122results about How to "Flight safety" patented technology

A rotary-wing apparatus that is aeronautically stable, easy to fly with a multidimensional control, small size, and safe to fly and low cost to produce. The rotary-wing apparatus includes a coaxial counter rotating rotor drive providing lifting power with an inherent aeronautical stability; Auxiliary propellers that face the direction of flight and are located on opposite sides of said coaxial Rotary-wing apparatus and enable flying forwards, backwards and perform yawing; A rotary-wing coaxial helicopter toy that is remotely controlled and safe to fly in doors and out doors, while performing exciting maneuvers even by untrained kids

A hovering remote-control flying craft having a molded frame assembly includes a plurality of arms extending from a center body with an electric motor and corresponding propeller on each arm. In various embodiments, the motor and propeller are mounted downward-facing at a distal portion of each arm with a motor cover over the motor. The center body can be formed of a two-piece molded structure that sandwiches a circuit board to provide structural support for the frame. The circuit board can include a plurality of tabs that facilitate mounting of wire connectors, and can also provide antennas and emitters for both IR and RF communications. In some embodiments, a removable safety ring protects the propellers from lateral contact.

The invention relates to the technology of UAV (unmanned aerial vehicle) control, aims at proposing a UAV locus and attitude cooperative control method and ironing out a defect in the locus planning for each UAV of a conventional UAV cluster, and can effectively reduce the requirements for the positioning precision of the UAV. Therefore, the invention provides a cluster UAV locus and attitude cooperative control method for a safety domain, and the method comprises the following steps: 1, control-oriented four-rotor-wing UAV locus and attitude model building: giving full consideration to the inherent characteristics of a four-rotor-wing UAV and the dynamic factors in flight, and building a locus and attitude mathematic model for the four-rotor-wing UAV; 2, cluster center locus planning: achieving the obstacle avoidance path planning for a cluster UAV central point based on a pseudo-spectral method; 3, safety flight region optimization: completing the optimization of a cluster UAV safetyflight envelope and a cluster UAV optimal formation configuration; 4, distributed cooperative controller design. The method is mainly used in a UAV control occasion.

The invention discloses an anti-collision fixed-point unmanned aerial vehicle for fire control, and belongs to the field of unmanned aerial vehicles. The anti-collision fixed-point unmanned aerial vehicle for fire control comprises an unmanned aerial vehicle body, a bomb-dropping gun and an anti-collision cover, wherein the bomb-dropping gun is arranged below the unmanned aerial vehicle body; a steering engine is mounted on the bomb-dropping gun and is used for controlling the bomb-dropping gun to launch a fire extinguishing bomb; a collimation mechanism is mounted on the parallelly arranged bomb-dropping gun, so that the bomb-dropping accuracy is improved; the anti-collision cover adopts a cage-shaped structure; the cage-shaped structure encircles the periphery of the unmanned aerial vehicle body to protect the unmanned aerial vehicle body from being collided; a waterproof cover is also arranged on a spiral paddle support to prevent the spraying of flames. According to the anti-collision fixed-point unmanned aerial vehicle, fixed-point fire extinguishment on high-rise buildings and narrow channels is carried out without geographical environment limitation, and the unmanned aerial vehicle is unlikely to collide and damage, high in flying speed, sensitive in actions and wide in application range.

An aircraft (1) having a rotary wing (2) and at least one main gearbox (5) for driving rotation of said rotary wing (2), said aircraft (1) having a first main engine (11) and a second main engine (12) driving said main gearbox (5), said aircraft (1) being provided with a main regulation system (15) regulating the first main engine (11) and the second main engine (12) in application of a setpoint that is variable. A secondary engine (21) is also capable of driving said main gearbox (5), said aircraft (1) having a secondary regulation system (25) that regulates the secondary engine (21) in application of a setpoint that is constant and that is independent of said main regulation system (15).

An arithmetic unit calculates an estimated time of arrival (ETA) of an aircraft at a target point, and obtains a difference between ETA and a required time of arrival (RTA) at the target point. It multiplies a time error corresponding to the difference in time by the velocity of the aircraft, thereby converting the time error to a distance error. The distance error is symbol-displayed as ΔP_TIME in a display unit. Thus, the time error concerning a flight of the aircraft is visually displayed as a distance error. If the distance error exceeds a preset threshold value, a caution such as a display message or a voice message is generated.

A system and method uses light signals to detect and display the position of an airborne vehicle, such as a helicopter, during takeoff or landing or low speed, low altitude operation. A transmitter on the vehicle emits light signals while an optical receiver retrieves reflected light signals. Using light detection and ranging techniques, various parameters, such as altitude, ground speed and relative wind, are calculated based on the Doppler shift within the reflected light signals. The signals are transmitted in three different directions to facilitate the measurements of different Doppler shifts. The parameters are also displayed on a screen or other visual device within the vehicle.

The embodiment of the invention provides a navigation method during satellite navigation signal failure as well as a navigation device. The method comprises the following steps: continuously receivinga satellite navigation signal, IMU data and visual navigation and positioning information; judging whether a satellite navigation signal receiving state at the current moment is a valid state or not;if the satellite navigation signal receiving state at the current moment is the valid state, navigating by virtue of a first navigation model; and if the satellite navigation signal receiving state at the current moment is an invalid state, navigating by virtue of a second navigation mode. The embodiment of the invention not only can avoid the condition that an unmanned aerial vehicle only provided with a low-precision IMU can not fly safely due to the satellite navigation signal failure but also can avoid attitude drift, caused by an accumulated error of the low-precision IMU, of the unmanned aerial vehicle, so that the unmanned aerial vehicle safely flies under the condition that a satellite navigation signal is lost during flight or the unmanned aerial vehicle is disturbed, and flightsafety of the unmanned aerial vehicle is improved.

The invention discloses a helicopter taking off and landing vertically and flying horizontally and application thereof. The helicopter comprises a fuselage, rotor mechanisms, wing mechanisms, an undercarriage device, a power mechanism, a control mechanism and a transmission mechanism. The fuselage comprises a nose, a fuselage middle part and a tail. The rotor mechanisms comprise double rotating rotor mechanisms. Rotary double-rotor mechanisms are longitudinally arranged on the fuselage. The multiple wing mechanisms are perpendicularly arranged on the two sides of the fuselage middle part. As both the double rotating rotor mechanisms and the rotary double-rotor mechanisms are designed, both vertical taking-off and landing and rapid horizontal flying are achieved; as the rotor mechanisms are installed on the nose and the tail of the fuselage of the helicopter respectively and can rotate front and back around the center axis of the fuselage, the range of the helicopter is 5-6 times larger than that of an existing helicopter, flight safety is ensured, production and operation cost is reduced, the design can be applied to various aircrafts, and the significant technical effects of a large range, a high flight speed, a high safety coefficient and control easiness of the helicopter can be achieved.

The invention discloses a power transmission line inspection-based multi-rotor unmanned aerial vehicle inspection operation simulation training system. The power transmission line inspection-based multi-rotor unmanned aerial vehicle inspection operation simulation training system is established by using the virtual reality technology. The system includes a training host as well as an unmanned aerial vehicle remote controller, a keyboard, a mouse, a display, and a virtual reality helmet which are all connected with the training host in a wireless or wired manner; the training host is the mastercontrol device of the system, and is provided with a virtual unmanned aerial vehicle flight control simulation unit, a virtual unmanned aerial vehicle flight simulation unit, a training evaluation management unit, a defect location and identification unit, a database unit and a background management unit; the unmanned aerial vehicle remote controller, the keyboard and the mouse are all the inputdevices of the system; and the display and virtual reality helmet are the display devices of the system. The simulation training system of the present invention can be used not only to improve the unmanned aerial vehicle inspection operation control skills of operators and but also to prevent unnecessary loss of personnel, grid lines, or unmanned aerial vehicles due to the improper handling of special circumstances.

The present disclosure relates a flight control method and a device for unmanned planes. The method comprises the steps of acquiring the current geographical position information of an unmanned plane; matching the current geographic position information of the unmanned plane with the collected flight airline parameter information; when the current geographic position information of the unmanned plane is matched with the collected flight airline parameter information, loading the matched flight airline parameter information to the unmanned plane; according to the flight airline parameter information, determining a target airline, and controlling the flight of the unmanned plane according to the target airline. Therefore, the complicated manipulation of users is avoided. Especially for unmanned plane users who are not familiar with terrains and environments, the flight is safer and more convenient through directly adopting the collected flight airline parameter information.

The invention relates to a deformable flying vehicle. Two sides of the left and the right of a vehicle body of a fixed wing aircraft are provided with wings which can be folded into the body. The tail of the body is provided with a vertical empennage and a horizontal empennage. The vertical empennage is provided with a rudder or is not provided with the rudder, and the left and the right of the vertical empennage are provided with a compressed air spouts. The bottom of the vehicle body is provided with a plurality of wheels which are driven by a controllable motor. The vehicle body is internally provided with a vertical ducted fan and also is provided with a horizontal thrust engine with controllable rotation pause and rotation speed. The compressed air is introduced from the horizontal thrust engine to the sprout through a control valve. The deformable flying vehicle achieves running, elevating, hovering and flying by controlling the wheels, the vertical ducted fan, the horizontal thrust engine, the wings and the empennages. The deformable flying vehicle has performance for both the ground and the air, is safe, flexible, economical and environmental protective for running and flying and is convenient for using.

The present invention provides a method and device of airspace capacity determination based on a bad weather condition. The method comprises: obtaining meteorological data in a prediction time interval of an airspace to be analyzed, wherein the meteorological data is configured to represent the bad weather condition; arranging the region of bad weather influence of the airspace to be analyzed, employing the min-cut and max-flow algorithm to perform modeling of the airspace capacity problem in the bad weather condition, and constructing and obtaining the circular airspace constraint model of the airspace to be analyzed; and employing the Dijkstra algorithm to determine the maximum airspace capacity of the airspace to be analyzed according to the circular airspace constraint model. The method provided by the embodiment of the invention can rapidly and accurately determine the maximum capacity of ensuring the safe flight of an aircraft in some airspace range, especially in the condition of uncertain meteorological conditions so as to guide air traffic air traffic controller to control the number of aircrafts flying in the corresponding airspace so as to ensure the safe and smooth flight of the aircrafts in the airspace.

The invention provides a bumping information determination method, and a service time judging method and apparatus. The bumping information determination method comprises the following steps: acquiring trajectory information of a drafted air route and predicting location information of a bumping area; judging whether a trajectory of the drafted air route is overlapped with the bumping area; and when the trajectory of the drafted air route is overlapped with the area, determining a time of a flight in the area according to the trajectory information of the drafted air route and the location information of the area.

The invention relates to a dual-rotor coaxial helicopter with wing-shaped rotors, and the helicopter belongs to B64C 27/04. helicopters according to international patent technology classification. The general layout adopts a mashup design of a dual-rotor coaxial helicopter and a fixed wing aircraft with preposed canard wings. An elevator is preposed, and horizontal wings and ailerons for lateral control are disposed at the rear. A control surface that is responsible for yaw control is positioned behind ducted propellers that are disposed at the rear and used for providing thrust. Fans are arranged below the fuselage on the left and the right so as to retreat or horizontally and slightly adjust the fuselage hovering position or make the fuselage revolve. Due to the wing shape change, when an engine encounters in-flight shut-down, the helicopter continuously suffers height loss, so that air and the rotors interact to convert the potential energy of the helicopter into kinetic energy, which makes the rotors continue to rotate according to the rotation direction of the engine during working hours. Consequently, a lifting force can be generated, and fall can be changed to a safe landing. The helicopter provided in the invention can solve or improve the problems of small speed, short flying range, low flight height, great vibration and noise, poor reliability, high cost and use fee in helicopters in active service.

The invention discloses an unmanned aerial vehicle group path planning method under an uncertain condition, and the method specifically comprises the steps of: enabling an unmanned aerial vehicle group to obtain environment information which comprises the coordinates of an obstacle in the environment and the positions of a starting point and a target point of an unmanned aerial vehicle, and enabling the unmanned aerial vehicle to also need to consider uncertain factors in the environment; providing a robust evaluation function to evaluate the route of the unmanned aerial vehicle group; and optimizing the initial air route of each unmanned aerial vehicle in the unmanned aerial vehicle group through a robust particle swarm optimization algorithm, so that the final optimized air route has robustness. The method is low in calculation complexity and high in efficiency, a robust unmanned aerial vehicle group planning flight path can be generated, safe and efficient flight under uncertain conditions is achieved, tasks are cooperatively completed, and a specified target is achieved.

The present invention relates to a flight unit-based freight falling apparatus and a system using the same, and more particularly, to a flight unit-based freight falling apparatus and a system using the same that are capable of safely delivering freight to a given destination and automatically falling the freight to the given destination, through a flight unit like an unmanned aerial vehicle, commonly known as a drone. The flight unit-based freight falling apparatus includes: a mainboard for receiving falling and returning commands to control the operations of the freight falling apparatus; afreight mounting part for mounting freight thereon; and a lifting and descending part for lifting and descending the freight falling apparatus by winding cables connected to the underside of a flightunit and having a first motor for supplying a driving force to control the lifting and descending speed of the freight falling apparatus.

An aircraft with stealth double wings comprises a main body and stealth double wings. The main body has two main wings respectively having a surface into which a space is formed. The stealth double wings respectively are located in the spaces and include a first and a second rotating shaft, a link rod, a first and a second wing. The link rod has two ends respectively connected with the two rotating shafts. The two rotating shafts respectively have another end connected with the first and second wings. Thereby, when the first wing is moved to cover and enclose the space's opening, the second wing is driven to be located within the space, and when the first wing is moved upwardly away from the space, the second wing is driven to cover and enclose the space's opening, so as to keep the surface intact.

The invention relates to the unmanned aerial vehicle battery technology field, and discloses an intelligent battery used for an unmanned aerial vehicle. The intelligent battery comprises a housing, a battery management board detachably disposed in the housing, and an electric core group capable of realizing rapid charging. The battery management board is provided with a battery management unit used for the management of the battery, is connected with the MOS tube of the battery management unit, is connected with the power supply input/output interface of the MOS tube, and is connected with the CAN bus interface of the battery management unit. The CAN bus interface is connected with the main control system of the unmanned aerial vehicle for CAN bus communication. The electric core group is electrically connected with the MOS tube. The intelligent battery used for the unmanned aerial vehicle is advantageous in that by arranging the CAN bus interface, the CAN bus communication with the main control system of the unmanned aerial vehicle is realized, and a problem of instable data transmission between the intelligent battery and the main control system of the unmanned aerial vehicle is prevented, the stability of the communication is improved, and the safety and the reliability of the flight of the unmanned aerial vehicle are guaranteed.