An intentional fluid manipulation apparatus (IFMA) assembly with a first thrust apparatus that imparts a first induced velocity to a local free stream flow during a nominal operation requirement. The first thrust apparatus creates a streamtube. A second thrust apparatus is located in a downstream portion of the streamtube. The second thrust apparatus imparts a second induced velocity to the local free stream flow. The second induced velocity at the location of the second thrust apparatus has a component in a direction opposite to the direction of the first induced velocity at the location of the second thrust apparatus.

Vertical take-off, landing and horizontal straight flight of an aircraft includes activation a plurality of front and rear lifting in-ring propellers, each of which is connected to a respective independently operating electric motor. In addition, horizontal straight flight of the aircraft includes activation of additional left and right pushing propellers, each of which is connected to an independently operating electric motor. The front and rear lifting in-ring propellers are respectively positioned generally horizontally and symmetrically opposite to one another and equidistantly relative to a longitudinal axis of the aircraft. The right pushing propeller and the left pushing propeller are positioned generally vertically and symmetrically opposite to one another and equidistantly relative to the longitudinal axis of the aircraft.

Vertical take-off, landing and horizontal straight flight of an aircraft includes activation a plurality of front and rear lifting propellers, each of which is connected to a respective independently operating electric motor. In addition, horizontal straight flight of the aircraft includes activation of additional left and right pushing propellers, each of which is connected to an independently operating electric motor. The front and rear lifting propellers are respectively positioned generally horizontally and symmetrically opposite to one another and equidistantly relative to a longitudinal axis of the aircraft. The right pushing propeller and the left pushing propeller are positioned generally vertically and symmetrically opposite to one another and equidistantly relative to the longitudinal axis of the aircraft.

According to one implementation, a rotating device includes at least one ring, at least one motor and a power transmission mechanism. The least one ring rotates in a circumference direction. The at least one ring includes no hub for housing a motor inside the at least one ring. The at least one motor generates power for rotating the at least one ring. The power transmission mechanism transmits the power to the at least one ring.

An aircraft having a fuselage with one or more wings coupled to the fuselage. A pair of booms are attached to the one or more wings. Each boom has a front end coupled with a front propulsion system and a rear end coupled with a rear propulsion system. Each front propulsion system includes a front motor coupled with a foldable front propeller in a tractor configuration. Each rear propulsion system includes a rear motor coupled with a foldable rear propeller in a pusher configuration.

An aircraft having a fuselage with one or more wings coupled to the fuselage. A pair of booms are attached to the one or more wings. Each boom has a front end coupled with a front propulsion system and a rear end coupled with a rear propulsion system. Each front propulsion system includes a front motor coupled with a foldable front propeller in a tractor configuration. Each rear propulsion system includes a rear motor coupled with a foldable rear propeller in a pusher configuration.

The presently disclosed embodiments relate to vertical takeoff and landing (VTOL) aircraft that have the capability of hovering in both a “nose forward” and a “nose up” orientation, and any orientation between those two. The disclosed aircraft can also transition into wing born (non-hovering) flight from any of the hovering orientations. In addition, certain of the disclosed embodiments can, if desired, use only vectored thrust control to maintain stable flight in both hover and forward flight. No control surfaces (e.g. ailerons, elevators, rudders, flaps) are required to maintain a stable vehicle attitude. However, the disclosure contemplates aircraft both with and without such control surfaces.

The invention relates to an electric propulsion unit for an aircraft comprising at least one first propulsion member, a second propulsion member and a single electric motor configured to drive the first propulsion member and the second propulsion member in a counter-rotating manner, the electric motor comprising a peripheral stator element comprising a first peripheral stage and a second peripheral stage which are offset along an axis, the first peripheral stage comprising at least a first phase, a second phase and a third phase which are alternated according to a first sequence in such a way as to allow a rotation of the first rotor element in the first direction of rotation, the second peripheral stage comprising phases which are alternated according to a second sequence in such a way as to allow a counter-rotating rotation of the second rotor element.

The invention relates to an electric propulsion unit for an aircraft comprising at least one first propulsion member, a second propulsion member and a single electric motor configured to drive the first propulsion member and the second propulsion member in a counter-rotating manner, the electric motor comprising a peripheral stator element comprising a first peripheral stage and a second peripheral stage which are offset along an axis, the first peripheral stage comprising at least a first phase, a second phase and a third phase which are alternated according to a first sequence in such a way as to allow a rotation of the first rotor element in the first direction of rotation, the second peripheral stage comprising phases which are alternated according to a second sequence in such a way as to allow a counter-rotating rotation of the second rotor element.

An electric vacuum jet engine is a more ecofriendly alternative to gas-fueled jet engines that generates the same or higher thrust than traditional gas-fueled jet engines. The jet engine includes a tubular housing, at least one first propeller assembly, and at least one second propeller assembly. The tubular housing accommodates an alternating of series of propeller assemblies formed by the at least one first propeller assembly and the at least one second propeller assembly. Together, the at least one first propeller assembly and the at least one second propeller assembly generate several vacuums along the tubular housing that increase the velocity of air flow through the tubular housing to generate the thrust necessary to propel the desired aircraft. The tubular housing also includes a housing inlet and a housing outlet corresponding to the open ends of the tubular housing through which air flow enters and exits the tubular housing, respectively.