A junction of a pylon with an aircraft wing, the pylon including a primary structure extending from front to rear along a longitudinal axis and in the form of a box with a rear face and an upper spar forming an upper face of the box, a longitudinal median plane separating the primary structure into two parts, left and right, the junction comprising a rear attachment system for attaching the pylon to the wing, this system being arranged at the rear of the primary structure, the rear attachment system including a shoe attached beneath the wing, the shoe being connected, via at least one articulated connecting rod, to a fitting attached to the rear face of the pylon by an articulation whose articulation pin, termed the horizontal articulation pin, is perpendicular to the longitudinal median plane, and the shoe being connected to the upper spar via a force reacting system.

A junction of a pylon with an aircraft wing, the pylon including a primary structure extending from front to rear along a longitudinal axis and in the form of a box with a rear face and an upper spar forming an upper face of the box, a longitudinal median plane separating the primary structure into two parts, left and right, the junction comprising a rear attachment system for attaching the pylon to the wing, this system being arranged at the rear of the primary structure, the rear attachment system including a shoe attached beneath the wing, the shoe being connected, via at least one articulated connecting rod, to a fitting attached to the rear face of the pylon by an articulation whose articulation pin, termed the horizontal articulation pin, is perpendicular to the longitudinal median plane, and the shoe being connected to the upper spar via a force reacting system.

A wing assembly includes a center wing structure and a pair of outer wing structures. The center wing structure includes a center wing front spar, a center wing rear spar, and an engine mounting location on each side of a wing centerline. Each outer wing structure includes an outer wing front and rear spar configured to be coupled respectively to the center wing front and rear spar to define a wing joint coupling the outer wing structure to the center wing structure. The center wing structure is configured such that the spar terminal ends of the center wing front and rear spars at each wing joint are located no further inboard than an engine centerline associated with the engine mounting location, and no further outboard of the engine centerline than ten percent of a distance between the engine centerline and the wing centerline.

A wing assembly includes a center wing structure and a pair of outer wing structures. The center wing structure includes a center wing front spar, a center wing rear spar, and an engine mounting location on each side of a wing centerline. Each outer wing structure includes an outer wing front and rear spar configured to be coupled respectively to the center wing front and rear spar to define a wing joint coupling the outer wing structure to the center wing structure. The center wing structure is configured such that the spar terminal ends of the center wing front and rear spars at each wing joint are located no further inboard than an engine centerline associated with the engine mounting location, and no further outboard of the engine centerline than ten percent of a distance between the engine centerline and the wing centerline.

An aircraft includes a wing with integrated ducted fans and ribs. Each respective ducted fan comprises a duct ring, a guide grille arranged within the duct ring, and an electric motor supported by the guide grille. The ribs are integrated into the guide grille. Each respective electric motor can be cylindrical, and the ribs can run tangentially along the electric motors.

The present invention relates to a wing assembly (10) for an aircraft with a fuselage and at least one pair of wings, the wing assembly (10) defining a direction of flow (F) with respect to which the wing assembly (10) is configured to create lift for the aircraft, comprising a main section (12), which is configured to be mounted to the fuselage in a fixed manner so as to extend from the fuselage in an extension direction of the wing; and a plurality of flap sections (14) each with a body part (16), which are mounted to the main section (12) in a pivotable manner so as to be individually pivotable around a pivot axis (A) by means of a pivoting means (18) over a range of angular orientations including a horizontal orientation in which the body part (16) of the flap section (14) is substantially aligned with the main section (12) to form an elongate and substantially continuous cross-section; and a vertical orientation in which the flap section (14) is angled downwards with respect to the main section (12). The invention further relates to an aircraft equipped with at least one pair of such wing assemblies.

The present invention relates to a wing assembly (10) for an aircraft with a fuselage and at least one pair of wings, the wing assembly (10) defining a direction of flow (F) with respect to which the wing assembly (10) is configured to create lift for the aircraft, comprising a main section (12), which is configured to be mounted to the fuselage in a fixed manner so as to extend from the fuselage in an extension direction of the wing; and a plurality of flap sections (14) each with a body part (16), which are mounted to the main section (12) in a pivotable manner so as to be individually pivotable around a pivot axis (A) by means of a pivoting means (18) over a range of angular orientations including a horizontal orientation in which the body part (16) of the flap section (14) is substantially aligned with the main section (12) to form an elongate and substantially continuous cross-section; and a vertical orientation in which the flap section (14) is angled downwards with respect to the main section (12). The invention further relates to an aircraft equipped with at least one pair of such wing assemblies.

A hybrid propulsion system for a tiltrotor aircraft comprises one or more engines that provide thrust whenever the tiltrotor aircraft is in a first forward flight mode, one or more electrical or hydraulic power sources, and two or more pylon assemblies. Each pylon assembly houses one or more electric or hydraulic motors connected to the one or more electrical or hydraulic power sources and a proprotor. All or part of each pylon assembly is rotatable. The proprotors provide lift whenever the tiltrotor aircraft is in a vertical takeoff and landing mode and a hover mode, and provide thrust whenever the tiltrotor aircraft is in a second forward flight mode.

A hybrid propulsion system for a tiltrotor aircraft comprises one or more engines that provide thrust whenever the tiltrotor aircraft is in a first forward flight mode, one or more electrical or hydraulic power sources, and two or more pylon assemblies. Each pylon assembly houses one or more electric or hydraulic motors connected to the one or more electrical or hydraulic power sources and a proprotor. All or part of each pylon assembly is rotatable. The proprotors provide lift whenever the tiltrotor aircraft is in a vertical takeoff and landing mode and a hover mode, and provide thrust whenever the tiltrotor aircraft is in a second forward flight mode.

Rotary electric engines, aircraft including the same, and associated methods. A rotary electric engine includes a nacelle, a fan configured to generate thrust, a stator operatively coupled to the nacelle, and a rotor operatively coupled to the fan. The fan includes a plurality of fan blades. The rotor includes a plurality of rotor magnets operatively coupled to respective blade tips of the fan blades. The stator includes a plurality of field coils configured to produce a magnetic interaction between the field coils and the rotor magnets to rotate the fan. In examples, the stator is configured to rotate each field coil relative to the nacelle. In examples, an aircraft includes one or more rotary electric engines pivotally mounted within engine mount regions. In examples, a method of operating an aircraft includes operating one or more rotary electric engines in a vertical lift configuration and in a forward flight configuration.