The lifting, stabilizing and propelling arrangement for vertical take-off and landing aircraft, uses rotating wings, turbines or lift fans, propellers and stabilizers on the trailing edges of the wings and empennages, centrifugal or tangential turbines applied on the sides of the fuselage, on the inlet and outlet edges of the wings, or centrifugal or tangential turbines on the sides of the fuselage and inside the wings, those that carry the fuselage are fixed and produce only lift and those that go in the wings they rotate with them and produce lift during vertical flight and propulsion during horizontal flight, add some horizontal stabilizing fans at the tips of the wings and others for direction in the vertical empennage.

An electric reaction control system that can selectively expel a “burst” or “puff” of air to alter the orientation of the aircraft during flight. An aircraft incorporating ducting, an air compressor, an electric motor, and a plurality of nozzles can facilitate in-flight trajectory modifications. When an air burst is needed to provide thrust for the purposes of reaction control, nozzles are selectively opened and closed to provide roll, pitch, and yaw of the aircraft. The ERCS can facilitate an electric aircraft that would be very agile and very light, utilizing electric power, as opposed to jet power.

An electric reaction control system that can selectively expel a “burst” or “puff” of air to alter the orientation of the aircraft during flight. An aircraft incorporating ducting, an air compressor, an electric motor, and a plurality of nozzles can facilitate in-flight trajectory modifications. When an air burst is needed to provide thrust for the purposes of reaction control, nozzles are selectively opened and closed to provide roll, pitch, and yaw of the aircraft. The ERCS can facilitate an electric aircraft that would be very agile and very light, utilizing electric power, as opposed to jet power.

Embodiments described herein relate to a vertical take-off and landing aircraft, specifically an electric or hybrid electric aircraft having a plurality of ducted fans. The aircraft includes a plurality of axially oriented fans, laterally oriented fans, forward air intakes, side exit ports and rear exhaust ports. The aircraft achieves flight by capturing air in the intakes and diverting the air through the axially oriented fans or the laterally oriented fans through the channels selectively.

A propulsion system includes at least one compressor, multiple conduits, a multiple-way valve, and at least one thrust augmentation device. A series of flaps can be retracted, tilted and operated in conjunction with the at least one thrust augmentation device. A converging channel in fluid communication with the valve is configured to allow expansion to ambient of a compressed air stream in a preferred single direction. The at least one thrust augmentation device each contains a mixing section, a throat section and a diffusor. Each said augmentation device receives compressed air from the at least one compressor via at least one of the conduits and valve and uses pressurized air as motive gas to generate thrust by fluidically entraining ambient air, mixing it with the motive gas and ejecting the motive gas at high velocities via the diffusor.

A propulsion system includes at least one compressor, multiple conduits, a multiple-way valve, and at least one thrust augmentation device. A series of flaps can be retracted, tilted and operated in conjunction with the at least one thrust augmentation device. A converging channel in fluid communication with the valve is configured to allow expansion to ambient of a compressed air stream in a preferred single direction. The at least one thrust augmentation device each contains a mixing section, a throat section and a diffusor. Each said augmentation device receives compressed air from the at least one compressor via at least one of the conduits and valve and uses pressurized air as motive gas to generate thrust by fluidically entraining ambient air, mixing it with the motive gas and ejecting the motive gas at high velocities via the diffusor.

A Coanda system for controlling directions of an aircraft. The system includes a fluid passage defined in part by a casing wall having an inner surface facing the fluid passage. The fluid passage is configured to pass fluid from a first end inlet to a second end outlet. A fluid control element including a Coanda surface is disposed at the second end outlet. The fluid control element is moveable within the second end outlet to direct the fluid exiting the fluid passage between an upper gap and a lower gap, around the Coanda surface. A contour element is disposed on the inner surface of the casing wall upstream of the fluid control element, and further assists in directing the fluid to the open gap.

A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.

A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.

A system for providing active flow control in an aircraft having a gas turbine engine. The system includes an environmental control system that includes a cabin blower system having a compressor operable to compress a fluid delivered by a fan section of the gas turbine engine to generate a pressurised fluid for use by the environmental control system. The environmental control system is fluidicly connected to an active flow control system via a fluid supply line, for allowing the pressurised fluid generated by the compressor to be supplied to the active flow control system so that it can be ejected from the aircraft across an exterior surface of a movable control element of the aircraft.