Abstract: Propulsion system for a helicopter comprising a main engine, a main rotor, a main gearbox including an output mechanically connected to the main rotor, a reduction gearbox mechanically coupled between the main engine and a first input of the main gearbox, and an assistance device. The assistance device comprises a first electric machine mechanically coupled to the reduction gearbox and configured to operate as an electric generator to take off energy produced by the main engine, and a second electric machine mechanically coupled to a second input of the main gearbox, the second electric machine being supplied with electrical power by the first electric machine and configured to operate as an electric motor to deliver additional mechanical power to the main gearbox.

Abstract: A wing for an aircraft is disclosed having a fixed wing, a foldable wing tip portion mounted to the fixed wing via a hinge rotatable about a hinge axis between an extended position and a folded position, and an actuation mechanism for moving the foldable wing tip portion. The actuation mechanism includes a drive arm mounted to the fixed wing in a manner rotatably driven about a drive axis, and the drive arm is configured to effect movement of the foldable wing tip portion between the extended position and the folded position upon rotation of the drive arm about the drive axis.

Abstract: A door assembly for a payload bay (10) having an opening (12), the door assembly comprising at least one door (20, 220). The at least one door comprises: a panel section (22, 222) having a first end (24, 224) and a second end (26, 226); and a first mounting member (30, 230) arranged orthogonally to the panel section at the first end and having a first engagement feature (31, 231) having a rotational axis (18, 218) about which the panel section is arranged to rotate. The engagement feature is arranged to engage with a first fixing member (16, 216) on one side of the payload bay to rotatably couple the panel section to the payload bay. The at least one door is arranged to translate between a closed configuration, in which the panel section is arranged in the same plane as the opening, and an open configuration, in which the panel section is arranged at at least 90 degrees to the plane of the opening, by rotating about the rotational axis.

Abstract: One variation of a system for generating thrust at an aerial vehicle includes: a primary electric motor; a rotor coupled to the motor; an internal-combustion engine; a clutch interposed between the motor and an output shaft of the internal-combustion engine; an engine shroud defining a shroud inlet between the rotor and the internal-combustion engine, extending over the internal-combustion engine, and defining a shroud outlet opposite the rotor; a cooling fan coupled and configured to displace air through the engine shroud; and a local controller configured to receive a rotor speed command specifying a target rotor speed, adjust a throttle setpoint of the internal-combustion engine according to the target rotor speed and a state of charge of a battery in the aerial vehicle, and drive the primary electric motor to selectively output torque to the rotor and to regeneratively brake the rotor according to the target rotor speed.

Abstract: An aircraft lavatory monument is provided that includes a first lavatory including a first door providing access to the first lavatory from an aisle of an aircraft; a second lavatory proximate the first lavatory, the second lavatory including a second door providing access to the second lavatory from the aisle of the aircraft; and a movable wall disposed between the first lavatory and the second lavatory, the movable wall including a latching mechanism positioned on an exterior edge of the movable wall and accessible from the aisle of the aircraft, where the latching mechanism, responsive to being in a locked position, causes the movable wall to be positioned at a first position separating the first lavatory from the second lavatory and providing privacy therebetween, and where the latching mechanism, responsive to being in an unlocked position, allows the movable wall to collapse thereby forming an enlarged bathroom space.

Abstract: A system and method for a blended wing body aircraft with permanent tanks is presented. The aircraft comprises a blended wing body and at least a tank permanently attached the blended wing body. The at least a tank is configured to store liquified gas fuel and further comprises at least a vent configured to vent gaseous fuel from the at least a tank and an insulation to reduce thermal transfer to the liquified gas fuel inside of the at least a tank.

Abstract: Systems, apparatuses and methods provides for technology that moves a locking vent door from an opening position to a locking position, where in the opening position, the locking vent door opens a locking vent, and in the locking position, the locking vent door closes the locking vent. When the locking vent door is in the locking position, the technology prohibits movement of a handle from an engaged position to a disengaged position. When the locking vent door is in the opening position the technology moves the handle from the engaged position to the disengaged position, moves a lock from a locking position to an unlocking position, and moves a pressurization vent door from the pressurization position to the depressurization position based on the lock being moved from the locking position to the unlocking position.

Abstract: An anti-aircraft system is described and includes an unmanned aerial vehicle (UAV) comprising a body; a wing connected to the body; and propulsion systems associated with the wing, wherein the propulsion systems comprise pylons releasably connected to opposite ends of the wing such that the propulsion systems may be selectively released from the wing during flight of the UAV.

Abstract: An aircraft is disclosed, including a fuselage having a longitudinal axis and a passenger compartment having a floor and a ceiling. The aircraft further includes rows of seats fixed to the floor adjacent and aisle and a mobile container suspended from multiple tracks mounted on the ceiling over the aisle.

Abstract: Apparatus for controlling multi-rotor vehicle vibrations and related methods are disclosed herein. An example apparatus includes a vibration level detector to determine a vibration level of a frame of a vehicle based on data received from a sensor of the vehicle, the vehicle including a rotor. The apparatus includes a rotor operation analyzer to determine an operational parameter of the rotor based on the vibration level. The apparatus includes a communicator to transmit an instruction including the operational parameter to a controller of the rotor.

Abstract: Vertical takeoff and landing vehicles (VTOLs) of the type used for the point-to-point delivery and transport of payloads (e.g., packages, equipment, etc.) and personnel, are significantly stabilized at least during takeoff and landing with present aspects significantly ameliorating or significantly eliminating destabilizing effects, including ground effect, during VTOL takeoff and/or landing.

Abstract: A method for defining the steady state speed of an auxiliary power unit (APU) of an aircraft according to the aircraft operating condition.

Abstract: An unmanned aerial vehicle (UAV) includes a fuselage, electronics disposed with the fuselage, a heat sink, and a solar shield. The heat sink is thermally connected to the electronics and includes a cooling plate disposed on or extends through an exterior surface of the fuselage. The cooling plate is exposed to an external environment of the UAV to conduct heat from the electronics to the external environment via convection. The solar shield extends over the cooling plate and defines an air scoop within which the cooling plate is disposed. The air scoop directs airflow from the external environment across the cooling plate. The solar shield shades the cooling plate from solar radiation to prevent or reduce solar heating of the cooling plate.

Abstract: A fastening system for an aircraft configured to fasten at least one tank intended to contain liquid hydrogen includes a longitudinal box, an upper structure fastened to an upper side of the longitudinal box, a lower structure fastened to a lower side of the longitudinal box and at least two fastening frames including, on either side of the vertical plane of symmetry (P1), a fastening device for connecting a tank to the upper structure. The fastening system further includes at least two fastening devices for connecting a fastening point of the tank to the longitudinal box and at least two fastening devices for connecting a fastening point of the tank to the lower structure. The fastening system makes it possible to securely fasten at least one hydrogen tank on board an aircraft (AC).

Abstract: Flow control ducted fans are disclosed. A disclosed example flow control apparatus for use with an aircraft includes a duct defining an inner cavity with a primary flow path, a fan disposed in the inner cavity, an aperture on an exterior surface of the duct and upstream from the fan, the aperture fluidly coupled to the inner cavity to define a secondary flow path, and a door to control a degree to which the aperture is opened.

Abstract: A platform system is configured for use within an internal cabin of a vehicle. The platform system includes a base, and a support plate moveably coupled to the base. The support plate is configured to be moved in relation to the base to allow a wheelchair to be selectively secured to and removed from the support plate. For example, the support plate is moveable between a first position in which the wheelchair is supported on the support plate in a forward-facing position within the internal cabin, and a second position in which at least a portion of the support plate is moved into an aisle of the internal cabin to allow the wheelchair to be moved onto and off the support plate.

Abstract: A modular passenger seat system includes a passenger seat having a seat leg with a distal end portion. The distal end portion includes a tube. The tube includes a sidewall having a first aperture and a second aperture. The modular passenger seat system includes a first detent member and a second detent member disposed within the first aperture and the second aperture in the sidewall of the tube. Each of the first detent member and the second detent member is configured to extend through the first aperture and the second aperture when the tube is received within the bushing. The modular passenger seat system includes a shaft movably disposed within the seat leg. The shaft has a lower end which when displaced against a biasing member enables the first detent member and the second detent member to retract inwardly into the tube.

Abstract: An access panel to be received in an access aperture in a lower skin of a wing on an aircraft incorporates a body surrounded by a sealing flange. The body is configured to be received in the access aperture and the sealing flange is configured to be received on a sealing land surrounding the access aperture. An integral heat exchanger extends from a top surface of the body into a fuel tank in the wing to conduct heat from the fuel to an external surface of the access panel.

Abstract: A pitch angle blocking device for blocking the pitch angle of a multi-blade rotor that has neighboring first and second rotor blades in circumferential direction that extend from a rotor hub of a rotary-wing aircraft In non-operational mode of the rotary-wing aircraft. The present embodiments further relate to a multi-blade rotor of a rotary-wing aircraft that is adapted to receiving such a pitch angle blocking device, and to a rotary-wing aircraft with such a multi-blade rotor. The pitch angle blocking device comprises first and second attachment means that are configured to be non-rotatably and releasably attached to the first and second rotor blades spaced apart from the rotor hub, and a connecting device that non-rotatably connects the first attachment means with the second attachment means.

Abstract: A locking device locks a landing gear mounted in rotation on an aircraft and includes a deployment hydraulic jack including a first chamber connected to a first hydraulic supply and a second chamber connected to a second hydraulic supply. The locking device includes a hydraulic actuator connected to a rotary distributor. The rotary distributor includes a coupling operationally connecting the rotary distributor to a strut of the landing gear, a first supply port fluidly connected to the first hydraulic supply, and a first outlet port fluidly connected to the hydraulic actuator.