2516results about "Toy aircrafts" patented technology

Method and system for remote control of a drone helicopter and RC plane using a handheld device is disclosed. Piloting commands and actions are performed using the handheld device, which includes a motion sensor module, with gyro-sensor and g-sensor for controlling roll, yaw and pitch of flying object under relative or absolute coordinate system. The gyro-sensor controls both heading and rotation of flying object in place around its yaw by rotating handheld device around its yaw axis; g-sensor controls pitch and roll by rotating handheld device around its pitch axis and roll axes. Upon determining free falling of flying object, throttle is thereby adjusted so as to land it safely. Flying object further has a camera, and video images are transferred wireless to be displayed on touch screen, and image zoom-in and zoom-out are provided via multi-touch of touch screen. RF and IR capability is included for wireless communication.

A quadrotor UAV including ruggedized, integral-battery, load-bearing body, two arms on the load-bearing body, each arm having two rotors, a control module mounted on the load-bearing body, a payload module mounted on the control module, and skids configured as landing gear. The two arms are replaceable with arms having wheels for ground vehicle use, with arms having floats and props for water-surface use, and with arms having pitch-controlled props for underwater use. The control module is configured to operate as an unmanned aerial vehicle, an unmanned ground vehicle, an unmanned (water) surface vehicle, and an unmanned underwater vehicle, depending on the type of arms that are attached.

The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors.

A crosswind kite system adapted to operate in an alternate mode in high winds. The system may operate at reduced efficiency in high winds in order to moderate loading on the system during those high winds. The system may use multi-element airfoils which are actuated to reduce the coefficient of lift of the airfoils in order to moderate loading in high wind conditions. Other flight aspects may be controlled, including flying the crosswind kite in side slip to induce drag which may lower loading on the system.

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 tethered airborne electrical power generation system which may utilize a strutted frame structure with airfoils built into the frame to keep wind turbine driven generators which are within the structure airborne. The primary rotors utilize the prevailing wind to generate rotational velocity. Electrical power generated is returned to ground using a tether that is also adapted to fasten the flying system to the ground. The flying system is adapted to be able to use electrical energy to provide power to the primary turbines which are used as motors to raise the system from the ground, or mounting support, into the air. The system may use an attachment mechanism for the tether adapted to move the tether attachment point relative to the flying craft.

A miniature aircraft 1 has a center axle 22, two rotors 3 and 5 provided substantially axially to the center axle 22 and capable of rotating in opposite directions, rotary wings 34 and 54 provided to the rotors 3 and 5, vibrating members 4 for rotating the rotary wings 34 and 54 via the rotors 3 and 5, and cables 471 and 472 connected to the vibrating members 4. A hollow part 221 is formed in the center axle 22 along the longitudinal direction thereof, and the cables 471 and 472 are easily positioned in the hollow part 221.

The purpose of the invention is a light aircraft, remotely supplied and remotely controlled, propelled by electrical motors coupled to propellers, this device being able to perform stationary flight and to move in the three space dimensions in a controlled way. The system includes an aircraft (1), a control unit (3) and a handling unit (4). The aircraft comprises four propellers, each of them driven by a electric motor, a gyroscopic device, tilt sensors, a yaw sensor and an extrenal protective body. The invention also describes the method for the fliht closed loop control. The main purpose of this invention is to provide a enjoyable and educative toy, mainly intended for indoor flight. In a variant of the invention, the aircraft is fitted with a miniaturized video camera, in order to perform remote inspections on buildings or elements difficult to access.

A vertical lift craft includes a vertical lift craft, a powered rotor system including two counter-rotating lift rotors rotatably mounted to the body and a cage fixed to the body and extending about the powered rotor system, the cage including flexible rods extending in an open mesh pattern and mutually attached at a plurality of intersections between the flexible rods and netting extending between the flexible rods to cover the cage. The mesh pattern includes latitudinally and longitudinally extending flexible rods and the cage further includes elastomeric bumpers at the plurality of intersections between flexible rods. A base has axles fixed relative to the body and wheels on the axles.

A motion-generating illuminated inflatable decoration includes an inflatable body with an inner space mounted on the mounting base, an air pump and a dynamic controlling device. The air pump is mounted in the inner space to pump ambient air into the inner space. The dynamic controlling device is mounted in the inflatable body and includes a pulling cord, a cord driving motor, multiple illuminating elements, a controller and a sensor. The pulling cord interconnects the inflatable body with the cord driving motor and will cause a motion of the inflatable body as the cord driving motor is rotated to change its length. The illuminating elements are mounted on the inflatable body to produce lights. The controller controls the cord driving motor and the illuminating elements to work as the sensor detects a person going through the inflatable decoration to attract the person's attention.

In order to measure the movement of a vehicle, especially an aircraft, an imaging optical system 2 which is to be positioned on the vehicle is used to detect an image of the environment 4, and an optoelectronic shift sensor 3 chip of the type comprising an inherent evaluation unit is used to measure any shift of the image from structures thereof. The shift sensor is equal or similar to the sensor used on an optical mouse. The sensor is positioned in such a way that infinite objects are focused. The measuring signal is evaluated to indicate movements and/or the position of the aircraft. The inventive system can also be used to measure distances e.g. in order to control the flight altitude. The invention further relates to methods for automatically controlling particularly a hovering flight by means of a control loop using optical flow measurement.

There is disclosed a radio control flying toy in which an airframe can be easily floated and a running direction can be easily controlled. The toy is provided with: an airframe 11 formed into a rectangular plate shape having a flat bottom surface on a lower side; first to fourth propellers 16a, 16b, 16c, and 16d which are disposed in four corners forming at least a quadrangular shape on the lower side of the airframe 11 and which feed air toward a bottom-surface side to float the airframe 11; first to fourth driving means 17a, 17b, 17c, and 17d which drive the first to fourth propellers 16a, 16b, 16c, and 16d, respectively; a control unit 20 which individually controls driving outputs of the first to fourth driving means 17a, 17b, 17c, and 17d, respectively; a transmitter 30 for transmitting a control signal for flight from the outside to the control unit 20; and a battery 21 which supplies power to the first to fourth driving means 17a, 17b, 17c, and 17d and the control unit 20.

The Multi-Rotor Safety Shield (MRSS) provides a complete and substantial encasement system which can be secured about a Drone, protecting a multitude of aircraft components from contact with any outside disturbance and which can protect the sensitive components from dust, water, wind, rain, snow, fingers, toes, appendages of any kind, and atmospheric changes as example, from disabling the Drone and can protect people, places or things from high velocity spinning exposed rotor/propellers. The MRSS provides rigid non-permeable platform for attaching or incorporating additional safety devices as found in the Drone industry (or other industries) resulting in a safety device that completely prevents the loss a Drone due to the catastrophic failure of any Drone system or combination of systems which would typically result in rapid decent, and/or uncontrolled flight. The MRSS makes Drones safe near humans and safe to use around public gatherings, stadium events, accident scenes, disaster search and rescue and disaster relief, and indoors for the security and communications markets among others expanding the availability of Drones to further assist humanity.

A miniature, unmanned aircraft for acquiring and/or transmitting data, capable of automatically maintaining desired airframe stability while operating by remote directional commands. The aircraft comprises a fuselage and a wing, a piston engine and propeller, a fuel supply, at least one data sensor and/or radio transceiver, a microprocessor disposed to manage flight, a radio transceiver for receiving remotely generated flight direction commands, a GPS receiver, a plurality of control surfaces and associated servomechanisms, for controlling flight stabilization and direction, roll, pitch, yaw, velocity, and altitude sensors. The microprocessor uses roll, pitch, yaw, and altitude data to control attitude and altitude of the aircraft automatically, but controls flight direction solely based on external commands. The aircraft does not exceed fifty-five pounds.

The present invention provides a radio control helicopter toy including a mast mounted projecting to the upper side of an airframe so as to be rotated by a main motor, a rotor mounted on the upper part of the mast via a rotor head with the blade surface of a rotor blade capable of inclining, a blade inclining mechanism having an arm with one end part side thereof mounted rotatably on the airframe side and the other end part side thereof is mounted to be driven to approach to the above-mentioned rotor head side by an actuator, for inclining the blade surface of the above-mentioned rotor by the magnetic force generated between magnets mounted on the end part of the arm and the above-mentioned rotor head or between a magnet and a ferromagnetic material, and a receiver loaded on the above-mentioned airframe for controlling the operation of the above-mentioned main motor and the actuator.

Methods and apparatus are provided for launching and landing unmanned aerial vehicles (UAVs) including multi-rotor aircrafts. The methods and apparatus disclosed herein utilize positional change of the UAV, visual signal, or other means to effect the launch or landing. The methods and apparatus disclosed herein are user friendly, particularly to amateur UAV users lacking practice of operating a UAV.

The author suggests a new method and a new inexpensive, large blade-rope type wind rotor, that will be suspended at high altitude and produce huge quantities of energy. The air installation embodiment includes (FIG. 25): propeller 220, wing 226, rope transmission 229, electric generator 12 located at ground. Water rotors can utilize energy of ocean and sea streams. The invention contains 11 projects: 6 for air, 1 for a river, 3 for the sea and ocean, and 1 for ships. They have a power capacity of up to 60 MgW (air), up to 200 MgW (water) for one unit. The suggested installations have the following advantages: 1. Huge power production capacity-up to 5000-10000 times more than conventional ground-based rotor designs. 2. The rotor operates at high altitude of 1-14 kilometers, where wind has high speed and high stability (permanent flows). 3. The installation is much less expensive compared to conventional currently-employed windmills, partly because no tower is necessary to fix the rotor in space. 4. Wind energy is free -environmentally friendly.