A cross flow fan to be incorporated into an aircraft comprises a cross flow fan rotor to be positioned in an aircraft, a drive arrangement for the cross flow fan rotor, and a plurality of vanes positioned downstream of the cross flow fan rotor. An aircraft is also disclosed.

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.

A cycloidal rotor is provided having a flexible by actuators or self-flexing blade-positioning tack, which can be brought into shape corresponding to currently desired blade orbit. This rotor can also be provided with frontal shielding or partial enclosure to assure that rotor operates at any speed as if in hovering flight; rotor track can be inclined to produce forward thrust or external thrusters can be used. Optionally in other embodiments blade orbit shape is determined by a variable cam mechanism or the inclination of blade positioning track of fixed shape to produce a change of its projected shape onto blades' plane of operation thus changing blades elliptic orbit. Blade centrifugal force countervailing mechanism is also proposed.

By providing propellers for vertical ascent and descent and for horizontal flight, and a blade for horizontal flight, it is possible to obtain an aerial vehicle capable of high speed horizontal flight and capable of flying a long distance.

An aerial vehicle is programmed or configured to respond to reports of events or conditions within spaces of a facility. The aerial vehicle travels to a location of a reported event or condition and captures data using onboard sensors. The aerial vehicle independently determines whether the reported event or condition is occurring, or is otherwise properly addressed by resources that are available at the location, using images or other data captured by the onboard sensors. Alternatively, the aerial vehicle transmits a request for additional resources to be provided at the location, where necessary. A map of the location generated based on images or other data captured by the onboard sensors may be utilized for any purpose, such as to make one or more recommendations of products that are appropriate for use at the facility.

A vertical take-off and landing (“VTOL”) aircraft has at least two flying wings (“FW”) with each FW equipped with multiple transverse-radial propellers or a propulsion system for producing a lift force and thrust force on the stationary or non-stationary FW. This VTOL/FWA is capable of exchanging payloads horizontally, as well as vertically, with a stationary or a moving object. In particular, the VTOL/FWA can “walk” on a building wall to adjust and anchor its position in order to rescue people from a high-rise-building window horizontally.

A system for creating thrust for flying machines with Vertical Take Off and Landing (VTOL) including a first propulsion unit, a second propulsion unit, a top winget, a bottom winget, two or more tracks running over said first and second propulsion units, and wherein the two or more tracks are configured to mount said top and bottom wingets.

An aerial vehicle is programmed or configured to respond to reports of events or conditions within spaces of a facility. The aerial vehicle travels to a location of a reported event or condition and captures data using onboard sensors. The aerial vehicle independently determines whether the reported event or condition is occurring, or is otherwise properly addressed by resources that are available at the location, using images or other data captured by the onboard sensors. Alternatively, the aerial vehicle transmits a request for additional resources to be provided at the location, where necessary. A map of the location generated based on images or other data captured by the onboard sensors may be utilized for any purpose, such as to make one or more recommendations of products that are appropriate for use at the facility.

The unmanned aerial vehicle, UAV, has a fuselage (1) with at least one rotating shaft (2) and one wing (3) positioned on the rotating shaft (2), protruding from either side of the fuselage (1). Preferably, the UAV has at least one rotor propeller (4) arranged on each rotating shaft (2), on either side of the fuselage (1), with one or more rotor blades (4a) and a housing (4b), which includes an actuator. The UAV is capable of shifting between a first flight mode using rotatable wings that rotate freely around the rotating shaft (2) only due to a direction and strength of wind impinging against a surface of the wings (3) and a downstream flow generated by the rotor propellers (4), and a second flight mode using fixed wings, kept in a predetermined position by a wing-locking mechanism, preferably a substantially horizontal position.

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.