590 results about "Flight control modes" patented technology

A hover aircraft employs an air impeller engine having an air channel duct and a rotor with outer ends of its blades fixed to an annular impeller disk that is driven by magnetic induction elements arrayed in the air channel duct. The air-impeller engine is arranged vertically in the aircraft frame to provide vertical thrust for vertical takeoff and landing. Preferably, the air-impeller engine employs dual, coaxial, contra-rotating rotors for increased thrust and gyroscopic stability. An air vane assembly directs a portion of the air thrust output at a desired angle to provide a horizontal thrust component for flight maneuvering or translation movement. The aircraft can employ a single engine in an annular fuselage, two engines on a longitudinal fuselage chassis, three engines in a triangular arrangement for forward flight stability, or other multiple engine arrangements in a symmetric, balanced configuration. Other flight control mechanisms may be employed, including side winglets, an overhead wing, and / or air rudders or flaps. An integrated flight control system can be used to operate the various flight control mechanisms. Electric power is supplied to the magnetic induction drives by high-capacity lightweight batteries or fuel cells. The hover aircraft is especially well suited for applications requiring VTOL deployment, hover operation for quiet surveillance, maneuvering in close air spaces, and long duration flights for continuous surveillance of ground targets and important facilities requiring constant monitoring.

The invention discloses a special photoelectric nacelle of a power patrol unmanned helicopter, which comprises an airborne part and a ground part, wherein the airborne part comprises a fixed part which is positioned in the upper part, a rotatable part which is positioned in the lower part and a servo control assembly; the rotatable part comprises a gyroscope stable rotating tower; the fixed part comprises an electronic control cabin; cables between the electronic control cabin and the gyroscope stable rotating tower are connected by a conducting slide ring which can support the gyroscope stable rotating tower to rotate by nx360 degrees; and the airborne part of the photoelectric nacelle is suspended on the helicopter by a vibration reducing device and communicated with a flight control system of the helicopter. The special photoelectric nacelle is a photoelectric task load with compact structure and high performance, can meet the requirement for remote power patrol, has self-stabilizing function and self-tracing function, can shoot a target to be traced from an image in real time, transmit the target to a ground control vehicle by a radio transmission system on an aerial carrier and is convenient for a patrol parson to directly master the scene condition to improve the efficiency of power patrol.

A unmanned plane automation detection target and tracking method is disclosed. An unmanned plane, a sonar distance detector installed on the unmanned plane, an illumination compensation module, an image de-noising module, a face detection module, a fuselage face identification module, a far-end face identification module, a target tracking module, a flight control module and a console module are included. The illumination compensation module carries out illumination compensation on an image. The image de-noising module carries out de-noising processing on the image. The face detection module carries out face detection on the received image. The fuselage face identification module identifies the detected face image and adds an identification result of the far-end face identification module. The far-end face identification module identifies the face image which can not be processed by a fuselage. The target tracking module tracks a target. The flight control module controls a movement track of the unmanned plane. The console module is manually monitored and emits various kinds of commands.

The invention relates to the field of unmanned aerial vehicles, in particular to a full-automatic unmanned aerial vehicle control system. The system, which is characterized in that: a ground control system comprises a main control system mainly comprising a central controller, a main control computer, the internet network and a central antenna, a user computer as a human-computer interactive interface, and a GPS navigation system; a vehicle-mounted flight control system of the unmanned aerial vehicle is provided with an aerial vehicle controller, a networking antenna, a GPS antenna, a DSP, a navigation camera, and a sensor; and the main control system of the ground control system gets the remote internet control authority, the main control computer inputs a signal to the central controller, the signal is processed by the central controller, and then the remote wireless communication and control of the vehicle-mounted flight control system are achieved through the antennas. Compared with the prior art, the system has the advantages of having high automation degree, realizing various flight missions of the unmanned aerial vehicle, and being applied to low altitude remote sensing, aerial photography, monitoring, photography measurement, videography, communication data retransmission and the like.

The invention discloses an unmanned helicopter relay data link system. The unmanned helicopter relay data link system comprises a relay unmanned helicopter module, a base station module, a ground station module, a remote controller module, a wireless transmitting module, a wireless receiving module, a relay unmanned helicopter main controller module and a target unmanned helicopter main controller module. The invention also discloses a control method for controlling the unmanned helicopter relay data link system. The control method comprises the following steps: 1, outputting the parameters of a controller and transmitting the output parameters to the base station module via a UDP network protocol by the ground station module; 2, encapsulating acquired flight control data and task data into one data frame by the base station module; 3, extracting the flight data and the task data in a data part respectively; 4, comparing the destination address of the data frame with the local address of an unmanned helicopter; 5, acquiring sensor data; and 6, after the base station module receives downlink data packets, forwarding the received downlink data packets to the ground station module. The unmanned helicopter relay data link system has the advantages of low communication cost, high transmission efficiency, high generality and the like.

The invention discloses an ARM (advanced RISC (reduced instruction set computer) machines) and FPGA (field-programmable gate array) based navigation and autonomous flight control system for an unmanned helicopter. The system comprises a PC (personal computer), an integrated navigation subsystem, a power supply module and controllers, wherein the integrated navigation subsystem comprises a sensor group; the sensor group comprises a GPS (global positioning system), a gyroscope, an accelerometer, a magnetoresistive sensor, a barometric altimeter and a sonar altimeter; the controllers include a main controller and a steering engine controller; the main controller adopts an ARM microprocessor to operate the integrated navigation algorithm and flight control PID (proportion integration differentiation) algorithm and simultaneously completes data acquisition of the GPS, the barometric altimeter and the sonar altimeter; and the steering engine controller adopts an FPGA to realize data acquisition of the gyroscope, the accelerometer and the magnetoresistive sensor and transfers the data to the main controller via a concurrent bus to carry out attitude calculation and control operation on the unmanned helicopter. With the unmanned helicopter as a carrier, the hardware environment of a whole set of flight control system integrating study of the aircraft navigation and control theory problem, data acquisition, information transfer and embedded control is set up.

The invention provides a flight control method and a device for an unmanned aerial vehicle, and belongs to the field of aerial vehicles. The method comprises steps of obtaining the current position of the unmanned aerial vehicle; obtaining division information of control regions, wherein each of the control regions corresponds to a control parameter; determining the flight restriction parameter of the current position according to the control parameter of the control area where the current position is if the unmanned aerial vehicle is in the divided control region; and performing flight control for the unmanned aerial vehicle according to the flight restriction parameter of the current position. According to the invention, flight states of the unmanned aerial vehicle can be controlled according to flight restriction rules of the control regions, thereby satisfying different flight restriction requirements of the control regions.

A flight control operation of a reference aerial vehicle is performed. For example, an image captured by an image sensor of the reference aerial vehicle is received. A target is detected in the image. A three-dimensional relative location of the target with respect to the reference aerial vehicle is determined based on the image. The flight control operation is performed based on the three-dimensional relative location of the target with respect to the reference aerial vehicle.

The invention discloses an unmanned helicopter flight control system which comprises an onboard unit and a ground control station unit. The onboard unit comprises a flight control computer, a sensor module, a servo control module, a wireless transmission module, a remote-controlled receiver and an actuating mechanism. The ground control station unit comprises a measuring and controlling terminal having a wireless transmission function; the measuring and controlling terminal comprises a PC (personal computer) console and a remote control. The system comprises an automatic control mode and a manual control mode and has the advantages of being small in size and light in weight. The invention further discloses a control method of the unmanned helicopter flight control system, and the method includes that output quantity is calculated and controlled by a closed-loop control algorithm to control the actuating mechanism to operate. By the method, complexity in manipulating a model helicopter is reduced, and the helicopter is enabled to have the basic capacity in automatic flight. Therefore, quite good society and economy benefits are achieved.

The invention discloses a flight control method of a small unmanned helicopter. According to the method, a flight execution unit, a state sensor unit, a parachute unit, a flight control unit, a ground control terminal and a remote controller unit are adopted, so that the effects of obstacle-avoidance flight, water-surface-avoidance landing, self-adaptive flight attitude control, power monitoring, automatic parachute opening in case of engine stop, flight control through a flight control panel, flight path generation through a signal panel and the like can be achieved. The flight control method of the small unmanned helicopter has the advantages that the self-adaptive obstacle-avoidance flight capacity of the small unmanned helicopter can be improved; the small unmanned helicopter can operate in a beyond visual range according to a preset instruction, can slowly land by using a parachute in an emergency of the engine stop in the air, is protected from being damaged, and can automatically avoid a water surface during landing.

The invention discloses a comprehensive shelter system of an unmanned aerial vehicle. The system comprises a truck, a subsection shelter, unmanned helicopters, a ground command measurement and control station, an automatic takeoff / landing lifting control system, a maintenance safeguard system and a power supply system, wherein the ground command measurement and control station is positioned at the front part of the subsection shelter for performing the flight control and the task deployment for the unmanned helicopters; the automatic takeoff / landing lifting control system is a launching platform of the unmanned helicopters; and the maintenance safeguard system comprises an automatic mixed refueling system and a storage and transportation locking system, and is used for replacing equipment of the unmanned helicopters and repairing, maintaining and fixing the unmanned helicopters in the shelter. All the systems are integrated in the comprehensive shelter, so that the comprehensive shelter system has such functions as maneuvering storage and transportation, takeoff and landing, task deployment, command control and on-site maintenance and safeguard of the unmanned helicopters, has the characteristics of high integration degree, quick response, strong maneuvering performance and convenience for transportation deployment, and can efficiently and quickly finish the task deployment of the unmanned helicopters.

The invention discloses a low-altitude airship flight control system and a flight control method thereof, belonging to the technical field of aircraft control. The system comprises a front-end data acquisition and processing subsystem, a navigation and flight control and state monitoring subsystem, a rear-end driving execution module subsystem and a flight application subsystem, wherein the front-end data acquisition and processing subsystem is connected with sensing equipment and used for transmitting acquired flight environment and airship state information, the navigation and flight control and state monitoring subsystem is connected with an airship navigation sensor and the rear-end driving execution module subsystem and used for transmitting navigation and flight control information,the rear-end driving execution module subsystem is connected with an airship execution controller and used for transmitting empennage steering engine pulse width modulation signals, propelling rotating speed control voltages and valve blower switch information, and the flight application subsystem is connected with a ground station and used for transmitting flight control instructions and telemetry parameter information through a data radio. The low-altitude airship flight control system disclosed in the invention is suitable for various civil and military systems.

The invention discloses a flight control method for an unmanned aerial vehicle. The method includes the first step of collecting coordinate information transmitted by a platform for landing and taking-off of the unmanned aerial vehicle, the second step of targeting the landing platform according to the collected coordinate information, the third step of controlling the unmanned aerial vehicle to fly to the place near the targeted platform and then collecting image information of guiding marks, used for guiding the unmanned aerial vehicle to land at the position and orientation on the platform, of the platform, and the fourth step of controlling the unmanned aerial vehicle to land onto a supporting device prearranged on the platform according to the guiding marks and distance information detected by a prearranged distance sensor. The invention further discloses an unmanned aerial vehicle control device. Through the flight control method and device for the unmanned aerial vehicle, the control accuracy of the unmanned aerial vehicle is improved, the weight of the unmanned aerial vehicle is reduced, and the flight time is prolonged.

The invention discloses flight control, permission and safety maintenance methods, flight permission and safety maintenance devices, a server and an aerial vehicle. The flight control method comprises when the unmanned aerial vehicle flies, a specific flight area which the unmanned aerial vehicle is entering is determined, and the unmanned aerial vehicle needs a flight permission to enter the specific flight area; application information and information of the specific flight area are sent to the server, the application information applies for the flight permission, and the information of the specific flight area indicates the specific flight area; and when the flight permission from the server is received, a flight instruction is sent, so that the unmanned aerial vehicle enters the specific flight area according to the flight instruction. The flexibility of a flight route of the unmanned aerial vehicle can be improved.

The invention discloses a flight control method, and the method is used for an unmanned plane. The method comprises the steps: obtaining the data information detected by a plurality of sensors (14) disposed on the unmanned plane; carrying out the fusion of the data information, so as to enable the data information to be unified in time; and calculating the relative height of the unmanned plane to a ground object according to the data information after fusion. The invention also relates to the unmanned plane and the flight control system.

A blade actuation system comprises at least one motor coupled to a rotor blade for changing the pitch angle of the rotor blade. The motor is configured to wirelessly communicate with at least one flight control computer to modulate the pitch angle. At least one generator may be mounted on a rotor shaft to generate power during rotation of the rotor shaft. The generator may provide power to the motor. The flight control computer is operative to provide control signals to at least one of the generators and motors for regulation thereof. The flight control computer, motor and generator may be configured to wirelessly communicate with one another.

The invention discloses a flight control method for a multiple-rotor-wing aircraft. The multiple-rotor-wing aircraft comprises multiple rotor wing mechanisms; the multiple rotor wing mechanisms provide power for the multiple-rotor-wing aircraft. The flight control method comprises the following steps: detecting whether the output power of the multiple rotor wing mechanisms is abnormal or not; if detecting that the output power of partial rotor wing mechanisms is abnormal, adjusting the output power of other rotor wing mechanisms, so as to enable the multiple-rotor-wing aircraft to keep balanced. The invention further discloses a flight control system for the multiple-rotor-wing aircraft. Through the above mode, additional power can be saved to stabilize the attitude, therefore, that the multiple-rotor-wing aircraft lands in a loss minimization manner is ensured, and the damage of the parts of the aircraft and damage to vehicles and people on the ground, which are caused by direct crash of the aircraft are avoided.

A flight control system for an aircraft is configured for receiving command signals representing commanded values of a location of a geospatial point and a radius about the geospatial point for defining a circular groundtrack. A sensor determines a geospatial location of the aircraft and provides a location signal representing the location of the aircraft. A controller for commanding flight control devices on the aircraft controls the flight of the aircraft and is configured to receive the command signals and the location signal. The controller uses the command signals and location signal to operate the flight control devices to control the flight of the aircraft for directing the aircraft generally toward a tangent point of the circular groundtrack and then maintaining a flight path along the circular groundtrack.

Control systems and methods of use provide for fully automated phases of flight of an aircraft. Such fully automated phases include takeoff, cruising flight, and landing without the need for operator input or other operator intervention. Control systems and methods also provide for self-limited compliance with an operators desired deviation from a predetermined flight path, as well as automatic contingency response to non-normal conditions. Onboard and / or ground-based operators may cooperate with the control system in order to control the associated aircraft. Furthermore, an operator need not have any flight skill in order to affect changes in the flight path or other aspects of flight control.

A flight control system and method for controlling the vertical flight path of an aircraft, the flight control system includes a stable decoupled model having a decoupled lateral equation of motion and a decoupled longitudinal equation of motion and a feedback command loop operably associated with the stable decoupled model. The feedback command loop includes a vertical flight path angle control law; an altitude control law; and a vertical speed control law.

The invention provides an agricultural plant protection unmanned aerial vehicle (UAV) planting control system which is composed of a vehicle-borne subsystem and a ground station subsystem. The vehicle-borne subsystem comprises a vehicle-borne GPS antenna (1), a vehicle-borne relative height detector (2), a vehicle-borne obstacle detector (3), and a vehicle-borne data returning and receiving system (4). The ground station subsystem comprises a ground station geographic information system (5), a ground station flight task planning and flight control system (6), and a ground station instruction receiving and sending system (7). According to the system of the invention, work currently needing vehicle-borne flight control is transferred to the ground, the air control part is only responsible for stability augmentation and obstacle detection, and a lot of path computation and flight control operation are managed and controlled by the ground in a unified manner. Therefore, the weight of the vehicle-borne system is reduced greatly, the difficulty in UAV developing is reduced, and the operation requirements of a variety of UAVs are satisfied effectively.

A flight control method for a drone, a drone, and a machine readable storage medium, the method comprising: controlling a vertical takeoff and landing fixed-wing drone to take off in a multi-rotor mode based on a one-key activation of a user, and automatically controlling the vertical take-off and landing fixed-wing drone to switch the flight mode from the multi-rotor mode to the fixed-wing mode and to fly in the fixed-wing mode after the vertical takeoff and landing fixed-wing drone flies to the designated altitude,; and, when the set landing condition is met, the vertical takeoff and landingfixed-wing drone automatically switches the flight mode from the fixed-wing mode back to the multi-rotor mode and drops to the designated position in the multi-rotor mode. It can realize that after asingle operation control of the vertical take-off and landing fixed-wing drone take-off, the vertical take-off and landing fixed-wing drone can complete the flight task autonomously and return to thedesignated position autonomously, so that the whole flight process is completed in one go, thus improving the user experience. At the same time, it can also reduce the occupation of the drone batterylife by manual operation.

A flight control system controls flight of an unmanned aerial vehicle by control signals of the unmanned aerial vehicle itself and from a ground facility. The unmanned aerial vehicle and the ground facility are each provided with at least one flight control unit (FCU) capable of controlling driving of an airframe actuator based on a sensor output signal from an airframe sensor. The at least one FCU on the unmanned aerial vehicle and the at least one FCU of the ground facility constitute a redundant system for flight control function. In the redundant system one of the at least one FCU on the unmanned aerial vehicle serves as a main unit. In the case where a malfunction has occurred in an FCU that performs flight control on the unmanned aerial vehicle, the ground facility is capable of causing another FCU to take over flight control function from the FCU.

An integrated fire and flight control (IFFC) system senses the actual engine torque of a rotary wing aircraft in successive real time intervals and compares the sensed interval values with one or more reference maximum torque limits for each of one or more prescribed maximum time intervals and, in the presence of an above limit actual torque for an above limit prescribed time interval, the IFFC automatically reduces the collective axis command.

The invention provides a flight control method based on battery monitor. The method is used for controlling the flight of an unmanned aerial vehicle. The method comprises the following steps: acquiring current remained power of the battery, current position and current height of an unmanned aerial vehicle according to the first set interval time; calculating the minimum electricity of flight according to the current position and the destination location of the unmanned aerial vehicle; calculating the minimum electricity of landing according to the current height of the unmanned aerial vehicle; calculating the first flight threshold electricity of the unmanned aerial vehicle according to the minimum electricity of flight and minimum electricity of landing; and comparing the first flight threshold electricity with the current remained electricity, and prompting a user to make a return voyage or land when the current remained electricity is less than or equal to the first flight threshold electricity. The invention further provides a battery monitor based flight control device. The device and the method can be used for well improving the flight efficiency of an unmanned aerial vehicle and avoiding occurrence of power down.

A method of controlling an aircraft in a turn without the use of a rudder by producing induced yaw. Induced yaw being produced by creating a net induced drag differential between an inboard wing to the turn and an outboard wing to the turn, whereby the net induced drag differential overcomes adverse yaw produced by the outboard wing.

A pilot flight control stick haptic feedback mechanism provides variable force feedback to the pilot flight control stick. The flight control stick is movable to a control position in a displacement direction. A motor control unit is operable to selectively supply motor feedback signals to a motor that is coupled to the flight control stick. The motor is responsive to the motor feedback signals to supply a variable feedback force to the flight control stick in a direction that opposes the displacement direction. A passive electromagnetic damping mechanism is electrically coupled to the motor and is at least selectively and passively supplies a non-braking damping force to the flight control stick.