An aircraft with folding mechanism, the aircraft including a fuselage, optionally a payload and/or landing gear attached to the fuselage, at least two longitudinal beams attached to the fuselage that preferably extend parallel to each other and parallel to a first aircraft axis, with lifting units attached to each of the longitudinal beams. At least one crossbeam is attached to the fuselage, and preferably extending parallel to a second aircraft axis and at right angles with respect to the longitudinal beams, with lifting units attached to the crossbeam. The longitudinal beams are rotatably attached to the fuselage by at least one respective first pivot joint configured for pivoting the longitudinal beams around a respective first pivot axis to a pivoted position. The crossbeam is rotatably attached to the fuselage, preferably by at least one second pivot joint, for pivoting the crossbeam around a second pivot axis to a pivoted position.

Provided is a flight vehicle that makes it possible to improve the safety of its passengers. The flight vehicle, which includes a fuel cell system, includes a fuselage part including a cabin. The fuel cell system includes at least one fuel gas tank, and a lower end of the fuel gas tank stands below a lower end of the fuselage part.

A motor-integrated fluid machine includes a rotating part that rotates around a rotation axis; an outer peripheral part provided at an outer periphery of the rotating part; and an outer peripheral drive motor that provides power from the outer peripheral part to rotate the rotating part. The rotating part includes a rotating support ring around the rotation axis, and blades provided on a center side of the ring and provided side by side in a circumferential direction of the rotation axis. The motor includes a rotor side magnet provided on an outer peripheral side of the ring in a radial direction, and a stator side magnet provided on an inner peripheral side of the outer peripheral part to face the magnet. The motor-integrated fluid machine includes a restraining part which covers and restrains the ring and the magnet from an outside to integrate the ring and the magnet

Hybrid propulsion is obtained by arranging, around a conventional turbomachine, a reversible electric machine linked to the low-pressure shaft via a mechanical movement transmission, a one-way clutch being arranged on the low-pressure shaft between the fan and a low-pressure compressor. The low-pressure shaft includes two aligned portions which can be separated and reconnected. A casing includes a first portion able to tilt around a horizontal transverse axis of the aircraft relative to a second portions of the casing. One portion of the low-pressure shaft, the fan and the reversible electric machine are mounted on the first portion of the casing, and the other portion of the low-pressure shaft is mounted on the second portion of the casing. This device facilitates electric taxiing of the aircraft, using the machine as a motor, whereas the rear of the low-pressure shaft remains stationary.

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.

Walking VTOL vehicles and related systems and methods are disclosed. A representative system can include one or more vertical thrust propulsion systems for providing vertical thrust for the vehicle, one or more horizontal thrust propulsion systems for providing horizontal thrust for the vehicle, and leg elements that are rotatable between a first configuration in which each leg element extends downwardly and a second configuration different from the first configuration. A representative method of operating a vehicle includes using vertical thrust to raise the vehicle upward, rotating a leg element forward, lowering the vehicle, and then rotating the leg element rearward to propel the vehicle forward.

A propulsion device, including a platform configured to support a passenger thereon; a thrust engine coupled to the platform, wherein the thrust engine is configured to provide a thrust output substantially along a first axis; a deflector assembly positioned proximate the thrust output, wherein the deflector assembly includes two deflecting guides to divert the thrust output into at least two thrust vectors angled with respect to the first axis; an actuator coupled to each deflecting guide to controllably adjust a position of the deflecting guides with respect to the thrust engine; and a controller in communication with the actuator, wherein the controller is configured to operate the actuator in response to one or more signals from at least one of the passenger and a sensor coupled to the platform.

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.

Disclosed is a take-off and landing station (1) for a flying vehicle (2) for transporting people and/or loads, which flying vehicle takes off and lands vertically and comprises a flight module (3), having a plurality of drive units (17) arranged on a supporting framework structure (16) of the flight module (3), and a transportation module (4), which can be coupled to the flight module (3). The take-off and landing station (1) comprises a holding apparatus (21) having a plurality of gripper elements and support elements (11) for supporting, fixing and/or orienting the supporting framework structure (16) during take-off and landing of the flying vehicle (2) or the flight module (3).

A ducted fan assembly includes a duct having an inlet, an inner surface, an expanding diffuser and an outlet. A fan disposed within the duct between the inlet and the expanding diffuser is configured to rotate about a fan axis to generate airflow. An active flow control system includes a plurality of injection zones circumferentially distributed about the inner surface. The expanding diffuser has a diffuser angle configured to create flow separation when the airflow is uninfluenced by the active flow control system such that the airflow has a thrust vector with a first direction that is substantially parallel to the fan axis. Injection of pressurized air from one of the injection zones asymmetrically reduces the flow separation between the airflow and the expanding diffuser downstream of that injection zone such that the thrust vector of the airflow has a second direction that is not parallel to the first direction.