221results about How to "Easy to fly" patented technology

The present invention relates to a reduced scale industrial helicopter, with an integrated automatic flight control system, that includes core autopilot functions, GPS management, and full-function navigation systems. The autopilot technology includes rapid launch capability, real-time in-flight switching between one or more of a) remote control, b) autopilot-directed, c) ground station controlled, and d) home modes, and is upgradeable. The helicopter is used for high or low altitude surveillance, and can handle various payloads, including photographic missions. The helicopter may include onboard batteries and / or a unique battery unit disposed beneath the helicopter, and includes autonomous features such as automatic takeoff, automatic landing, safety return to home base, and predetermined mission plans.

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. The rotary-wing coaxial helicopter toy is remotely controlled and safe to fly in doors and out doors, while performing exciting maneuvers even by untrained kids.

A dual, coaxial rotor helicopter is provided that is relatively easy to fly. Thrust is provided by two ducted fans that are mounted at the rear of the aircraft and spaced apart laterally. Differential thrust generated by the fans provides yaw control for the aircraft, and forward thrust is provided by the fans working in combination. The coaxial rotors are preferably utilized primarily for lift, and not for forward thrust, which simplifies the control requirements. The coaxial rotor with ducted fan configuration also results in lower vibratory loads being imposed on the helicopter, thereby increasing its speed capability. The fan ducts serve to protect the fans, augment the fan thrust at low airspeeds, increase the efficiency of the fans at cruise speeds, and provide horizontal and vertical stabilizing surfaces to ensure aircraft flight stability.

The invention discloses a flying saucer, belonging to an aircraft field; the invention comprises a cabin, an operation and control system, an electric system, a plurality of facilities inside cabin, a fuel system, a starting system and an ignition system; a device for regulating motion direction of the cabin and a device for regulating rotary stability of the cabin are arranged on the cabin; a fuel tank is arranged on the cabin and a fuel pipe is arranged on the fuel tank; a flywheel jet engine is arranged on the cabin and the flywheel jet engine includes a flywheel shaft, a flywheel and a jet device; the jet shaft is connected with the cabin; the flywheel is arranged on the flywheel shaft and a pluratliy of jet devices is arranged on the periphery of the flywheel. The flying saucer can realize vertical takeoff and landing; the invention is provided with the device for regulating the motion direction of the cabin and the device for regulating the rotary stability of the cabin; the flying saucer has simple operation, stable flight and convenient direction-changing; in the flight of the flying saucer, a spiral flow which surrounds the cabin, rotates around the cabin and at the same time spirally propels downwards the cabin is generated, thus greatly accelerating propelling speed of the flow downwards the cabin. The invention has the advantages of high flight speed, flexible direction-changing, high safety, and low fuel cost.

An unmanned aerial vehicle (UAV) includes a central body having a lateral dimension substantially less than a vertical dimension, and one or more propulsion units supported by the central body. The one or more propulsion units include rotor blades configured to rotate to generate lift for the UAV.

The invention discloses a multi-rotor unmanned aerial vehicle. The multi-rotor unmanned aerial vehicle comprises a vehicle body (10), supporting arms (20) extending outwards in the transverse direction from the vehicle body, rotors (30), first supporting frames (41) fixed to the end portions of the supporting arms and provided with hollow regions capable of containing the rotors, first tilting steering engines (43) fixed to the first supporting frames, and second supporting frames (42) located in the hollow regions and connected to output shafts of the first tilting steering engines, wherein the rotors are fixed to the second supporting frames through first motors (31) so as to be driven by the first tilting steering engines to transversely tilt. When the unmanned aerial vehicle moves transversely, the transversely-tilting rotors can supply lift force maintaining the unmanned aerial vehicle at a certain height and can supply transverse motion power to the unmanned aerial vehicle, and meanwhile the vehicle body does not incline. Due to the fact that the rotors are contained in the hollow regions formed by the first supporting frames, the rotors can tilt at large angles in the hollowregions, and only generation of the power in the horizontal direction and the lift force in the vertical direction needs to be guaranteed.