruise mode, and switching mode. The method includes S1: providing a control system; S2: providing a control device; the control system includes a flight control module and a control module; the control device can send different commands to the flight control module to control the aircraft to automatically align with the incoming wind direction.

This invention relates to the field of drone deception technology, and discloses a system and method for preventing autonomous drone flight. The method continuously monitors the drone's flight status data stream to identify the current flight mode type; based on the identified flight mode type, it dynamically extracts a set of control parameters from the drone's navigation system; it constructs an interference activation signal sequence using the control parameter set, performs time-series analysis on the interference activation signal sequence to locate parameter change event points; it divides the parameter change event points into intra-mode event points and inter-mode event points, thereby synthesizing flight path deviation parameters; it generates deception control parameters based on the flight path deviation parameters, and executes the deception control parameters to complete the deception action. This invention, by accurately identifying the drone's flight mode and generating targeted deception control parameters, achieves effective interference and path deviation control of the drone's autonomous flight, providing a new technical means for drone management.

An aircraft is disclosed. The aircraft includes a first pair of wings, each wing in the first pair of wings including one or more actuating flaps configured to move to facilitate the aircraft transitioning between a forward cruise mode and a vertical hover mode, and operating in one of the forward cruise mode or the vertical hover mode. The aircraft further includes a second pair of wings, and one or more propellers coupled to the second pair of wings and oriented horizontally to provide upward lift.

The application discloses a heavy-load long-endurance tilting rotor unmanned aerial vehicle. The unmanned aerial vehicle comprises a wing frame for supporting and tilting, unmanned wings installed on symmetrical two sides of the wing frame, a cargo hold installed on the lower part of the wing frame and used for loading goods, and an unmanned aerial vehicle hydraulic system installed on the cargo hold and used for controlling the unmanned wings. The unmanned aerial vehicle can realize vertical take-off and landing, hovering and fast level flight, is easy to control the moving direction and has strong environmental adaptability. The unmanned aerial vehicle has simple structure, low take-off requirement, small wind resistance, fast level flight speed, low energy consumption and long endurance, so that the voyage and load can be increased. The wing frame overall tilting system has low structural complexity, airflow disturbance is reduced, and the safety of flight mode conversion can be improved.