Abstract: A fuel tank dam comprises a first section, a second section, a third section, and a flange section. The first section can be fixed to a first structural component, and the second section can be fixed to a second structural component. The third section has a bellows comprising a plurality of folded sections and is disposed between the first section and the second section. The flange section extends along an outer plate at least from an edge section of the third section and can be fixed to the outer plate.

Abstract: A galley monument having an integrated display arrangement includes a display; a display holder, by which the display is movably attached to the galley monument, wherein the display holder is designed as a rotary-pivot joint; and a receiving region, into which the display can be pivoted into a stowed state by the display holder; wherein the display can be rotated by the display holder in a state of use in order to set an orientation for use.

Abstract: A galley monument for an aircraft has a plurality of walls which define at least one slide-in compartment of the galley monument, and a display device which is coupled pivotably to one of the walls by an articulation device, wherein that wall to which the display device is coupled has a receiving recess into which the display device can be pivoted into a stowage position. Furthermore, an aircraft is described which has at least one such galley monument.

Abstract: One embodiment is a rotor system including a rotor hub comprising a plurality of extension arms for connecting rotor blades to the rotor hub; a plurality of dampers connected between a respective one of the extension arms and the rotor hub; and a fairing disposed over the rotor hub, the fairing including an inlet plenum through which air is drawn from outside the fairing into the fairing; and at least one duct for conducting the air toward the at least one of the dampers.

Abstract: Propeller assemblies, aircraft including the same, and associated methods. A propeller assembly includes a first propeller and a second propeller operatively coupled to a coupling shaft and configured to pivot with respect to one another about a propeller rotation axis. The propeller assembly additionally includes a coupling assembly operatively coupled to the first propeller and the second propeller and configured to transition between a plurality of pivotal configurations defined between and including a stowed configuration and a deployed configuration. The coupling assembly transitions from the stowed configuration toward the deployed configuration when a coupling assembly rotational velocity rises above a threshold stowed rotational velocity. In examples, an aircraft includes one or more propeller assemblies operatively coupled to a fuselage.

Abstract: An aircraft lavatory complex incorporating lavatories accessible to passengers of reduced mobility (PRM) is disclosed. Left-side and right-side full service lavatory units are accessible via left-side and right-side lavatory access doors opening in opposing directions. The left-side and right-side full service lavatory units are separated by a common central partition repositionable by cabin crewmembers (but protected from independent repositioning by occupants of either lavatory unit) to enlarge either of the left-side or right-side lavatory units for enhanced PRM accessibility.

Abstract: An aircraft door arrangement, comprising a door pivotable between closed and open positions, a frame section in a door opening region, and an articulation arrangement connecting the door and frame section. First and second arms are mounted on the frame section, rotatable about first and second axes, respectively. Third and fourth arms are mounted on the door, rotatable about third and fourth axes, respectively. The second arm, at a first position, is rotatably coupled to the fourth arm about a fifth axis, and at a second position, closer to the second axis, is rotatably coupled to the third arm about a sixth axis. The third arm, at a third position, is rotatably coupled to the first arm about a seventh axis, and at a fourth position, closer to the third axis, is rotatably coupled to the second arm about the sixth axis. All axes are oriented substantially parallel.

Abstract: A modular aft galley and lavatory complex is disclosed. The galley complex is situated aft of an aircraft passenger cabin and incorporates left-side, right-side, and aft galley structures together partially enclosing an interior workspace, the left-side and right-side galley structures separated by a center aisle. Each galley structure includes trolley bays capable of securing trolleys therewithin. Each trolley can be removed from its trolley bay into the interior workspace or central aisle for use in catering or service operations inflight. Each galley structure includes storage bays accessible from the interior workspace. Between the upper and lower portions are flat workdecks and galley insert bays capable of accepting ovens, chillers, beverage makers, and other galley insert devices. Either the left or right galley structure includes a lavatory complex adjacent to the passenger cabin, incorporating aft lavatory units and a galley extension housing additional storage and cart space.

Abstract: A flow guide body for an aircraft includes a main body having an outer aerodynamic surface having a plurality of outlet openings, and flow control devices, each having an inlet, an interaction chamber, a first outlet and a second outlet. A first control inlet is connected to the interaction chamber at the first side of the chamber axis. The outlets are each connected to outlet openings in the aerodynamic surface. Each outlet has a control outlet. A second flow control device is arranged such that one outlet is connected with the inlet of the first flow control device. One of the control outlets of the first flow control device is connected to the first control inlet of the first flow control device, and the other of the control outlets of the first flow control device is connected to the first control inlet of the second flow control device.

Abstract: Continuous skin leading edge slats are disclosed. A disclosed example leading edge slat for use with an aircraft includes a single-piece nose skin defining upper and lower external surfaces of the leading edge slat, where the single-piece nose skin is to extend between a fore end and an aft end of the leading edge slat, and a box spar coupled to an inner surface of the single-piece nose skin. The box spar includes lateral walls extending away from the inner surface of the single-piece nose skin. The lateral walls define at least one compartment of the box spar.

Abstract: A differential thrust vectoring system including a first thruster rotation assembly configured to rotate a first thruster relative of an aircraft, a second thruster rotation assembly configured to rotate a second thruster of an aircraft, and an actuator. The system is configured such that actuation of the actuator causes disparate rotation about the tilt axis of the first and second thrusters.

Abstract: A flight control surface assembly adapted to be mounted to a main wing of an aircraft includes a flight control surface having a first portion and a second portion spaced from each other, a connection assembly adapted for movably connecting the flight control surface to the main wing, such that the flight control surface is selectively movable in a predetermined movement between a retracted position and an extended position with respect to the main wing, and for each of the flight control surface, a first roller with a first axial face and a second roller with a second axial face facing the first axial face mounted rotatably and coaxially. with a gap between the first and second axial end faces. A biasing mechanism biasing the first and second rollers towards each other, and a transmission mechanism coupled between the flight control surface and the rollers are included.

Abstract: An aerial vehicle having incline-controllable wings, according to one embodiment, can comprise: a body; a thrust part connected to the body and having a propeller and a rotary shaft; and the wings respectively arranged at both sides of the body, and disposed to be spaced from the thrust part. The wings pitch and rotate around a horizontal axis of the body such that the angle of attack of the wings is controlled, and an angle between the rotary shaft of the thrust part and the wing can vary because of the pitching and rotation of the wings.

Abstract: Rotor assemblies for aircraft are described where one or more blades of the rotor assembly includes a blade alignment device that passively orients a blade in response to an airflow around the blade alignment device when the rotor assembly is free-wheeling. One embodiment comprises a method of operating a rotor assembly for aircraft. The method comprises operating the rotor assembly in a free-wheeling state, where the rotor assembly includes a rotary hub that rotates about an axis and a plurality of blades extending radially from the rotary hub. At least one of the plurality of blades includes a blade alignment device. The method further comprises aligning the at least one of the plurality of blades in response to airflow around the blade alignment device when the rotor assembly is in the free-wheeling state.

Abstract: Retractable propulsor assemblies for aircraft are described that generate lift during vertical take-off, hover, and vertical landing. The retractable propulsor assemblies are deployed from a compartment in a fuselage of the aircraft to transition the aircraft into vertical flight, and are stowed in the compartment during cruise flight to reduce aerodynamic drag on the aircraft. One embodiment comprises a method of operating a VTOL aircraft. The method comprises deploying the retractable propulsor assembly from the compartment of the fuselage to provide the lift for vertical flight. The method further comprises transitioning the VTOL aircraft from the vertical flight to cruise flight, and stowing the retractable propulsor assembly in the compartment during the cruise flight to reduce the aerodynamic drag on the VTOL aircraft.

Abstract: In order to make available a space-saving sanitary unit having a toilet which offers improved user convenience to persons with restricted mobility, a cabin module for an aircraft is described which has a sanitary unit. The sanitary unit has a toilet cubicle with a toilet. The toilet cubicle is formed by four side walls and the toilet is arranged on a first side wall. A first access door is arranged in a second side wall, which extends transversely to the first side wall and adjoins the first side wall. A surface which is designed to at least partially accommodate a wheelchair is provided as an option within the toilet cubicle. The cabin module is configured to be installed with the second side wall transversely to a direction of flight. The first side wall 18a is aligned with an external wall in the installed state.

Abstract: A propulsion system for omnidirectional maneuverability and efficient forward flight of an airship. The propulsion system includes only fixed, unidirectional engines (17, 19, 20). Thrust vectors of the fixed engines (19, 20) are oriented in a way that their speeds can be chosen such that all forces acting on the airship (i.e., engine thrusts, gravity, buoyancy, wind and potentially others) together result in the desired motion. The engines may be four ducted fans (17) at the bow of the aircraft and four ducted fans (19) at the stern of the aircraft. The thrust vectors of the engines can be decomposed into three vectors of equal length that are each parallel to one of the three axes of a Cartesian coordinate system. Efficient forward flight is achieved by an additional engine (20) at the stern of the airship.

Abstract: A passenger door arrangement for an aircraft segment, which arrangement comprises a passenger door that is configured to assume a raised state and a lowered state, and a girt bar for arming and disarming an escape slide, the girt bar not altering its position relative to the passenger door in the transition from disarming to arming when the passenger door is in the lowered state. Also an aircraft segment, which comprises the passenger door portion and a fuselage portion, an external engagement means being fixed to the fuselage portion.

Abstract: A passive hub flapping lock including: one or more lever arms, each lever arm rotatably coupled to a pivot and comprising a first lever arm end and a second lever arm end; one or more stop wedges; one or more frames coupled to the one or more stop wedges, each frame coupled to the first lever arm end of one of the one or more lever arms; one or more weight sets, each weight set comprising one or more weights coupled to the second lever arm end of one of the one or more lever arms; and one or more pivot torsion springs, each pivot torsion spring positioned at the pivot.

Abstract: Disclosed herein is an auxiliary-pod mounting system for mounting an auxiliary pod to a landing skid assembly of a helicopter. The landing skid assembly comprises a forward crossbar, a rearward crossbar, and skids coupled to the forward crossbar and the rearward crossbar. The auxiliary-pod mounting system comprises a first rail. The auxiliary-pod mounting system also comprises a second rail, spaced apart from the first rail. The auxiliary-pod mounting system further comprises a mounting plate, interposed between and coupled to the first rail and the second rail. The mounting plate comprises pod engagement features configured to engage the auxiliary pod and to secure the auxiliary pod to the mounting plate. The auxiliary-pod mounting system additionally comprises a plurality of brackets configured to couple the first rail and the second rail to the forward crossbar and the rearward crossbar of the landing skid assembly of the helicopter.