An electric VTOL aeronautical apparatus is disclosed that has folding wings each having an inboard wing portion coupled to an outboard portion via a hinge. Folding wings are known to be used during flight, although using a motor to fold and unfold the wings. In the present disclosure, the motor with its concomitant weight and complication is obviated or reduced by making the rotational axis of the hinge such that end of the hinge on the leading edge of the wing is displaced more outboard and lower than the end of the hinge on the trailing edge to allow the wing to fold and unfold passively. When in forward flight, a folded wing has more of the underside of the wing facing the flow, which pushes the wing upward, i.e., unfolding the wing. When the aeronautical apparatus transitions to vertical flight, gravity pulls the wings downward into the folded position.

A propulsor includes a propulsor body and a prop assembly in rotational communication with the propulsor body. The prop assembly includes a plurality of prop blades configured for rotation about an axial centerline of the propulsor. The plurality of prop blades are rotatable between a deployed position and a stowed position. The propulsor further includes at least one linkage having a first linkage end and a second linkage end. The first linkage end of the at least one linkage is rotatably mounted to the propulsor body and the second linkage end is configured to be rotatably mounted to an aircraft body. The propulsor further includes a first motor coupled to the at least one linkage and configured to rotate the at least one linkage relative to the propulsor body between a first rotational position and a second rotational position.

A propulsor includes a propulsor body and a prop assembly in rotational communication with the propulsor body. The prop assembly includes a plurality of prop blades configured for rotation about an axial centerline of the propulsor. The plurality of prop blades are rotatable between a deployed position and a stowed position. The propulsor further includes at least one linkage having a first linkage end and a second linkage end. The first linkage end of the at least one linkage is rotatably mounted to the propulsor body and the second linkage end is configured to be rotatably mounted to an aircraft body. The propulsor further includes a first motor coupled to the at least one linkage and configured to rotate the at least one linkage relative to the propulsor body between a first rotational position and a second rotational position.

An rear fairing for a pylon supporting an aircraft turbojet engine forms an aerodynamic surface covering the base of the pylon. The rear fairing is elongated in a longitudinal direction and includes a floor arranged opposite the hot gases exiting the turbojet engine and side walls constituting aerodynamic surfaces. The floor and the side walls include ceramic matrix composite materials made from preforms formed by layers of superimposed warp and weft yarns, the preforms have interlayer weaving yarns connecting the layers to one another.

An rear fairing for a pylon supporting an aircraft turbojet engine forms an aerodynamic surface covering the base of the pylon. The rear fairing is elongated in a longitudinal direction and includes a floor arranged opposite the hot gases exiting the turbojet engine and side walls constituting aerodynamic surfaces. The floor and the side walls include ceramic matrix composite materials made from preforms formed by layers of superimposed warp and weft yarns, the preforms have interlayer weaving yarns connecting the layers to one another.

An assembly having an outer tubular portion delimiting an inner space, an inner tubular portion in the outer tubular portion, a fluid jacket in the inner tubular portion, a plurality of groups of at least four thermal flow sensors. For each group, the sensors of the group are disposed in the inner space and overall in one and the same plane perpendicular to a central line. In each group, the sensors of the group are distributed angularly about the central line. A control unit which, for each group, receives the data from each sensor of the group and which, on the basis of these data, determines a warning level. With such an arrangement, the monitoring of the values of the different thermal flow sensors makes it possible to monitor a potential problem at the fluid jacket.

An aircraft and a control system for the aircraft includes a tilt-wing defining an inlet configured to receive air and an outlet in fluid communication with the inlet such that the outlet is configured to expel the air. The control system includes a high-lift device coupled to at least one of a leading edge, and a trailing edge of the tilt-wing. The high-lift device is movable relative to the tilt-wing. The control system includes a compressor in fluid communication with the inlet and the outlet. The compressor is configured to increase pressure of the air that is expelled out of the outlet. The outlet directs the pressurized air toward at least one of the high-lift device and a center section of the tilt-wing to maintain attachment of airflow across the tilt-wing. A method of operating the control system of the aircraft occurs to maintain attachment of airflow across the tilt-wing.

An aircraft and a control system for the aircraft includes a tilt-wing defining an inlet configured to receive air and an outlet in fluid communication with the inlet such that the outlet is configured to expel the air. The control system includes a high-lift device coupled to at least one of a leading edge, and a trailing edge of the tilt-wing. The high-lift device is movable relative to the tilt-wing. The control system includes a compressor in fluid communication with the inlet and the outlet. The compressor is configured to increase pressure of the air that is expelled out of the outlet. The outlet directs the pressurized air toward at least one of the high-lift device and a center section of the tilt-wing to maintain attachment of airflow across the tilt-wing. A method of operating the control system of the aircraft occurs to maintain attachment of airflow across the tilt-wing.

A nacelle for an aircraft, including a structure, a cap attached to the structure and a seal system including an arch forming a channel which extends beneath a rear edge of the cap and which has a bottom, the arch being attached to the structure, a seal in the form of a solid block in the channel and beneath the rear edge of the cap, a spring system arranged to move the seal away from the bottom, and a retaining arrangement configured to prevent the seal from leaving the channel under the action of the spring system. With an arrangement of this kind, it is not necessary to oversize the bead, this being replaced with a solid seal mounted on a spring system.

A nacelle for an aircraft, including a structure, a cap attached to the structure and a seal system including an arch forming a channel which extends beneath a rear edge of the cap and which has a bottom, the arch being attached to the structure, a seal in the form of a solid block in the channel and beneath the rear edge of the cap, a spring system arranged to move the seal away from the bottom, and a retaining arrangement configured to prevent the seal from leaving the channel under the action of the spring system. With an arrangement of this kind, it is not necessary to oversize the bead, this being replaced with a solid seal mounted on a spring system.