Systems, methods, lift fans, and aircraft involving active flow control of a ducted fan or fan-in-wing configuration are described.

A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle defining a duct, and a fan located within the duct. The fan comprises a hub arranged to rotate around a rotational axis and a plurality of blades attached to the hub, each of which has a span from a root at the hub defining a 0 percent span position (r.sub.hub) to a tip defining a 100 percent span position (r.sub.tip) and a plurality of span positions therebetween (r∈[r.sub.hub, r.sub.tip]). The hub has a negative hade angle (γ) with respect to the rotational axis at an axial position coincident with the leading edge of the blades.

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.

A rotorcraft provided with a yaw motion control system comprising a fairing and a rotor provided with blades, the blades being arranged in the fairing and able to rotate about an axis of rotation of the rotor, the fairing comprising a casing defining an air stream, the air stream extending in a direction of flow of the air within the fairing from an intake section towards an outlet section. The rotorcraft comprises an ice protection system comprising at least one grille arranged upstream of the air stream in the air flow direction, the grille facing the intake section parallel to the axis of rotation and the casing, no grille facing at least one unprotected section of the intake section in a direction parallel to the axis of rotation.

The present invention provides an engine of a vertical take-off and landing aircraft, wherein the engine is configured to be movable with respect to an aircraft component of the aircraft between a hover position for take-off and landing, and a cruise position for forward flight, wherein the engine comprises an aerodynamic component having at least one aerodynamic element movable between a first position according to a first operational state of the aircraft, and a second position according to a second operational state of the aircraft, the aerodynamic element defining an aerodynamic surface in contact with an airstream passing through the engine.

The present invention relates to an aerially distributable communications device (ACCD) including one or more gyrochutes and communications module configured for wireless communication with external communication nodes. The communications module can be configured for mesh network type communication with similar aerially distributable communications device, or as a gateway type communications device to a wide area network such as a satellite network. The ACCD is for deployment in remote areas and/or areas where normal communications networks are down, such as disaster areas. The ACCD can be deployed from an aircraft or a spacecraft. The ACCD can further be configured with emergency equipment such as water purification equipment, power charging equipment, or the like.

An acoustic system for an Urban Air Mobility (UAM) vehicle may comprise: a first shroud configured to be disposed around a rotor of the UAM vehicle, the first shroud comprising: a radially inner wall configured to be spaced radially outward from a blade tip of a rotary blade of the rotor, the radially inner wall including a perforated portion; and a hollow chamber defined by an internal surface of the first shroud and the radially inner wall.

An acoustic system for an Urban Air Mobility (UAM) vehicle may comprise a first shield configured to be disposed around a rotor of the UAM vehicle, the first shield having an annular shape, the first shield configured to be disposed radially outward from a blade tip of a rotary blade, the first shield configured to redirect sound waves from a substantially radial direction to a second direction, the second direction being orthogonal to the radial direction.

A duct for a ducted-rotor aircraft includes a hub, a duct ring, and a plurality of stators that extend outward from the hub. The duct ring defines a trailing edge. The duct includes one or more fittings, such as a system of fittings. Each fitting has a body that defines a first attachment interface that is configured to couple to structure of the duct ring and a second attachment interface that is configured to couple to one of the plurality of stators. The first and second attachment interfaces are spaced from each other such that when the fittings are coupled to the duct ring and the plurality of stators, all or substantially all of each of the plurality of stators are located aft of the trailing edge of the duct ring.