Abstract: An aerial refueling system utilizes the full drogue-probe coupling event as a control parameter for hose control. A variety of different types of signal sending and signal receiving devices may be used to indicate a coupling event between the drogue and probe. A positive coupling signal may serve to trigger a hose reel actuator to take up slack in the hose 16.

Abstract: An aircraft passenger seating unit and aircraft seating arrangements including seating units, each seating unit configured as a window-facing seating unit or as an aisle-facing seating unit. Each individual seating unit including first and second laterally adjacent seats mounted on a common platform and oriented at an angle to a longitudinal aircraft axis. A forwardmost point of each of the first and second seats, when in an upright sitting position, resides along a plane common to both the first and second passenger seats perpendicular to the longitudinal aircraft axis to allow longitudinal alignment of rows and increased seating density.

Abstract: An aircraft passenger compartment suite may include a first side with a first display device, a second side with a second display device, and a privacy divider separating the first side and the second side. The first display device may be configured to actuate between a first deployed position and a first stowed position via a first stowage mechanism. The second display device may be configured to actuate between a second deployed position and a second stowed position via a second stowage mechanism. The privacy divider may include one or more panels configured to actuate between a panel deployed position and a panel stowed position. The privacy divider may be open when at least one of the first display device is in the first stowed position, the second display device is in the second stowed position, or the one or more panels are in the panel stowed position.

Abstract: The present disclosure provides an aircraft security door as well as methods, systems and apparatus for handling an aircraft security door. In one implementation, a method for installing an aircraft security door onto an aircraft is disclosed. The method includes transferring the aircraft security door to an aircraft service stair, supporting the aircraft security door by a bridge crane coupled to the aircraft service stair, positioning the aircraft service stair in proximity to a fuselage of the aircraft adjacent to an opening in the fuselage, positioning the aircraft security door relative to the opening using the bridge crane, and securing the aircraft security door to the opening.

Abstract: A wing system (2) for an aircraft includes a movable flow body (6) and a cover panel (8), wherein the flow body (6) and the cover panel (8) both are movably supported on a main wing body (4). While the flow body (6) is actively driven into upwards or downwards deflected positions, the cover panel (8) is coupled with the flow body (6) to follow its motion. The cover panel covers a part of the flow body (6) and the main wing body (4) in order to provide a substantially continuous, closed outer contour.

Abstract: Transformable seat assembly includes a seat support structure and a seat connected to the seat support structure with a first hinge having a first axis of rotation. A back support structure is connected to the seat support structure with the back support structure positioned on a back side portion of the seat support structure and the first hinge is positioned on an opposing front side portion of the seat support structure. A wall member having a first end portion connected to the back support structure with a second hinge having a second axis of rotation, wherein the seat is rotatable about the first axis of rotation from an occupant support position to a deployed position and the wall member is rotatable about the second axis of rotation from an overlying position with respect to the back support structure to the wall member extending away from the back support structure.

Abstract: The invention relates to a fastening unit (100) for movably fastening an aircraft component (300) to a support structure (400) of an aircraft (500). The fastening unit (100) has a connection element (5) having a hole (5a). The fastening unit (100) also has a first support arm (1) having a first end (1a) for connecting to the support structure (400) of the aircraft (500) and having a second end (1b) for connecting to the connection element (5). The fastening unit (100) also has a second support arm (2) having a first end in (2a) for connecting to the support structure (400) of the aircraft (500) and having a second end (2b) for connecting to the connection element (5).

Abstract: An aircraft propulsive assembly comprising a pylon and a turbomachine attached to the pylon by an engine attachment system. The attachment system comprises two engine attachments each secured to the pylon and to the turbomachine. Each engine attachment comprises at least one fitting attached to the pylon by a first main link, and attached to the turbomachine by a second main link. Each main link has a clearance-free fit. The fitting being, moreover, secured to either the pylon or the turbomachine by an additional link, referred to as a safety link, which backs up one of the main links. The safety link is in the form of an assembly with a clearance. The assembly of the safety link comprises at least one passage which receives, in a sliding manner, a tool for checking a presence of the clearance.

Abstract: An assembly for an aircraft, which includes a pylon with a bearing face and a contact face, an engine mount with a bearing face and a contact face bearing against the contact face of the pylon, at least two bolts comprising a threaded stem with a head and a nut bearing against the bearing face of the engine mount, for each head, a bearing washer with a first bearing face and a second bearing face, where the second bearing face of the bearing washer bears against the bearing face of the pylon, and where the head bears against the first bearing face of the bearing washer, a shoe, and, for each bearing washer, a clamp that is secured to the shoe and comprises a first branch and a second branch between which the bearing washer is clamped and is free to rotate.

Abstract: An engine attachment configured to link an engine and an aircraft pylon comprising a first end fitting having two mutually parallel wings, a joining piece positioned between the first end fitting wings and linked to the first end fitting by a link system, fixing elements, linking the first end fitting and the pylon, including first and second fixing elements positioned between the first end fitting wings which are inclined by an angle of between 10 and 45° to be able to be put in place and removed in the presence of the joining piece linked to the first end fitting by the link system. The inclined fixing elements absorb lateral loads. The joining piece and the first end fitting are linked by the link system before the engine is fixed to the pylon. The engine is fixed to the pylon by putting the fixing elements in place.

Abstract: A forward engine attachment system for an engine of an aircraft, the forward engine attachment system including a jet engine pylon including, in the region of the forward part thereof, a front part having an attachment wall, and a forward engine attachment with a connecting rod system on either side of a median plane, wherein each connecting rod system is fixed in articulated manner by at least one first link point to the attachment wall and is designed to be fixed in an articulated manner by at least one second link point to a forward part of the engine. Such a forward engine attachment system thus includes a direct coupling between the jet engine pylon and the engine, allowing the production of an assembly that is less heavy and is easier to produce.

Abstract: A balloon system, preferably including a balloon and a payload. A balloon, preferably including a plurality of gores, a plurality of load members, and an apex fitting. A method of balloon system operation, preferably including deflating a balloon, and optionally including operating the balloon system in flight and/or landing the balloon system.

Abstract: Offset drive arm actuation of inboard flaps is disclosed. A disclosed example apparatus includes an inboard flap support for moving an inboard flap. The inboard flap support includes an offset drive arm extending between a first attachment point of the inboard flap and a first pivot of a support, and a linkage extending between a second attachment point of the inboard flap positioned at a different position from the first attachment point and a second pivot of the support.

Abstract: A method of adjusting a center of gravity (CG) of an aircraft includes: inputting at least one load parameter into a flight computer, determining, via a processer of the flight computer, the CG of the aircraft. Responsive to a determination by the processor that the CG is outside of a CG envelope, moving at least a first movable ballast of a plurality of movable ballasts from a first ballast dock to a second ballast dock to move the CG toward the CG envelope. Each of the first and second ballast docks may include a housing and a first ballast tray secured within the housing and comprising a plurality of channels.

Abstract: A fastener for holding together two or more structures. The fastener includes a first bush and a second bush. The first bush includes a hollow shaft having a first end and a second end opposite to the first end. The first end of the first bush has a first radially-extending protrusion. The second bush includes a hollow shaft having a first end and a second end opposite to the first end. The first end of the second bush has a second radially-extending protrusion. The second end of the second bush is configured to connect to the second end of the first bush so as to resist separation of the first and second bushes and so as to define an axial hole through the fastener defined by the shaft of the first bush and the shaft of the second bush.

Abstract: A system for controlling turbulence of fluid flowing past a window includes an imaging device compartment defining an interior and an exterior separated by a window, wherein the window encloses at least a portion of the interior, wherein the exterior includes at least one turbulator on a side upstream of the window positioned to induce turbulence over the entirety of a boundary layer of the fluid flowing past the window for even heat transfer between the fluid and the window.

Abstract: Embodiments are directed to a selectable drive system that allows a rotor gearbox to send torque to a proprotor assembly and/or through a multiplier planetary gear set to a pylon-mounted ducted fan thrust unit. The rotor drive system may be a stop-fold system in which rotor blades can be folded when not rotating. This allows a normally idle lift engine to provide additional aircraft thrust during cruise where an aircraft is typically using only a dedicated thrust engine for high speed flight. An inline engage/disengage actuator or “shift fork” on the rotor gearbox is used to select the torque-output direction. The multiplier planetary gear set increases the output RPM that is received from the rotor gearbox and that is applied to the thrust fan unit.

Abstract: A linking device connecting an aircraft engine and a primary structure of an aircraft pylon, comprising a support connected to the primary structure, a spreader, extending between first and second ends that has a central part connected to the support by a principal link comprising a principal rotation axis, at least one system for limiting the deflection of the spreader comprising an extension secured to the spreader and also upper and lower stops, secured to a fitting secured to the support, between which the extension is positioned.

Abstract: An unmanned aircraft system includes a flying wing airframe having leading and trailing edges with respective sweep angles. A thrust array is coupled to the airframe and includes first and second motor mounts each selectively rotatably coupled to the leading edge by a locking joint. Each motor mount has first and second propulsion assemblies coupled to respective first and second distal ends thereof. A power system is operably associated with the thrust array and is operable to provide power to each propulsion assembly. A flight control system is operably associated with the thrust array and is operable to independently control the speed of each propulsion assembly. In a flight configuration, each motor mount is locked substantially perpendicular with the leading edge by the respective locking joint. In a compact storage configuration, each motor mount is locked substantially parallel with the leading edge the respective locking joint.

Abstract: A side of body carbon fiber reinforced polymer (CFRP) composite rib assembly that is formed by connecting an aft CFRP rib web, a middle CFRP rib web, and a forward CFRP rib web together. The side of body CFRP rib assembly includes a plurality of stiffeners connected to the aft CFRP rib web, the middle CFRP rib web, or the forward CFRP rib web. A first stiffener connects the aft CFRP rib web with the middle CFRP rib web and a second stiffener connected the forward CFRP rib web to the middle CFRP rib web. The stiffeners may be connected via fasteners or may be co-bonded or co-cured with the side of body CFRP rib web. The stiffeners connected to the side of body CFRP rib assembly may include more than one shape and may be aluminum, a thermoset, and/or a thermoplastic.