491results about How to "Improve flight safety" patented technology

The invention discloses an unmanned perception based unmanned aerial vehicle route planning method for rapidly planning the vehicle driving route. According to the invention, based on the unmanned flight perception system, road video images around a target vehicle are photographed by utilizing an unmanned flight to be sent to a ground station; the ground station receives the video images and processes the video images so as to obtain the vehicle and road messages, route planning is carried out according to the vehicle position, and the route is transmitted to the unmanned aerial vehicle; and a computer module of the ground station calculates a flight control signal to control the unmanned aerial vehicle to follow the vehicle to proceed, and corrects the route in real time. According to the invention, based on an unmanned flight platform, the operation state is stable; and the road environment around the vehicle is photographed from a great height, the coverage area is wide, and the observed road traffic information is distinct and clear, so that the road distribution condition and the traffic condition around the target vehicle can be obtained rapidly, the reasonable route planning can be obtained, the route is more precise, and the road condition analysis is more timely and accurate.

A system for autonomously keeping an aircraft's station in a formation flight of a plurality of aircraft includes a navigation system configured to determine a position of an aircraft. A data link is configured to allow the aircraft to communicate data with at least one other aircraft in the formation flight of the plurality of aircraft. A sensor is configured to detect a presence of another aircraft within a predetermined distance of the aircraft. A processor is configured to provide control signals to the aircraft's autoflight system to keep the aircraft at a predetermined station relative to the other of the plurality of aircraft in the formation flight.

Systems and methods for UAV safety are provided. An authentication system may be used to confirm UAV and / or user identity and provide secured communications between users and UAVs. The UAVs may operate in accordance with a set of flight regulations. The set of flight regulations may be associated with a geo-fencing device in the vicinity of the UAV.

The invention provides a servo system for instructing a pan-tilt system of an unmanned aerial vehicle (UAV) by adopting head movement of an operator, belonging to the field of UAV control. The servo system is characterized in that the servo system comprises a head attitude sensor, a ground station, data radios, video radios and a UAV pan-tilt system capable of pitching and yawing, wherein the head attitude sensor is used for detecting the head movement of the operator; the ground station is used for computing the deflection command according to the head movement and sending the deflection command to the vehicle-mounted pan-tilt system via the data radios to ensure the vehicle-mounted pan-tilt system and a camera carried by the vehicle-mounted pan-tilt system to deflect towards the direction expected by the operator; the camera returns the shot videos to the ground station via the video radios and the ground station displays the shot videos in real time; and the operator corrects the deflection rate and direction of the vehicle-mounted pan-tilt system in real time according to the videos displayed by the ground station to ensure the camera to aim at the expected target all the time. By using the servo system, the operator can control deflection of the vehicle-mounted pan-tilt system by adopting the gut reaction of own head movement, and the servo system has the characteristics of being easy in operation and convenient use in and can obviously reduce the workload of the UAV operator.

A method for validating received positional data in vehicle surveillance applications wherein vehicles transmit positional data indicating their own position to surrounding vehicles. A a radio direction finding antenna arrangement of a receiving unit receives a signal carrying positional data indicating an alleged position of a vehicle, transmitted from a radio source. The bearing from the receiving unit to the radio source is estimated utilizing the radio direction finding antenna arrangement and the received signal. The distance between the receiving unit and the radio source is estimated based on the time of flight for a signal travelling there between at known speed. An estimated position of the radio source is calculated based on the estimated bearing and the estimated distance. A deviation value indicating the deviation / coincidence between the alleged position of a vehicle is determined according to the received positional data and the estimated position of the radio source.

The invention discloses a general aviation low-altitude monitor and service system comprising an area monitor and service system which is used for receiving flight information submitted by each aviation service station system and is in information interaction with an airspace management department; the aviation service station systems which are used for obtaining flight information of airspace of service stations and providing flight information for general aircrafts in the airspace of the service stations; general aviation airport control tower systems which are used for obtaining flight information of airport local airspace and providing flight information for general aircrafts in the airport local airspace; a motor command system which is used for obtaining flight information of airspace uncovered by the aviation service station systems and the general aviation airport control tower systems and providing flight service information for the general aircrafts in the airspace; a low-altitude flight service network system which is used for providing user interfaces for low-altitude general aviation flight personnel; and an airborne monitor service terminal which is used for obtaining real-time information of the general aircrafts.

An avionic system and ground station for aircraft out of route management and alarm communications composed of an avionic device, which is fitted onboard the aircraft, with a memory unit for storing the flight paths data, runways, orography, and obstacles; processors to compute the stored or received data, available from sensors monitoring the onboard situation. Processors will compute commands to be sent to the aircraft's autopilot to temporarily take over the aircraft control and return it to pre-set flight levels or spatial positions; communication devices suitable for transmitting the real time onboard situation to ground control stations when potentially dangerous events occur.

The invention discloses an active fault tolerance control method of a four-rotor aircraft based on a sliding-mode observer. The active fault tolerance control method is provided by considering that a performer may have faults when the four-rotor aircraft is in a state delay condition and combining the sliding-mode observer with sliding-mode control. The sliding-mode observer is designed, linear transformation is carried out on the system, faults of the performer are reconstructed on the basis of the ideal of equivalent error injection, compensation control is added into sliding-mode control by utilizing the reconstructed estimation value of the performer faults, and a complete active fault tolerance controller is formed. According to the invention, the sliding-mode observer is designed, the faults are reconstructed and estimated, online adjustment of the controller gain is realized, the provided control law is optimal, the control precision and response speed of flight of the four-rotor aircraft are effectively improved, and a design basis of the fault tolerance controller is provided for the complex four-rotor aircraft with performer faults. The method can be applied to active fault tolerance control for the four-rotor aircraft with time variation and time lag.

The invention relates to an unmanned helicopter three-dimensional positioning and mapping method based on laser detection and image recognition, which belongs to the technical field of application of unmanned aerial vehicles. A distance measurement sensor based on laser detection and image recognition, an altimetric sensor and a flight control computer are comprised, wherein the distance measurement sensor consists of a vehicle-mounted camera and a laser emitter and used for detecting the distance from the unmanned helicopter to obstacles around. The distance measurement sensor is used for detecting and measuring distance for the around environment of the unmanned helicopter by means of changing the angle of pitch and the angle of yaw. The altimetric sensor is used for measuring the flight altitude from the unmanned helicopter to the ground. The distance measurement data obtained from the measurement under different angles of altitude, angles of yaw and flight altitudes can realize three-dimensional synchronous positioning and mapping of unknown environment by the unmanned helicopter. In the invention, the around environment can be rapidly, simply and reliably detected during the flying by carrying the distance measurement sensor based on laser detection and image recognition on the unmanned helicopter.

Methods and systems for aircraft engine trend monitoring include periodically recording the outputs of engine-condition sensors and analyzing the results to examine piston-engine performance trends and predict the need for engine maintenance. Various analyses can be performed, separately or in parallel, including comparing the current parameter values with values recorded for that parameter in previous instances of similar operating conditions; comparing parameter values to predetermined nominal ranges; and detecting parameter values that exhibit trends over time that if followed would result in out-of-bound readings. Sensed parameter values can also be used to detect when recommended engine operating conditions are being exceeded. By using the results of the analyses to inform engine maintenance scheduling and provide alerts to the pilot and maintenance staff regarding recommended engine performance trends and / or operating condition exceedances, the methods and systems contribute to enhancing the level of safety that can be achieved despite significant maintenance-budget reductions.

The method in accordance with the invention is a method of providing a 3D emergency descent trajectory for aircraft comprising the steps of searching for at least one possible better trajectory allowing a secure continuation in relation to the relief and / or the surrounding conditions towards a homing point as soon as a situation requiring an unscheduled modification of the current trajectory occurs, wherein this trajectory is updated as a function of the alterations in the surrounding conditions, as a function of the information provided by the onboard sensors and / or outside information received.

The ground station full power takeover control system during the take-off and landing phase of the UAV belongs to the field of UAV technology, and is characterized in that it includes: UAV control department and ground station control department; among them, the UAV control department includes: airborne sensor Group, flight control computer, steering gear adapter, steering unit, downlink data link transmitter and uplink data link receiver; ground station control department, including: ground station, downlink data link receiver, uplink data link transmitter , take-off and landing platform and take-off and landing platform sensor group; during the take-off and landing stages of the UAV, the flight control computer uses the downlink data link to send the flight data to the ground station; the ground station uses the relative motion of the UAV and the take-off and landing platform relationship, continuously calculate the UAV control instructions, and manipulate the UAV through the uplink data link, so that it can complete take-off and landing under the full control of the ground station. The invention can improve the safety of the unmanned aerial vehicle in the take-off and landing stages, and expand its application occasions.

An illumination device and an aircraft having an illumination device which by a corresponding selection of the wavelength and of the irradiation angle prevents a person situated in the aircraft from becoming tired. The illumination device is arranged in an aircraft such that light given off by the illumination device can be irradiated onto the retinohypothalamic tract of a person who is present in the aircraft in a predetermined position, and the illumination device is designed to give off light at a predetermined wavelength, which light achieves the desired effect.

The invention relates to a vehicle environment sensing system and method based on an unmanned plane, and the system and method are used for quickly acquiring the road environment information around a vehicle. The sensing system comprises the unmanned plane and an earth station, the unmanned plane id connected with the vehicle through a mooring rope, the road surface is shot by the unmanned plane, and a video image is transmitted to the earth station; the earth station is arranged in the target vehicle, the earth station can process the video image to obtain the vehicle environment information, and the earth station also can calculate the flight control parameter and send the parameter to the unmanned plane to make the unmanned plane and the vehicle move together. The sensing method is based on the sensing system, the unmanned plane takes off and hovers above the vehicle, the unmanned plane establishes a communication for sensing the environment and transmits the video image to the earth station, the earth station processes the video image, calculates the vehicle environment information and transmits the information to the vehicle, and the earth station calculates the flight control parameter and transmits the parameter to the unmanned plane. According to the invention, the system can perform the wide area observation in the direction vertical to the vehicle plane direction, the coverage is wide, the road environment information around the target vehicle can be easily sensed, and the distance between the objects in the image can be precisely calculated.

A safe lander consists of a flight airplane, transducer multi-path multiplexing receiver and emitter set on said airplane, digital processor / computer of land based simulator, flight control unit of land based airplane simulator, remote navigation electronic interface unit, land based airplane simulator, unique airplane identification ID and configuration unit, analysis unit of land based processing station, two-way RF communication unit of space to ground and ground to space, and remote pilot display set on land based simulator.

The invention discloses a multi-rotor aircraft driven by duct lift fans with diversion helms. The multi-rotor aircraft comprises the multiple duct lift fans with diversion helms, and an aircraft fuselage, wherein the aircraft fuselage comprises a frame, a landing gear, a power module, a flight control module , a load cabin and other function modules; the duct lift fans with the diversion helms are mounted on the aircraft fuselage and mainly consist of propellers, propeller driving units, the diversion helms, diversion helm driving units, ducts and the like, and the ducts are arranged at the peripheries of the propellers and used for improving the efficiency of the propellers, protecting the propellers and reducing the noise of the propellers; the propellers are driven by the propeller driving units; and the diversion helms driven by the diversion helm driving units are arranged on the air inlet sides or the air outlet sides of the duct lift fans.

The invention discloses a design method of a ground station three-dimensional navigation map of a small unmanned air vehicle. The method comprises the steps of Google Earth application program interface (API)-based map data acquisition, geographical coordinate conversion and navigation function implementation. Network map data of a flight area can be stored into a local two-dimensional array by a Google Earth API; map data is drawn into a ground station navigation map area by a three-dimensional drawing interface, so that a three-dimensional map can be formed; flight destinations of the unmanned air vehicle are inquired in local map data and are drawn in the three-dimensional map, so that the three-dimensional map navigation function can be realized. By virtue of the method, the three-dimensional navigation map with low cost can be provided for a ground station of the small unmanned air vehicle, the map display intuition is improved, and the flight safety of the unmanned air vehicle can be improved under complex terrain conditions.

A system for controlling access to data at the user interface level includes a device permissions manager to manage user access to data on a device including a device permissions comparator configured to receive a plurality of user profiles corresponding to users in proximity to the device and including user permissions to the data, and to generate a comparison of the user permissions. The device permissions manager also includes a device access controller configured to control access to the data on the device in response to the comparison of the user permissions.

The invention provides a quadrotor posture control method based on an MIMO nonlinear uncertain backstepping approach, which helps to improve flight safety and control performance of a quadrotor aircraft. The quadrotor posture control method comprises the steps of: establishing a quadrotor aircraft mathematical model based on aerodynamics and rotor aircraft motion principles and according to requirements for control performance; establishing a quadrotor aircraft model according to the quadrotor aircraft mathematical model and precision requirements; and analyzing and decoupling the quadrotor aircraft model according to uncertainty, external disturbance, underactuation and strong coupling characteristics of the quadrotor aircraft mathematical model and the quadrotor aircraft model, so as to determine a backstepping robust compensation controller based on inner and outer loop control. The quadrotor posture control method is suitable for the technical field of automation and control.

The invention discloses a culvert-type vertical take-off and landing lifting body unmanned aerial vehicle and relates to the technical field of vertical take-off and landing unmanned aerial vehicles.The culvert-type vertical take-off and landing lifting body unmanned aerial vehicle comprises a fuselage (1), lifting force rotor wings (2), a take-off and landing culvert (3), tilting-rotating thrustculverts (7) and tilting-rotating thrust rotor wings (8). The take-off and landing culvert (3) is composed of a through hole penetrating through the upper surface and the lower surface of the fuselage (1), and the lifting force rotor wings (2) are arranged in the take-off and landing culvert (3). The tilting-rotating thrust culverts (7) are hinged to the rear end of the fuselage (1) through tilting-rotating control mechanisms (9), the tilting-rotating control mechanisms (9) are configured to be capable of enabling the included angle between the axis of each tilting-rotating thrust culvert (7)and the axis of the fuselage (1) to be variable, and the tilting-rotating thrust rotor wings (8) are arranged in the tilting-rotating thrust culverts (7). Under the conditions that the vertical take-off and landing capacity of the unmanned aerial vehicle is maintained and the overall weight of the unmanned aerial vehicle is not excessively increased, the flight speed of the unmanned aerial vehicle is increased, the flight stability of the unmanned aerial vehicle is improved, the rotor wing exposed problem is avoided through the culverts, and the flight safety and the take-off and landing hovering efficiency are improved.

The invention provides an intelligent course control method for an unmanned plane. The method comprises the steps that power-on self-test is conducted on the unmanned plane, the course and the GPS coordinates of a takeoff point in a northeast coordinate system are recorded, and the unmanned plane takes off in a common remote control mode; an initial course locking mode or a return flight point locking mode is selected; if the initial course locking mode is selected, the course of the unmanned plane at the takeoff point is used as the initial course, and intelligent course control is achieved under a rectangular coordinate system with the takeoff point as the original point; if the return flight point locking mode is selected, intelligent course control is achieved under polar coordinates with the takeoff point as the polar point. According to the intelligent course control method for the unmanned plane, crashes of the unmanned plane or contact lost accidents caused by misoperation conducted due to the fact that control staff can not judge the current course when being unskilled in operation or the flight distance is too long can be effectively reduced, operation of the unmanned plane can be greatly simplified, and the flight safety of the unmanned plane is improved.

The invention relates to a calculation method for an aircraft navigation aid system making it possible to maintain a vertical safety margin with an obstruction profile, the aircraft comprising a navigation system, an automatic piloting system, a database system and a display device, characterized in that the method comprises the following steps: calculation of an obstruction altitude profile, calculation of a vertical safety margin with respect to the obstruction profile, of a plurality of vertical safety trajectories and of the respective flight setpoints for the aircraft to execute the trajectories, selection of the flight setpoints making it possible to maintain the aircraft as close as possible to the obstruction profile while maintaining between the aircraft and the obstruction profile at least the vertical safety margin, filtering of the flight set point values so that the variation of the values of the setpoints does not exceed a variation difference in a duration predefined in the system.

The disclosure provides in one embodiment a wing tip device for a wing of an air vehicle. The device comprises a tip tail element, a boom element attaching the tip tail element to a wing tip, a hinge element connecting the tip tail element to the boom element, and an actuator element connected to the hinge element. One or more wing load sensors sense wing loads, and a flight control system controls the actuator element. A load alleviation method and system for an air vehicle are also provided.