An aerial vehicle including a set of rotors, a processor configured to configured to control the set of rotors for aerial vehicle flight, and a housing defining a plurality of cooling channels, wherein, for each rotor of the set, a projection of the processor and the cooling channels onto the respective rotor plane does not intersect the swept area of the rotor, and a distance from the rotor axis of a first rotor of the set to a cooling channel is less than 75% of a rotor diameter of the first rotor. A method for aerial vehicle operation, including providing an aerial vehicle including a rotor, a processor, and a housing, flying the aerial vehicle, and, while flying the aerial vehicle, actively cooling the processor, including, at the rotor, forcing airflow toward the processor.

An aerial vehicle including a set of rotors, a processor configured to configured to control the set of rotors for aerial vehicle flight, and a housing defining a plurality of cooling channels, wherein, for each rotor of the set, a projection of the processor and the cooling channels onto the respective rotor plane does not intersect the swept area of the rotor, and a distance from the rotor axis of a first rotor of the set to a cooling channel is less than 75% of a rotor diameter of the first rotor. A method for aerial vehicle operation, including providing an aerial vehicle including a rotor, a processor, and a housing, flying the aerial vehicle, and, while flying the aerial vehicle, actively cooling the processor, including, at the rotor, forcing airflow toward the processor.

The invention relates to a device for propelling a passenger, comprising a body arranged to receive said passenger and cooperating with a fuel-fed thrust unit. The arrangement of such a device enables great freedom of movement in the air. More specifically, the thrust unit comprises at least one thrust sub-unit, each advantageously comprising at least two thrusters and secondary course-correction and/attitude-correction thrusters.

The invention relates to a device for propelling a passenger, comprising a body arranged to receive said passenger and cooperating with a fuel-fed thrust unit. The arrangement of such a device enables great freedom of movement in the air. More specifically, the thrust unit comprises at least one thrust sub-unit, each advantageously comprising at least two thrusters and secondary course-correction and/attitude-correction thrusters.

A flight control system for an aircraft comprises a flight control computer system connected via a bus system with a plurality of bus nodes, which each are configured to at least one of controlling an associated aircraft device based on command messages received from the flight control computer system via the bus system and sending information messages to the flight control computer system via the bus system. The bus system is a redundant bus system comprising plural independent bus sub-systems, wherein each bus node is configured to communicate with the flight control computer system via two different bus sub-systems, wherein each bus node further is configured to communicate with the flight control computer system on basis of an associated predetermined bus communication protocol via a first bus sub-system and on basis of an associated predetermined bus communication protocol via a second bus sub-system.

An electrically powered vertical takeoff and vertical landing (VTOL) aircraft, which comprises at least two main propellers, wherein the main propellers are adapted to generate at least 70% of the aircraft propulsion. The aircraft also comprises at least one adjustment propeller, which has its propeller slipstream adapted to produce a torque relative to a first axis or the first and second axes with respect to a fuselage of the aircraft for turning the aircraft relative to said first axis or said first and second axes. In addition, not less than 35%, but not more than 85%, of the aircraft's mass is adapted to lie, during takeoff and/or landing, on a rear side of a propeller line of said main propellers with respect to a nose of the aircraft.

A flight propulsion system for Vertical Take-Off and Landing (VTOL) and Short Take-Off and Landing (STOL) aircraft, having a two cyclorotors, installed in the front and rear portions of a pair-wings mechanism involving top wing and bottom wing, three degree-of-freedom DOF adjusting mechanism for pair-wings, a dielectric barrier discharge (DBD) plasma actuators, a bar mechanism for pitching oscillation and rotation speed controls and rear cyclorotor, a yawing mechanism for rear cyclorotor, all on each side of the flight vehicle. This propulsion system is particularly useful for VTOL aircraft. The main features are: high controllability and manoeuvrability, low noise and environmental pollutions, VTOL, STOL, hover state flights, marine and ground take-off and landing, high safety, suitable for different aircraft scales and for different missions and purposes, instant altering the flight direction.

One embodiment is a rotor system comprising a duct ring; a hub disposed centrally to the duct ring; first and second stators each connected between the duct ring and the hub; first and second control vanes rotatably connected to the first and second stators, respectively; a structural hoop having a first end connected to the first control vane and a second end connected to the second control vane, the structural hoop for translating rotation of the first control vane about a vane axis to the second control vane; and a mechanism for restricting at least one of forward-aft movement and side-to-side movement of the structural hoop relative to the duct ring.

A propulsion system for an aerial vehicle or toy aerial vehicle includes a bladeless fan drive and a peripheral ground-engagement part. The bladeless fan drive operates in a plane (x′-y′) and is configured for producing thrust. The peripheral ground-engagement part comprises a hubless wheel and a rotatable tire component. The bladeless fan drive is secured within the hubless wheel by two pivot points on opposing sides of the bladeless fan drive, such that the plane of the bladeless fan drive is pivotable about a pivot axis (x′) spanning between the two pivot points, the pivot axis (x′) being orthogonal to a hubless wheel axis (z) of the peripheral ground-engagement part.

A method for controlling a thrust vectored aircraft includes mapping aircraft control commands with a flight controller through at least an inner-mixing space and generating output commands.