Abstract: A transportation system and method serve passenger-conveying VTOL air vehicles (AVs) at a vertiport. The vertiport has a flight deck including at least one landing pad, a passenger terminal, and a dynamic partition arrangement that defines a capsule for receiving one of the AVs at a time. The dynamic partition arrangement assumes a first open state in which it is open to the flight deck and closed to the passenger terminal and a second open state in which it is closed to the flight deck and open to the passenger terminal. A robotic system includes a handling robot that automatically approaches and docks with the AV after landing, and conveys the AV between the landing pad and the capsule via an opening provided by the first open state of the dynamic partition.

Abstract: A propulsion system according to an exemplary embodiment of this disclosure, among other possible things includes a fuel storage tank that is configured to store a fuel in a compressed state, a power generation device that is configured to consume the fuel and generate an output, a fuel system that is configured to provide the fuel from the fuel storage tank to the power generation device, and an electrochemical compressor that is in communication with the fuel system. The electrochemical compressor is configured to gather residual fuel from the fuel system and communicate the gathered residual fuel to at least one of the power generation device and the fuel storage tank.

Abstract: An aircraft includes a fuselage defining a longitudinal axis between a forward end and an aft end. The aircraft includes an electrical system having an electric storage. The electric storage is positioned within the fuselage.

Abstract: A gimbaled rotor assembly for an aircraft. The gimbaled rotor assembly including a static mast; a spherical bearing comprising an inner component and an outer component pivotable relative to each other about a bearing focus, the inner component fixedly coupled to the static mast; a rotor hub rotatably coupled to the outer component, allowing for relative rotation of the rotor hub about a rotor axis and for pivoting together with the outer component about the bearing focus; and a primary hub spring coupling the outer component to the static mast and configured for opposing pivoting of the rotor hub about the bearing focus from a neutral position.

Abstract: A removable barrier and an aircraft including such a removable barrier. The barrier including a panel configured to block at least partly an opening delimited by a frame, a plurality of straps each connected to the panel and each having first and second ends, for each strap, a first connection configured to connect the first end of the strap and a first edge of the frame at least temporarily, a second connection configured to connect the second end of the strap and a second edge of the frame at least temporarily, at least one folded overlength at the level of at least one of the first and second ends of the strap, at least one breakable connection keeping the overlength folded.

Abstract: A dual-occupancy aircraft minisuite incorporating a modular multiple-egress door assembly is disclosed. In embodiments, the dual-occupancy minisuite can accommodate two passengers in enhanced privacy. Access to (and egress from) the minisuite is through the modular multiple-egress door assembly, which provides forward and rear (relative to the egress gap between) sets of outer, intermediate, and inner doors. The outer doors translate laterally along rails in the intermediate doors, and the intermediate doors likewise translate laterally along rails in the inner doors, to open the minisuite for passenger access or direct view (or to close the minisuite for enhanced privacy). The forward and rear sets of doors are proportioned such that when any forward or rear translating door is jammed in a closed position, the remaining egress gap is of sufficient width to provide a distinct and independent emergency egress path for each occupying passenger of at least minimum required width.

Abstract: A partition for dividing a portion of an aircraft including at least a first inflatable cavity defined by a plurality of material sheets, and a nozzle configured to provide fluidic access to the first inflatable cavity, wherein the nozzle is configured to attach to an aircraft air vent.

Abstract: A lift-changing mechanism is configured to change generated by a wing of an aircraft and includes a slit and an opening and closing member. The slit extends in a wingspan direction inside the wing and forms openings on the lower surface of the wing and on the upper surface of the wing respectively. A part of airflow below the lower surface is allowed to flow toward the upper surface through the slit. The opening and closing member is configured to open and close the slit. When the opening and closing member opens the slit, lift generated on the wing is decreased compared with when the slit is closed.

Abstract: A retractable propeller apparatus of an air mobility vehicle has a structure enabling a propeller to be exposed or hidden depending on whether the air mobility vehicle is in a high-speed flight or a parking position. In particular, the retractable propeller apparatus includes: a base having a mount provided with a space; a propeller unit disposed on the mount and configured to generate a flow of air; a cover configured to close the space and be movable in the top-bottom direction with respect to the mount; and a lift unit disposed on the mount connected to the cover, and configured to move the cover. The cover selectively closes or opens the space based on an operation of the lift unit such that the propeller unit is operable.

Abstract: The present disclosure relates to a low mass system for releasably securing a robotic arm to a spacecraft and also securing various payloads to the robotic arm and to each other, permitting the robotic arm to be both moved from one location to another suitably equipped location on a spacecraft to another and to allow the free end of the robotic arm to be secured to any payload also similarly equipped such that this payload may be manipulated by the robotic arm.

Abstract: A stiffener skeleton that is configured to be mounted to an upper deck of a rotary wing aircraft in a maintenance phase, comprising an upper stiffening structure with a plurality of supporting arms for providing upside stiffening support, and a lateral stiffening structure with a plurality of supporting legs for providing lateral stiffening support, wherein the plurality of supporting arms and the plurality of supporting legs form a self-supporting frame structure.

Abstract: Embodiments are directed to a rotor blade comprising a blade tip attached to the outboard end of the rotor blade. The blade tip has at least two sides that are tapered together to an edge. The length of the blade tip extending away from the outboard end to the edge is a distance that is greater than half the thickness of the outboard end. When the rotor blade is operating in a folded configuration, air flows over the sides in a direction generally parallel to a longitudinal axis of the rotor blade. The sides have profiles that minimize or prevent separation of the air flow from the blade tip.

Abstract: A modular bar and shop space for an aircraft galley is disclosed. In embodiments, the bar and shop space includes an aircraft monument installable either adjacent to a galley complex or as a standalone. The monument has upper and lower portions disposed behind upper and lower panels; the upper portion includes chiller and warmer compartments. The lower portion includes storage shelving and is deployable into the space in front of the monument. When the lower portion deploys, the vertical upper panel tracks downward into a horizontal workdeck above the storage shelving. The deployed workdeck may be used as a counterspace for a snack bar or social area for passengers, or as additional temporary workspace for cabin crew.

Abstract: An aerodyne comprises a fuselage, a fixed wing , a thruster for cruising flight, and a rotary wing for stages of vertical flight and held stationary during cruising flight. The rotary wing includes at least two contrarotating single-blades disposed at the top of the fuselage and hinged about respective axes perpendicular to the rotor axes of rotation. A maneuvering procedure for maneuvering the aerodyne includes a transition stage between a stage of vertical flight and a stage of cruising flight, wherein in the transition stage, when the speed of each single-blade is less than a threshold speed of rotation, the pitch of each single-blade is such that it no longer provides any lift force and the transverse hinge of the single-blade to its rotor axis is held locked in a position such that the single-blade is perpendicular to the rotor shaft.

Abstract: A method for optimizing the operation of at least one first propeller and of at least one second propeller of a hybrid helicopter. The method comprises the following step during a control phase: deflection, with an autopilot system, of at least one aerodynamic stabilizer member into a setpoint position having, with respect to a reference position, a target deflection angle that is a function of a setpoint deflection angle, the setpoint deflection angle being calculated by the autopilot system in order to compensate for a torque exerted by the lift rotor at zero sideslip.

Abstract: An aircraft, including a fixed nacelle disposed on a wing of the aircraft, the fixed nacelle including a nacelle opening; a proprotor pylon disposed on the wing and rotatable relative to the fixed nacelle between a substantially horizontal position and a non-horizontal position, wherein rotation of the proprotor pylon to a non-horizontal position exposes the nacelle opening; and a movable cover disposed on at least one of the wing and fixed nacelle, said movable cover including a plurality of cover members that are movable between a closed position where at least a portion of the cover members collectively form a protective cover in front of the nacelle opening when the proprotor pylon is positioned in the non-horizontal position and a stowed position where at least a portion of the plurality of cover members are stowed. In other aspects, there is provide a method of covering a nacelle opening.

Abstract: A galley message center defines a tablet recess were a tablet is docked, substantially flush with the surrounding bulkhead so that a utensil storage drawer may be closely disposed to the message center and slide out in front of the tablet without the tablet needing to be removed. The docking element of the message center may be hinged to allow the tablet to be folded down with the screen against a recessed surface to protect the screen and prevent undesired or accidental interaction. The utensil storage drawer includes a plurality of features for securely holding utensils when not in use and place all of the stored utensils within reach of the flight staff, in proximity to a galley working surface.

Abstract: A method of controlling at least a first pitch of a first propeller and a second pitch of a second propeller of a hybrid helicopter, the hybrid helicopter having a thrust control and a yaw control that are configured to generate orders for modifying respectively a mean pitch component and a differential pitch component of the first pitch and of the second pitch, the hybrid helicopter having a collective pitch control for modifying a collective pitch component of main blades of the lift rotor. The method includes a step of: keeping with the control system the first pitch and the second pitch within a control domain that varies as a function of information relating to the collective pitch component.

Abstract: A transportation system and method serve passenger-conveying VTOL air vehicles (AVs) at a vertiport. The vertiport has a flight deck including at least one landing pad, a passenger terminal, and a dynamic partition arrangement that defines a capsule for receiving one of the AVs at a time. The dynamic partition arrangement assumes a first open state in which it is open to the flight deck and closed to the passenger terminal and a second open state in which it is closed to the flight deck and open to the passenger terminal. A robotic system includes a handling robot that automatically approaches and docks with the AV after landing, and conveys the AV between the landing pad and the capsule via an opening provided by the first open state of the dynamic partition.

Abstract: Aircraft having hybrid propulsion are disclosed. A disclosed example propulsion system for an aircraft. The propulsion system includes an engine, an electric motor, a first propeller mounted to an aerodynamic body of the aircraft, the first propeller driven by the engine, a second propeller mounted to the aerodynamic body and positioned outboard relative to the first propeller, the second propeller driven by the electric motor, and a selector to control whether the propulsion system is operated in a hybrid mode in which the first and second propellers are driven.