Abstract: A door arrangement for an aircraft comprising a door designed to close an aperture in an outer skin of the aircraft, and a articulated arm which is fixed by a first end to the door and which is designed to move the door in at least two translational directions and at least two rotational directions. An aircraft area with this door arrangement and an aircraft having such an aircraft area are furthermore provided. The aircraft area comprises a door aperture arranged in an outer skin of an aircraft, and a door arrangement. Here the door of the door arrangement may be designed to close the door aperture from an inside of the outer skin, and the articulated arm of the door arrangement may be fixed to the aircraft area.

Abstract: A metallic-composite joint fitting is provided. The fitting may comprise a frustoconical internal bearing having a bore, a conical sleeve configured to be disposed about the frustoconical internal bearing, a composite structure configured to couple between the frustoconical internal bearing and the conical sleeve, a metallic end fitting configured to be disposed within the bore and couple to the frustoconical internal bearing, and an external nut configured to couple to the metallic end fitting and the conical sleeve, wherein at least one of the frustoconical internal bearing or the conical sleeve comprises a flanged portion mutually configured to couple the conical sleeve to the frustoconical internal bearing via a locking ring.

Abstract: A system and a method for improving a stall margin of an aircraft during a climb phase of flight are disclosed. In one embodiment, the method comprises using data indicative of a phase of flight of the aircraft and data indicative of an angle-of-attack, and automatically commanding a deployment of leading edge slats movably attached to wings of the aircraft when the following conditions are true: the aircraft is in a climb phase of flight; and the angle-of-attack equals or exceeds a predefined deployment angle-of-attack threshold value.

Abstract: A system for an aircraft wing including a power drive unit (101), a first actuator (104C) for actuating a first aerodynamic device (103), a second actuator (104A) for actuating a second aerodynamic device (102), a first drive path (109B) configured to operate between the power drive unit (101) and the first actuator (104C), a second drive path (109A) operably connecting the power drive unit (101) and the second actuator (104A), the first drive path (109B) including a lost motion device (108A), the lost motion device (108A) being configured to selectively operably connect the power drive unit (101) to the first actuator (104C) and selectively operably disconnect the power drive unit (101) from the first actuator (104C).

Abstract: A space vehicle element configured to be at least partially destroyed during re-entry of a space vehicle into the atmosphere comprises a heat generating part comprising a metallo-thermal composition for providing additional heat during re-entry of the space vehicle into the atmosphere by an exothermic reaction of the metallo-thermal composition. The destruction of the space vehicle element is expedited by the additional heat provided by the heat generating part. The heat generating part is at least partially integrated within the space vehicle element or at least partially surrounds a portion of the space vehicle element. The application further relates to a corresponding method of manufacturing a space vehicle element configured to be destroyed during re-entry of the space vehicle into the atmosphere.

Abstract: A high-lift device includes a flap disposed at a leading edge of a wing, and configured to be retracted in the lower surface and extended toward of the leading edge; a first rotary shaft and a second rotary shaft, the axial direction of the rotary shafts being disposed along the spanwise direction of the wing, respectively; a first link mechanism connected to the first rotary shaft and the flap; and a second link mechanism connected to the second rotary shaft and the flap. When the first link mechanism is driven with the first rotary shaft, the flap is retracted in the lower surface of the leading edge or is extended toward the front of the leading edge. When the second link mechanism is driven with the second rotary shaft, the position or the angle of the flap moved by the first link mechanism is changed.

Abstract: A wing for an aircraft including a wing tip section with an inboard section, a fairing in which an opening connecting an exterior of the fairing and an interior of the fairing is formed and which is mounted to the inboard section of the wing tip section, a movable device arranged in the exterior of the fairing, a connecting assembly movably connecting the movable device to the wing tip section such that the movable device is movable between a retracted position and at least one extended position, and a drive mechanism. The connecting assembly includes an actuating element, which extends through the opening and includes a first section, which is arranged in the interior of the fairing and is drivingly coupled to the drive mechanism, and a second section, which is arranged in the exterior of the fairing and coupled to the movable device.

Abstract: An emergency exit system comprising a first primary structure frame, a second primary structure frame extending substantially parallel to the first primary structure frame, a door opening arranged between the first primary structure frame and the second primary structure frame, and a door shiftable substantially parallel to the first primary structure frame and the second primary structure frame between a closed position and an open position. In the closed position, the door closes the door opening. In the open position, the door opens up the door opening. At least one of the primary structure frames comprises a primary structure guide element for guiding the door when the door is shifted between the closed position and the open position.

Abstract: An electric aircraft comprises a single passenger seat, vertical takeoff and landing capable rotorcraft with an amphibious undercarriage for ground or water landing and takeoff. An electrical power system includes an independent battery for each motor with quick-swap mechanism to enable drained batteries to be easily removed for external charging and swapped for a charged replacement battery. A ballistic recovery system may be deployed to safely land the aircraft in the event of an emergency and may be manually deployed in response to the passenger activating a deployment mechanism integrated into handles within the cockpit. An on-board flight control system includes an automated flight controller that places constraints on flight maneuvers, and a manual flight controller provides a passenger with a limited level of control over the flight.

Abstract: An electric vertical take-off and landing (eVTOL) vehicle is positioned to be in a charging position on the ground, wherein the eVTOL vehicle is capable of performing vertical take-offs and landings. The battery is charged while in the charging position on the ground using a wind turbine that includes the rotor.

Abstract: A mass transportation system provides an airborne passenger vehicle tethered to a host vehicle. The host vehicle traverses along a fixed route. The airborne passenger vehicle moves between a stowed position fixedly secured to the host vehicle and a deployed position in which the airborne passenger vehicle is flying above the host vehicle.

Abstract: A wing ring flying saucer is disclosed, which is operative to be driven to fly fast without needing an extra engine, and can turn, brake and fly backwards. The method of flying the wing ring flying saucer is as follows: airfoils of the wing ring or flow generators are enabled to repeat the same inclining process while passing by a specific section in circular motions of two times or more than three times in succession, so that a force perpendicular to the axial direction is created from an original resultant force in line with the axial direction of the wing ring (that is, a resultant force created by lift produced by all the airfoils), thereby enabling the wing ring flying saucer to fly, turn and go backwards at a relatively high speed.

Abstract: A system for providing active flow control in an aircraft having a gas turbine engine. The system includes an environmental control system that includes a cabin blower system having a compressor operable to compress a fluid delivered by a fan section of the gas turbine engine to generate a pressurised fluid for use by the environmental control system. The environmental control system is fluidicly connected to an active flow control system via a fluid supply line, for allowing the pressurised fluid generated by the compressor to be supplied to the active flow control system so that it can be ejected from the aircraft across an exterior surface of a movable control element of the aircraft.

Abstract: A wing for an aircraft, comprising a fixed wing, a foldable wing tip portion mounted to the fixed wing via a first hinge rotatably about a first hinge axis between an extended and folded positions, and an actuation unit to actuate the foldable wing tip portion for movement about the first hinge axis. The actuation unit comprises a link, a first and a second linear actuator. The link is rotatably mounted to the fixed wing via a second hinge, the first linear actuator is rotatably mounted to the fixed wing via a third hinge spaced from the second hinge, and is rotatably mounted to the link via a fourth hinge spaced from the second hinge. The second linear actuator is rotatably mounted to the foldable wing tip portion via a fifth hinge, and is rotatably mounted to the link via a sixth hinge spaced from the second hinge.

Abstract: Methods, systems, and assemblies for controlling flight control surfaces of an aircraft wing are described. The method comprises displacing a first trailing edge of a first flight control surface towards a contact surface of a second flight control surface; determining a mechanical stiffness of the first flight control surface as defined by a ratio of ?F/?X as the first flight control surface is displaced, where ?F is a difference in force F applied to at least two different positions X1 and X2 of the first flight control surface at times T1 and T2, and ?X is a difference in position X2?X1; and achieving full contact between the first trailing edge and the second leading edge when a known full contact mechanical stiffness is reached.

Abstract: A bridging structure for a deforming foil, such as a morphing wing, that provides a fluid-dynamic surface throughout foil deformation that forms a curved fluid-dynamic surface with a relatively low drag. A high extent of foil deformation can be provided, with lower actuation force, providing a fluid-dynamic surface with a simple or complex curve in one direction, by providing a set of rail-mounted members that are joined at one end to a deforming sheet. By coupling the members with high elongation, resilient bodies, adjacent members can support each other, while permitting extension, and accommodating curvature.

Abstract: An aircraft actuator torque limiter includes a disengageable torque transmitter between a rotary shaft and a driven member. The disengageable transmitter includes a friction pack including at least one contact member mounted secured in rotation with the rotary shaft and a complementary contact member, mounted secured in rotation with the driven member. The transmitter includes a clamp of the friction pack and a mover of the clamp, able to contract or expand differentially relative to the rotary shaft along the axis of rotation during a temperature variation. The clamp mover is made from a second material having a thermal expansion coefficient different from that of the first material forming the rotary shaft.

Abstract: Various systems and methodologies may be utilized to determine whether a particular shipment/item is eligible for delivery between a manual delivery vehicle and a final destination location via an autonomous delivery vehicle. To ensure autonomous deliveries are performed in a resource effective manner, shipments/items deemed eligible for autonomous delivery may be vetted by comparing the destination for the autonomous delivery shipment/item against one or more manual delivery destinations (serviced by the manual delivery vehicle operator), and ultimately identifying an optimal launch location for the autonomous delivery vehicle to leave the manual delivery vehicle to complete the autonomous delivery. If the autonomous delivery location does not satisfy applicable autonomous delivery criteria, the autonomous delivery shipment/item may be reclassified for manual delivery by the manual delivery vehicle operator.

Abstract: A hybrid-electric propulsion system for an aircraft is provided herein that can include a propulsor and a turbomachine comprising a high pressure turbine drivingly coupled to a high pressure compressor through a high pressure spool. An auxiliary power unit can be operably coupled with a starter motor. An electrical system can comprise a first electric machine coupled to the turbomachine. The first electric machine can be separate from the starter motor. A controller can be configured to provide electrical power from an electric power source to the first electric machine to drive the first electric machine to start, or assist with starting, the turbomachine.

Abstract: A flap support mechanism includes a carrier beam on which a flap is mounted. The carrier beam is rotatably mounted at a fixed rotational axis and has a pair of flanges, each flange having an aperture, and a channel extending aft from the pair of flanges. A fuse pin is received through the aperture in each flange. A coupler link is attached to an actuator at a first end and pivotally engaged to the carrier beam by the fuse pin. Extension of the coupler link by the actuator rotates the carrier beam from a stowed position to a deployed position. Responsive to a moment induced on the flap and carrier beam by a ground contact load, the fuse pin is frangible to shear releasing the coupler link to translate into the channel.