208 results about "Fly control" patented technology

The invention discloses an unmanned autonomous cluster flight control method based on a bionic alert mechanism, which is applied to the field of unmanned autonomous cluster control, and is characterized in that a W-MSR algorithm and a dynamic weighted bionic alert mechanism are fused, the W-MSR filters and eliminates extreme values of neighbor individuals, the dynamic weighted bionic alert mechanism strengthens input from informed individuals, and the dynamic weighted bionic alert mechanism is used for improving the robustness of the unmanned autonomous cluster flight control. And meanwhile, the influence of suspicious individuals is inhibited, so that the local information aggregation degree is effectively improved, and group splitting can be prevented. Different from a scheme depending on explicit attacker recognition, the method can improve the motion accuracy and connectivity of the unmanned autonomous cluster in a confrontation environment by probabilistically suppressing the influence of suspicious individuals and amplifying a consistent signal, provides a new idea for improving the security of a swarm intelligence system, and has a wide application prospect. Damage of malicious individuals to the cluster is effectively defended, and robustness and recovery capability of the cluster in a complex environment are improved.

Disclosed here are unmanned aerial vehicle embodiments including some embodiments having a fuselage, tail, and wings including example embodiments with an adaptable payload section, alternatively or additionally, modular flight surfaces including tail, wings and motor, alternatively or additionally the vehicle configured for short landings with reversible thrust, alternatively or additionally, the unmanned aerial vehicle configured with direct connection to moveable flight control surfaces.

Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a system of an aircraft is disclosed, configured to determine one or more desired commands for the aircraft, retrieve engine information for at least one electric propulsion unit (EPU) of a plurality of EPUs of the aircraft, wherein the engine information includes at least one time-based metric for temperature associated with the at least one EPU, generates control commands based on the received engine information, and controls effectors according to the generated control commands to meet the desired commands of the aircraft.

The invention discloses a bionic butterfly based on a flapping wing structure, and belongs to the field of flapping wing type aircrafts, a butterfly main body comprises a rack, two motors assembled with speed reduction groups, two couplings, two wings and two wing connecting pieces; the wing connecting piece comprises connecting parts and a transmission shaft which are connected with each other, and the two wings are respectively fixed on the two connecting parts; the rack is T-shaped, longitudinal mounting holes matched with a transmission shaft in shape are formed in the two ends of the transverse part of the rack, and semicircular fixing grooves matched with a motor in shape are formed in the two sides of the tail end of the longitudinal part of the rack; the two transmission shafts are respectively mounted in the two mounting holes; the two motors are respectively bonded in the two fixing grooves; one ends of the two couplings are connected with the output ends of the two speed reduction sets respectively, and the other ends of the two couplings are connected with the two transmission shafts respectively. The flapping wing type bionic butterfly provided by the invention is small in size and light in weight, and more efficient flapping wing driving and more stable flight control can be realized.

The invention provides a modular free-combination rotor unmanned aerial vehicle and a combination method, and the unmanned aerial vehicle comprises a plurality of independent rotor unmanned aerial vehicle units, and each rotor unmanned aerial vehicle unit comprises a fuselage and a rotor; a battery, a motor, a communication module and a power control module are arranged in the machine body; a standard socket is arranged outside the fuselage and used for being fixedly connected with other rotor wing unmanned aerial vehicle units or rods with the same interfaces, and sharing of power supply and communication is achieved through the standard socket. The power control module dynamically adjusts rotor power distribution in real time according to the form of the combined unmanned aerial vehicle, and the communication module automatically establishes a master-slave control relation after combination to achieve unified coordination of flight control. According to the technical scheme provided by the invention, through free combination of the modular rotor unmanned aerial vehicle units, a specific unmanned aerial vehicle can be quickly formed, the purchase and use cost is reduced, and the flight stability and safety are improved.

The invention discloses an intelligent cleaning unmanned aerial vehicle for high-rise building curtain wall maintenance and a cleaning method of the intelligent cleaning unmanned aerial vehicle. The cleaning method comprises the steps that data such as wind speed, temperature and humidity are detected in real time through a sensor system, and a flight control unit dynamically adjusts the flight path and attitude according to the information. The image recognition technology is used for recognizing the stain type and distribution of the building curtain wall, generating a cleaning path and adjusting the working mode of the cleaning module. And the spraying and cleaning modes are automatically adjusted according to the types of stains. The intelligent calculation module monitors the cleaning effect in real time, and feedback information is used for adjusting cleaning parameters. Meanwhile, the flight control unit plans a flight path to ensure that obstacles outside the building are avoided; according to the intelligent cleaning unmanned aerial vehicle for high-rise building curtain wall maintenance and the cleaning method thereof, the defects in the prior art are overcome, the intelligent cleaning unmanned aerial vehicle has the advantages of being high in wind resistance, intelligent in cleaning, high in endurance and high in efficiency, and automatic cleaning of the high-rise building curtain wall is achieved.

Unmanned and remotely controlled airship constituted from system of multirotor combined with inflatable envelope. The airship may be lifted / powered by a power system comprising three or more rotors. In some embodiments, the airship may be constructed using rods, connectors, the main system / control box and the rotors. The airship system may have a systemic symmetry for weight distribution and flight control and may be, for example, a symmetric ellipsoid envelope / blimp.

An automated control system for a glider towed by a tug employs a sensor system (e.g., cameras mounted on at least one of the aircraft) to determine the relative position and velocity of the glider. A controller determines corrections to the flight characteristics of the glider in response to this data from the sensor system to maintain the glider on the surface of a limit sphere extending behind the tug with a predetermined radius based on the length of the tow cable. An interface to the flight controls of the glider maintains the desired flight characteristics of the glider provided by the controller.

The embodiment of the invention discloses an unmanned aerial vehicle soft fence control method, and the method comprises the steps: obtaining personnel state information, generating environment risk distribution information based on the personnel state information, and carrying out the time alignment processing of the environment risk distribution information, so as to obtain the risk distribution information corresponding to the current moment of an unmanned aerial vehicle; acquiring a current flight state of the unmanned aerial vehicle, predicting a motion state of the unmanned aerial vehicle in a future period of time, and determining a risk assessment result according to the motion state and the risk distribution information; performing constraint processing on the operator control input according to the risk assessment result to generate a safety control instruction; inputting the safety control instruction into the flight controller to execute flight control, and triggering a safety protection strategy when the risk degree meets a preset condition; the unmanned aerial vehicle can be effectively prevented from entering a crowded or high-risk area, and the flight safety and controllability of the unmanned aerial vehicle in a complex personnel environment are improved.

The invention discloses a self-coupling PID (proportion integration differentiation) flight control method of a rudder-controlled transverse-row type rotor unmanned aerial vehicle based on dynamic multi-dimensional heterogeneous fuzzy logic, and belongs to the technical field of flight control of rudder-controlled transverse-row type rotor unmanned aerial vehicles. A flight control system architecture of the self-coupling PID flight control method is composed of three core modules: (1) a dynamic multi-dimensional fuzzy logic coupling PID controller (DMHFL-SCPID); (2) control instruction distribution; and (3) a six-degree-of-freedom dynamical model of the rudder-controlled transverse rotorcraft. According to the control algorithm, input and output dynamic parameters of a system are analyzed in real time, and four-dimensional flight control quantities (roll, pitch, yaw and height instructions) are generated. A control distribution strategy based on the aerodynamic characteristics of the rotor converts the instructions into actuating quantity of an actuating mechanism, and flight attitude adjustment is realized by changing aerodynamic load distribution of a rotor system, so that the unmanned aerial vehicle is guided to realize accurate tracking along a predetermined flight path.

An inceptor apparatus for an aircraft comprises a primary inceptor member provided in the form of a stick member having a grip portion, at which the stick member can be gripped by a pilot's hand, and a secondary inceptor member provided at an upper portion of the primary inceptor member and having an actuating portion, at which the secondary inceptor member can be manually actuated by a pilot's thumb. Both inceptor members have associated a respective sensor assembly which is provided to generate electronic flight control signals or commands in response to at least one of i) pivoting movements of the respective inceptor member around each of two independent maneuvering axes associated to the inceptor member, ii) forces acting on or via the respective inceptor member in pivoting directions with respect to each of the maneuvering axes, and iii) lateral flexing or bending of the respective inceptor member.

The invention provides a solid sounding rocket landing point control guidance method which comprises the following steps: calculating a geocentric angle between a rocket depletion point and a target landing point, the speed of the rocket depletion point and the to-be-increased speed of the target landing point of the rocket according to current real-time parameters of the rocket; taking the target drop point of the rocket as a constraint, and calculating a theoretical program angle of the rocket according to the depletion point speed of the rocket and the to-be-accelerated speed of the target drop point of the rocket; the actual pneumatic influence and the earth rotation influence are considered, the theoretical program angle of the rocket is corrected, and the actual program angle of the rocket is obtained; and the actual program angle is issued, and guidance calculation is completed. According to the method, the theoretical program angle is iteratively calculated in real time on the rocket computer to complete flight control of the rocket, it is guaranteed that the drop point precision meets the requirement, the problems that a traditional perturbation guidance method is large in calculation amount and poor in adaptability are solved, and high-precision and low-calculation-complexity real-time guidance is achieved.

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 present disclosure relates generally to flight control of electric aircraft and other powered aerial vehicles. In one embodiment, a method is disclosed, comprising: receiving a descent rate command from a pilot input device, determining a proximity of each propeller of at least two propellers to a vortex ring state; and controlling the aircraft's descent rate to be less than the commanded descent rate when at least one of the at least two propellers is within a first threshold proximity to the vortex ring state.

Aspects of the present disclosure generally relate to systems and methods for flight control of aircraft driven by an electric propulsion system and in other types of vehicles. In some embodiments, an aircraft is disclosed, the aircraft comprising: at least one electric propulsion unit; at least one sensor configured to measure at least one aircraft condition; and at least one flight control computer configured to dynamically vary at least one torque command for the at least one electric propulsion unit based at least on the at least one aircraft condition; wherein the at least one electric propulsion unit is configured to generate thrust based on at least one dynamically changed torque command.

The application discloses a kind of based on hybrid power eVTOL unmanned aerial vehicle control method and related device, its method includes: flight control computer is based on flight control instruction obtains the flight phase that eVTOL unmanned aerial vehicle currently is in, the flight phase includes vertical take-off and landing phase, overdrive mode phase, cruise phase and emergency mode phase;The flight control computer indexes to the flight control strategy corresponding to the flight phase that eVTOL unmanned aerial vehicle currently is in;The flight control computer controls the turbine power generation system and / or the power battery pack based on the flight control strategy to N cruise electric drive unit and M vertical take-off electric drive unit on the eVTOL unmanned aerial vehicle Power supply processing.In the embodiment of the application, turbine power generation system and power battery pack are connected in parallel to supply power for eVTOL unmanned aerial vehicle, while combining redundancy flight control system, so as to achieve optimization in voyage expansion and safety performance improvement.

The application is a divisional application of the original application with the application number 2021108483611. The application discloses a waterproof unmanned aerial vehicle. The unmanned aerial vehicle comprises a shell and a second sealing partition. A flight control cavity is formed in the shell. The second sealing partition is arranged in the upper shell of the shell and arranged in the horizontal direction. The second sealing partition divides the flight control cavity into an upper sealing cavity and a lower sealing cavity. The upper sealing cavity is provided with an upper opening for mounting components. A detachable cover plate assembly is arranged at the upper opening. The cover plate assembly seals the upper opening. The internal cavity of the unmanned aerial vehicle is divided by the sealing partition. The sealing partition blocks the diffusion of water into the internal cavity of the unmanned aerial vehicle, avoids the problem that water enters one cavity and then enters other cavities, and seals the battery mounting port by the battery sealing cover to prevent water from flowing in from the battery mounting port.

A vertical takeoff and landing vehicle which includes an allocation block that receives a set of desired forces or desired moments and a health metric associated with at least one of: (1) a motor controller or (2) a rotor that operates in a vertical takeoff and landing mode at least some of the time. A command signal is determined per a first manner that attempts to satisfy both the set of desired forces or desired moments and the health metric. If the command signal is unable to be determined in the first manner, a second manner is used that prioritizes flight control associated with one or more of a roll axis or a pitch axis over flight control associated with a yaw axis where the axes are mutually orthogonal. The command signal is output to the motor controller that controls the rotor using the command signal.

The invention relates to an aircraft system for suppressing movement of a structural flight element. The aircraft system includes a movable aircraft structure, a power source, a controller, a resistor, and a first transistor connected in series to the resistor. When the power source of the aircraft provides power, the controller controls the first transistor to prevent current from flowing through a terminal of the first transistor and through the resistor. Further, when the power supply of the aircraft does not provide power, the first transistor allows a current generated by a back electromotive force (EMF) voltage generated by movement of the movable aircraft structure to flow through a terminal of the first transistor and through the resistor.

The invention discloses a multi-rotor aircraft with lift-enhanced wings, which comprises rotor power devices, a fuselage for mounting airborne equipment and connecting the rotor power devices, and a pair of independent and controllable lift-enhanced wings, the high-lift wings are mounted on the fuselage; when the multi-rotor aircraft with the high-lift wings flies, a flight control algorithm controls the tilting angles of the high-lift wings according to the attitude and the flight speed of the aircraft, so that the high-lift wings are in a proper attack angle state, and proper lift force can be provided for the aircraft. The flying speed can be increased, the cruising ability is improved, and transportation and storage are convenient.

A method for controlling an aircraft with a rotary wing provided with a power plant comprising a plurality of engines, the aircraft comprising a human-machine interface controlling a control member capable of acting on a longitudinal acceleration of the aircraft. During the economy operating mode during which one of the engines does not supply power, the method comprises measuring a forward speed of the aircraft, and adjusting an authority of the human-machine interface over the longitudinal acceleration with a flight control computer as a function of the forward speed.

Aspects of the present disclosure generally relate to systems and methods for flight control of aircraft driven by an electric propulsion system, as well as other types of aircraft. In some embodiments, a flight control system of an aircraft is disclosed, the flight control system configured to: determine one or more desired commands for an electric aircraft; determining at least one reference command based on the desired command and one or more aircraft conditions; monitoring an energy state of a plurality of battery packs, wherein at least a first battery pack of the plurality of battery packs is electrically isolated from at least a second battery pack of the plurality of battery packs; adjusting the at least one reference command based on the monitored energy states of the plurality of battery packs; generating a control command for the plurality of actuators based on the adjusted at least one reference command; and controlling the plurality of actuators to satisfy the one or more desired commands of the electric aircraft according to the generated control commands.

The present invention relates to a flight control system for a VTOL aircraft (10) that defines an aircraft reference coordinate system having a roll axis (Xb), a pitch axis (Yb), and a yaw axis (Zb), wherein the flight control system comprises first and second manual control devices for inputting control commands by an operator, and a flight control computer connected to the first and second manual control devices and configured to output flight control commands based on the pivot positions of first and second stick members with respect to first to fourth control axes, wherein the first manual control device comprises a first stick member, the first stick member being pivotable around first and second control axes with respect to a first neutral position, and the second manual control device The system comprises a second stick member, the second stick member being pivotable around third and fourth control axes with respect to a second neutral position, and the flight control computer is configured to derive and output flight control commands for longitudinal motion control based on the pivot position of the first stick member with respect to the first control axis, for lateral motion control based on the pivot position of the first stick member with respect to the second control axis, for vertical motion control based on the pivot position of the second stick member with respect to the third control axis, and for directional motion control based on the pivot position of the second stick member with respect to the fourth control axis, while at least partially eliminating the interconnection between the individual directions of motion. The present invention further relates to a VTOL aircraft (10) having such a flight control system.

An improved inceptor includes a grip configured to move a shaft and a mechanical linkage coupling the shaft to a sensor. The inceptor also includes a redundant mechanical system that includes a second shaft movable by the grip and a second mechanical linkage coupling the second shaft to the sensor. Accordingly, movement of the grip is relayed to the sensor by two discrete mechanical systems. In examples, redundant mechanical systems can be provided for any of three or more rotational directions, e.g., roll, pitch, yaw, and / or the like.

Aircraft performance modification system including a center-of-gravity (CG) subsystem and processor system(s) operatively integrated with components of the aircraft. The CG subsystem is configured to adjust the location of the aircraft CG within, and at times outside, a range of CG locations specific to the aircraft. The processor system(s) is / are configured to manage and concurrently adjust the aircraft CG, aircraft flight controls settings, and aircraft engine power control settings to manipulate control forces about one or more axes of the aircraft, and for automatically or autonomously controlling adjustments to (i) the aircraft CG such that the CG location is within, and at times outside, the range of CG locations, (ii) movement and positions of aircraft flight control surfaces, and (iii) aircraft engine(s) output power, to reduce drag by providing / controlling aircraft configurations that result in adjusted drag, yielding flight performance improvements attributable to decreased drag, and to prevent a stalled condition.

A propulsion system includes a propulsion device and a flight control device. The propulsion device includes a motor. The motor includes a rotor magnet. The flight control device acquires a motor temperature. The flight control device acquires a motor current. The flight control device performs management processing for managing demagnetization of the rotor magnet using driving information such as the motor temperature and the motor current. The management processing includes processing of determining whether a state of the motor is in an abnormal region, a demagnetization region, or a general region. In the management processing, the motor current is limited according to which region the state of the motor is in.

This invention provides an amphibious, multifunctional remote sensing and monitoring drone for water environment, belonging to the field of water environment monitoring technology. It includes a drone body, a flight control module and a data transmission module mounted on the head of the drone body, a pre-reserved assembly slot at the bottom of the drone body, an electric actuator mounted in the assembly slot, a C51 microcontroller mounted inside the drone body, a battery mounted inside the drone body, and mounting bases mounted on all four sides of the drone body. This invention solves the problems of some current drones having remote sensing and monitoring capabilities but lacking water collection capabilities, and others having limited water collection methods that cannot simultaneously collect water from multiple layers without interference, and where surface impurities may clog water collection.

The invention discloses a flight control parameter read-write and synchronous configuration system and method, and belongs to the technical field of aircraft control, and the system comprises a parameter read-write interface module, a parameter analysis module, a synchronous driving module, a visual configuration module, a storage module and an interaction adaptation module. According to the method, parameters are read by calling a flight control parameter interface, the parameters are visually displayed in a standardized form after being analyzed, parameter writing is completed after a user configuration modification instruction is received, real-time synchronization of the parameters of a flight control end and a ground station UI end is achieved through a synchronous driving module, and local persistence and multiplexing of configuration are completed through a storage module at the same time. According to the invention, the existing flight control interface is reused, the interaction logic is optimized, unified read-write, real-time synchronization and visual configuration of flight control parameters are realized, the efficiency and usability of flight control parameter debugging are improved, and parameter management requirements of various flight control systems are met.

The application discloses a missile rudder deflection dynamic distribution method based on four-rudder control and belongs to the technical field of flight control. Compared with a traditional missile channel rudder deflection distribution mode, when distributing three channel rudder deflections of the missile, the application fully considers the sizes of the pitch channel and the yaw channel rudder deflections, and the roll channel rudder deflection is differentially distributed on four single rudders according to the relative sizes of the pitch channel and the yaw channel required rudder deflections. The distribution scheme can effectively improve the use rate of the rudder deflection, makes the three channels pay a large rudder deflection, improves the control precision of the missile and increases the flight stability. The application is simple in calculation, stable in performance and easy to realize in engineering.