An integrated multimode thermal energy transfer system, method and apparatus for full-scale clean fuel electric-powered multirotor aircraft with automatic on-board-capability to provide sensor-based temperature awareness and adjustment to critical components and zones of the aircraft. Automatic computer monitoring, including by a programmed triple-redundant digital autopilot computer, controls each motor-controller and motor to produce pitch, bank, yaw and elevation, while simultaneously measuring, calculating, and adjusting temperature and heat transfer of aircraft components and zones, to protect critical components from exceeding operating parameters and to provide a safe, comfortable environment for occupants during flight. By using the results of the measurements to inform computer monitoring, the methods and systems can use byproducts including thermal energy disparities and differentials related to both fuel supply systems and power generating systems to both add and remove heat from different aircraft zones to improve aircraft function, comfort, and efficiency.

An aerodyne comprises a fuselage, a fixed wing , a thruster for cruising flight, and a rotary wing for stages of vertical flight and held stationary during cruising flight. The rotary wing includes at least two contrarotating single-blades disposed at the top of the fuselage and hinged about respective axes perpendicular to the rotor axes of rotation. A maneuvering procedure for maneuvering the aerodyne includes a transition stage between a stage of vertical flight and a stage of cruising flight, wherein in the transition stage, when the speed of each single-blade is less than a threshold speed of rotation, the pitch of each single-blade is such that it no longer provides any lift force and the transverse hinge of the single-blade to its rotor axis is held locked in a position such that the single-blade is perpendicular to the rotor shaft.

A roadable VTOL flying vehicle having a road-configuration and a flight-configuration. The roadable VTOL flying vehicle includes a roadable vehicle; at least one rotor having at least one blade, the rotor is rotatably attached to an upper section of the roadable vehicle of the flying vehicle; at least one motor configured to operatively rotate the least at least one rotor; at least one angular position sensor configured to detect the angular position of each of the at least one rotor; and a vehicle control sub-system configured to affect automatic transformation of the flying vehicle from the road-configuration to the flight-configuration and from the flight-configuration to the road-configuration, wherein the vehicle control sub-system is configured bring the at least one rotor into a parking state, when in road-configuration.

A configuration instruction associated with configuring a plurality of batteries which supply power to a plurality of motors in a vehicle is received. The batteries are configuring as specified by the configuration instruction, where the batteries are able to be configured in a plurality of configurations, including: a first configuration where at least some of the batteries are electrically connected together in parallel and a second configuration where at least some of the batteries are electrically connected together in series.

A rotorcraft in which lift and thrust can be supplied by rotors, and specifically a drone comprising a camera that is used for making optical and/or sound recordings, especially during (live) events, such as concerts, gatherings, dance events, etc. The camera gives an impression of the events and is capable of recording specific details thereof, such as individual people.

A rotorcraft in which lift and thrust can be supplied by rotors, and specifically a drone comprising a camera that is used for making optical and/or sound recordings, especially during (live) events, such as concerts, gatherings, dance events, etc. The camera gives an impression of the events and is capable of recording specific details thereof, such as individual people.

An unmanned aerial vehicle according to the present disclosure is an unmanned aerial vehicle that can fly in midair and includes a propulsion unit configured to generate a propulsion force for fly in midair, a laser light source configured to illuminate laser light, an imaging unit configured to generate a captured image by capturing vertically below the unmanned aerial vehicle during flight in midair, and a controller configured to control an operation of the propulsion unit. The controller analyzes a captured image, extracts a light spot formed by laser light, measures a positional relationship with another unmanned aerial vehicle based on the extracted light spot, and executes a collision avoidance operation with respect to another unmanned aerial vehicle based on the measured positional relationship.

A multi-axis aircraft with a wind resistant unit includes a fuselage having an upper face and a lower face. The fuselage includes a central axis passing through the upper face and the lower face. A plurality of rotors is mounted to the fuselage. Each rotor includes a rotating axis parallel to the central axis. A wind resistant unit includes a plurality of wind barriers disposed in a radial direction perpendicular to a reference axis. Each wind barrier includes a plurality of rods fixed by at least one fixing member. Two adjacent rods have a passage therebetween. Each rod includes an axis proximal end facing the reference axis and an axis remote end remote to the reference axis. Each wind barrier includes a coupling end and an airflow diversion end. The coupling end is fixed by at least one coupling member to the upper face of the fuselage.

A multi-axis aircraft with a wind resistant unit includes a fuselage having an upper face and a lower face. The fuselage includes a central axis passing through the upper face and the lower face. A plurality of rotors is mounted to the fuselage. Each rotor includes a rotating axis parallel to the central axis. A wind resistant unit includes a plurality of wind barriers disposed in a radial direction perpendicular to a reference axis. Each wind barrier includes a plurality of rods fixed by at least one fixing member. Two adjacent rods have a passage therebetween. Each rod includes an axis proximal end facing the reference axis and an axis remote end remote to the reference axis. Each wind barrier includes a coupling end and an airflow diversion end. The coupling end is fixed by at least one coupling member to the upper face of the fuselage.

Embodiments are directed to a rotor-based remote flying vehicle platform such as a quadrotor, and to methods for controlling intra-flight dynamics of such rotor-based remote flying vehicles. In one case, a rotor-based remote flying vehicle platform is provided that includes a central frame. The central frame has a control center that is configured to control motors mounted to the vehicle platform. The central frame also has a communication port configured to interface with functionality modules. The communication port is communicably connected to the control center. The rotor-based remote flying vehicle platform further includes at least a first arm that is connected to the central frame and extends outward, as well as a first motor mounted to the first arm, where the first motor is in communication with the control center. The method for controlling intra-flight dynamics may be performed on such a rotor-based remote flying vehicle.