A multi-dimensional vehicle configured for aerial and ground mobility is provided and includes a vehicle body, a plurality of vehicle wheels movably associated with the vehicle body and configurable between a ground mobility configuration and an aerial mobility configuration and a control device, wherein the control device is configured for wireless communication and is associated with the plurality of vehicle wheels to controllably operate the plurality of vehicle wheels and to controllably configure the plurality of vehicle wheels between the ground mobility configuration and the aerial mobility configuration, wherein each of the plurality of vehicle wheels include a wheel rim having an inner rim circumference and a plurality of fan blades distributed along the inner rim circumference, wherein the plurality of fan blades are configured to create a flow channel between each of the plurality of fan blades and an adjacent fan blade.

An optical-based aerial gaming system comprises: a multirotor unmanned flying device comprising: a main body; a plurality of propulsion units, a wireless receiver configured to receive data via radio communication; a wireless transmitter configured to send data via radio communication; one or more light generators configured to project laser or infrared light from the unmanned flying device; and one or more light sensors configured to detect laser or infrared light projected by a separate unmanned flying device; and a remote control unit comprising: a wireless transmitter configured to send data via radio communication; and a wireless receiver configured to receive data via radio communication, wherein the unmanned flying device is configured to transmit to the remote control unit, using the wireless transmitter of the unmanned flying device, at least a portion of encoded data of the detected laser or infrared light.

An apparatus for facilitating propulsion of a vehicle. The apparatus comprises a housing with an interior space, an inlet, and an outlet, a propulsion mechanism, and a gimbal. The propulsion mechanism is disposed in the interior space and comprises and an upper rotor and a lower rotor rotatably mounted on a first portion and a second portion of a spindle. The upper rotor rotates in a first direction and the lower rotor rotates in a second direction opposite to the first direction. Upper rotor blades have a first blade pitch and lower rotor blades have a second blade pitch opposite to the first blade pitch. The rotating of the upper rotor and the lower rotor creates a fluid flow from the inlet to the outlet for generating a directional thrust. The gimbal rotatably attaches the propulsion mechanism to the housing. The housing is rotatable for vectoring the directional thrust.

A remote controlled aircraft includes an aircraft that may be flown. A plurality of light emitters is coupled to the aircraft. A plurality of fans is coupled to the aircraft. Each of the fans may move air thereby facilitating each of the fans to urge the aircraft to fly. A control unit is coupled to the aircraft and the control unit is electrically coupled to each of the fans. The control unit includes a global positioning system. Thus, the control unit may identify a position of the aircraft with respect to Earth. A remote control is provided and the remote control may be manipulated. The remote control is in electrical communication with the control unit such that the remote control controls directional flight of the aircraft.

An aerial device (100) capable of controlled flight has a body (110), a rotor (120) arranged to rotate relative to the body; and a deployable sheet (130), the sheet having an undeployed configuration in which the sheet is folded against the body and a deployed configuration in which the sheet is at least partially unfolded away from the body.

According to a first aspect of the invention, there is provided a method for operating a multicopter experiencing a failure during flight, the multicopter comprising a body, and at least four effectors attached to the body, each operable to produce both a torque and a thrust force which can cause the multicopter to fly when not experiencing said failure. The method may comprise the step of identifying a failure wherein the failure affects the torque and/or thrust force produced by an effector, and in response to identifying a failure carrying out the following steps, (1) computing an estimate of the orientation of a primary axis of said body with respect to a predefined reference frame, wherein said primary axis is an axis about which said multicopter rotates when flying, (2) computing an estimate of the angular velocity of said multicopter, (3) controlling one or more of said at least four effectors based on said estimate of the orientation of the primary axis of said body with respect to said predefined reference frame and said estimate of the angular velocity of the multicopter. The step of controlling one or more of said at least four effectors may be performed such that (a) said one or more effectors collectively produce a torque along said primary axis and a torque perpendicular to said primary axis, wherein (i) the torque along said primary axis causes said multicopter to rotate about said primary axis, and (ii) the torque perpendicular to said primary axis causes said multicopter to move such that the orientation of said primary axis converges to a target orientation with respect to said predefined reference frame, and (b) such that said one or more effectors individually produce a thrust force along said primary axis.

An aerial vehicle capable of convertible flight from hover to linear flight includes a body having a longitudinal body axis, a plurality of forward wings, a plurality of aft wings, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. Each forward wing extends a forward wing plane. Each aft wing extends from an aft wing plane. The aerodynamic propulsors are mounted longitudinally between the plurality of forward wings and plurality of aft wings.

A gyro unit mounted on a steered object for performing steering based on a steering signal received from the outside comprises a gyro sensor, a calculation portion and a controller. The calculation portion is configured to perform calculations for posture control of the steered object based on the steering signal and a detection signal of the gyro sensor. The controller is configured to perform control such that a control direction of the posture control switches when the steered object moves forward and backward.

A remotely controlled flying camera system can to disable recording and/or streaming by a camera system on a flying device based on one or more programmed criteria. The programmed criteria can be based on predictions of when the flying camera system is likely being used as a surveillance camera and/or in situations that can result in an invasion of privacy. The predictions can be based on movements of the flying device and/or the surrounding. The system can reduce privacy invasion concerns with the use of the flying camera system, without completely removing or disabling the associated camera system.

This disclosure relates to a method for realizing obstacle avoidance functionality of a flying device. The method includes: providing a flying device without obstacle avoidance functionality, wherein the flying device includes a flying body and a remote controller; the flying body includes a wireless receiving module, a flying controlling module and an actuator; and second, installing a sensor and a micro controlling module; the wireless receiving module only send a first flying order that is from the remote controller, to the micro controlling module; the sensor only send an obstacle information to the micro controlling module; and the micro controlling module calculates the first flying order and the obstacle information to obtain a second flying order, and sends the second flying order to the flying controlling module; and the flying controlling module controls the flying body to fly according to the second flying order.