A ducted fan assembly includes a duct having an inlet, an inner surface, an expanding diffuser and an outlet. A fan disposed within the duct between the inlet and the expanding diffuser is configured to rotate about a fan axis to generate airflow. An active flow control system includes a plurality of injection zones circumferentially distributed about the inner surface. The expanding diffuser has a diffuser angle configured to create flow separation when the airflow is uninfluenced by the active flow control system such that the airflow has a thrust vector with a first direction that is substantially parallel to the fan axis. Injection of pressurized air from one of the injection zones asymmetrically reduces the flow separation between the airflow and the expanding diffuser downstream of that injection zone such that the thrust vector of the airflow has a second direction that is not parallel to the first direction.

A ducted fan assembly includes a duct having an inlet, an inner surface, an expanding diffuser and an outlet. A fan disposed within the duct between the inlet and the expanding diffuser is configured to rotate about a fan axis to generate airflow. An active flow control system includes a plurality of injection zones circumferentially distributed about the inner surface. The expanding diffuser has a diffuser angle configured to create flow separation when the airflow is uninfluenced by the active flow control system such that the airflow has a thrust vector with a first direction that is substantially parallel to the fan axis. Injection of pressurized air from one of the injection zones asymmetrically reduces the flow separation between the airflow and the expanding diffuser downstream of that injection zone such that the thrust vector of the airflow has a second direction that is not parallel to the first direction.

A method of operating an electrically powered rotorcraft of the type having a fuselage and a set of N rotors driven by a set of electric motors and coupled to the fuselage, N≥4, under a failure condition preventing ordinary operation of the rotorcraft. The method includes entering a failsafe mode of operation wherein autorotation of at least four of the rotors is enabled. The method also includes using electrical braking associated with a selected group of the rotors to control yaw of the rotorcraft.

The present invention relates to the propulsion system and aircraft with vertical take-off and landing—VTOL that uses aerodynamic phenomena of thrust amplification, including at zero speed, to reduce the thrust/weight ratio. According to the invention, an individual aircraft 1, with vertical take-off and landing, uses a fuselage 2 in the form of a frame 3 that merges two propulsion system, 4 and 5 one in the front and the other in the rear, of the bi-planar type, located at the ends of the fuselage 2. The propulsion system 4 uses two wings 6 and 7, which are superimposed, parallel and distanced by a certain distance D. The rear wing 7 is fixed perpendicularly to the frame 3 in its median area, so that an angle α between 25° and 80° is formed with the horizontal plane in static position. The front wing 6 and the rear wing 7 are secured at their ends by two jet limiters 8. Similarly the rear propulsion system 5 uses two wings 8 and 10. On each rear wing 7 and 10 are installed a number of electric motors 11, preferably located at equal distances from each other. Each electric motor 11 actuates a tractor propeller 12.

An improved rotorcraft of the type having a fuselage and a set of N≥4 rotors. The rotorcraft includes a structural support system affixed to the fuselage and mounting the set of rotors. The support system is configured as a set of airfoils that provide lift when the fuselage is in level flight. The fuselage has a central longitudinal axis that defines the direction of forward flight of the rotorcraft. Each of the rotors defines a corresponding rotational plane, that is tilted forward in the direction of the forward flight, when the central longitudinal axis of the fuselage is horizontal. Each airfoil may be positioned so that a majority of its length is disposed beneath the rotational plane of its corresponding rotor. When the rotorcraft is at a cruise speed, the airfoils are configured to provide lift that approximately matches the lift provided by the rotors.

An improved rotorcraft of the type having a fuselage and a set of N≥4 rotors. The rotorcraft includes a structural support system affixed to the fuselage and mounting the set of rotors. The support system is configured as a set of airfoils that provide lift when the fuselage is in level flight. The fuselage has a central longitudinal axis that defines the direction of forward flight of the rotorcraft. Each of the rotors defines a corresponding rotational plane, that is tilted forward in the direction of the forward flight, when the central longitudinal axis of the fuselage is horizontal. Each airfoil may be positioned so that a majority of its length is disposed beneath the rotational plane of its corresponding rotor. When the rotorcraft is at a cruise speed, the airfoils are configured to provide lift that approximately matches the lift provided by the rotors.

An aircraft that takes off and lands vertically for transporting people and/or loads, and a method for operating same. The aircraft comprises: a flying unit having a framework structure formed in a plane E, drive units arranged on the framework structure and air-guiding devices each having an adjustable angle of incidence which can be varied between a minimum and maximum angle of incidence; a transport unit comprising a conveying pod and connection device for connecting the conveying pod to the flying unit, the connection device comprising an elongate shaft connecting the conveying pod at one end; and an articulated coupling device for connecting the flying unit to the other end of the elongate shaft. An adjustable tilt angle α of the flying unit can be varied between a minimum angle α.sub.min of 0° ≤ α.sub.min < 30° and a maximum tilt angle α.sub.max = 90°.

A compound aircraft embodies an array of rotors for vertical flight positioned on support booms and wing elements for cruise flight coupled to a central fuselage housing avionics and a pusher propeller for forward propulsion. The aircraft accommodates a cargo-carrying container with mating of the surfaces between container and fuselage and latching mechanisms for attaching and detaching the container and vehicle.

A compound aircraft embodies an array of rotors for vertical flight positioned on support booms and wing elements for cruise flight coupled to a central fuselage housing avionics and a pusher propeller for forward propulsion. The aircraft accommodates a cargo-carrying container with mating of the surfaces between container and fuselage and latching mechanisms for attaching and detaching the container and vehicle.

UAV configurations and battery augmentation for UAV internal combustion engines, and associated systems and methods are disclosed. A representative configuration includes a fuselage, first and second wings coupled to and pivotable relative to the fuselage, and a plurality of lift rotors carried by the fuselage. A representative battery augmentation arrangement includes a DC-powered motor, an electronic speed controller, and a genset subsystem coupled to the electronic speed controller. The genset subsystem can include a battery set, an alternator, and a motor-gen controller having a phase control circuit configurable to rectify multiphase AC output from the alternator to produce rectified DC feed to the DC-powered motor. The motor-gen controller is configurable to draw DC power from the battery set to produce the rectified DC feed.