Abstract: Assemblies and methods for facilitating the assembly of aircraft wings to a fuselage are disclosed. In some embodiments, a wing unit includes features that are configured to define one of more parts of a pressure vessel that is partially defined by the fuselage portion. In some embodiments, the aircraft assemblies disclosed herein comprise one or more first structural interfaces that permit positional adjustment between the wing unit and the fuselage portion so that one or more second structural interfaces may be finished only after such positional adjustment. In some embodiments, the aircraft assemblies disclosed herein comprise one or more structural interfaces that are disposed outside of the wing unit in order to eliminate or reduce the need for assembly personnel to access the interior of the wing unit to carry out the structural assembly of the wing unit to the fuselage portion.

Abstract: An escape hatch for an aircraft includes a door body having an exterior side and an interior side opposite the exterior side; an exterior handle movably connected to the door body, the exterior handle rotatable between a stowed position, in which the exterior handle is recessed within an opening of the door body, and an unstowed position, the exterior handle being accessible from the exterior side of the door body to open the door; and a visual indicator connected to the door body and visible from the interior side of the door body only when the exterior handle is in the stowed position.

Abstract: A method and apparatus for generating an interactive interface on a display of an aircraft comprising: determining that an aircraft system has a faulty condition, the aircraft system comprising a plurality of system functions, the system functions being independently 5 actuatable, the determining comprising: generating an indication of which one of the system functions is associated with the faulty condition; generating the interactive interface, the interactive interface comprising a visual representation of a control panel, the control panel comprising a plurality of actuatable switches, each one of the actuatable switches being associated with a corresponding one of the system functions, the generating comprising: 0 determining, based on the indication, which one of the actuatable switches is to be associated with a visual faulty status, and displaying, on the display, the interactive interface comprising the visual faulty status.

Abstract: Methods and related apparatus for improving synchronization of two or more engines on an aircraft are disclosed. Such method may be used where each engine comprises a first spool and a second spool, and, where a rotational speed of a first spool of a first engine has been substantially synchronized with a rotational speed of a first spool of a second engine. An exemplary method comprises receiving a value of a sensed parameter useful in controlling the first engine; adding a bias to the value; and using the biased value for controlling the first engine to cause a change in rotational speed of the second spool of the first engine in relation to the rotational speed of the first spool of the first engine.

Abstract: A lock for an aircraft door. The lock includes an outer shell having an inner cavity. A core is rotatably mounted within the inner cavity to rotate about an axis of the core. The core has a keyhole extending through the core from a first end of the core for receiving a key therein, to an opposed second end of the core. The keyhole defines an air leakage path through the core. A cam has a cam arm mounted about the core and is rotatable therewith. The second end of the core protrudes from the cam. A cover is attached to the second end of the core. The cover blocks the keyhole at the second end of the core and obstructing the air leakage path. An aircraft door, methods, and a retrofit kit are also disclosed.

Abstract: A blended wing body aircraft having an interior cabin with a usable volume of at most 4500 ft3 and a cabin aspect ratio of at most 4, wherein a combination of the wings and center body has a wetted aspect ratio of at least 1.7 and at most 2.8. Also, a blended wing body aircraft having an interior cabin with a usable volume of at least 1500 ft3 and at most 4500 ft3 and a cabin aspect ratio of at least 2 and at most 4, wherein a combination of the wings and center body has a wetted aspect ratio of at least 1.9 and at most 2.7. Also, a blended wing body aircraft wherein at least each profile section having normalized half-span values from 0 to 0.3 has a leading edge having a normalized height having a nominal value within the range set forth in Table 4.

Abstract: There is described a vehicle color-lighting control system. The system comprises at least one sidewall (101) having an electrically-controllable coloring mechanism (106) embedded therein and arranged for coloring at least a portion of the at least one sidewall with at least one first color; a lighting sub-system (110) comprising at least one light source (112) mounted within the vehicle to illuminate an interior of the vehicle with at least one second color in a first state and with at least one third color in a second state; and a controller coupled to the coloring mechanism and the lighting sub-system and configured for operating the coloring mechanism to color the at least one portion of the at least one sidewall with the at least one first color and concurrently illuminate the interior of the vehicle with the at least one second color.

Abstract: An insert for an air intake of a suction duct, the insert including an inner portion configured to extend within the suction duct, a mating portion configured for sealingly engaging the air intake, and an outer portion configured for extending outside of the suction duct. The inner portion includes a conduit having a central axis extending along an inlet direction at the inlet end and along an outlet direction at the outlet end, the inlet and outlet directions being non-parallel. The outlet end has a smaller cross-sectional area than that of the suction duct. The insert includes an inlet in fluid communication with the inlet end of the conduit. The outer portion includes a curved lip surrounding at least part of an inlet opening of the inlet, the lip configured to direct a flow into the inlet opening and toward the inlet end of the conduit.

Abstract: An aircraft cabin comprising a credenza and a lounge chair disposed above the credenza is disclosed. The lounge chair is adjustable between a first configuration defining a first seating arrangement and a second configuration defining a second seating arrangement. Also disclosed is a mechanism to facilitate the adjustment of the lounge chair.

Abstract: A handle assembly for an aircraft door includes a shaft to open the door, an exterior handle deployable between a stowed position and a deployed position, and a clutch having a driving member coupled to the exterior handle and a driven member coupled to the shaft. The clutch is configurable between a disengaged configuration in which the driving member and the driven member are disengaged, and an engaged configuration in which the driving member and the driven member are engaged so that actuation of the exterior handle rotates the shaft to open the door. Rotation of the exterior handle between the stowed position and the deployed position drives an axial movement of the driving member toward the driven member to configure the clutch to the engaged configuration.

Abstract: A wing assembly includes a swept wing body, a leading edge of the wing body extending outward and rearward from a wing root to a wing edge; a first slat selectively movably connected to the wing body; and a second slat selectively movably connected to the wing body, the second slat being disposed outboard of the first slat, a flexible sealing member disposed and connected between the first slat and the second slat; at least a portion of the first slat, at least a portion of the second slat, and at least a portion of the flexible sealing member defining a slat gap therebetween, at least a majority of the slat gap being substantially parallel to a predetermined local airflow direction. An aircraft is also disclosed which includes a fuselage; and two oppositely disposed wing assemblies connected to the fuselage.

Abstract: An aircraft and an aircraft wing assembly for an aircraft. The wing assembly includes a wing body assembly including a wing body; and at least one protruding portion connected to the wing body. The protruding portion extends aftwardly from an aft side of the wing body assembly, a leading edge of the wing body assembly defining a leading edge line, a trailing edge of the wing body assembly defining a trailing edge line extending between the inboard end and the outboard end, the trailing edge including a trailing edge of the protruding portion, the trailing edge line being a smooth line, a chord distance being defined longitudinally from the leading edge line to the trailing edge line, the chord distance at a center of the protruding portion being greater than the chord distance inboard of protruding portion and outboard of the protruding portion.

Abstract: Systems and methods associated with electrical systems of aircraft are disclosed. A method disclosed herein comprises generating electricity using an electric generator operatively coupled to an engine of the aircraft, supplying the electricity generated using the electric generator to a baseline power bus; generating electricity using an electric starter generator operatively coupled to the engine; and supplying the electricity generated using the electric starter generator to a supplemental power bus independent from the baseline power bus.

Abstract: A method of and a system for propagating a configuration setting of a 3D model to other 3D models, the 3D model and the other 3 Ds being part of a same 3D model category. The 5 method comprises dividing the 3D model into a first plurality of surfaces; associating to each one of the first plurality of surfaces, a unique surface identifier. For each one of the other 3D models, the method comprises dividing the one of the other 3D models into a second plurality of surfaces; establishing a correspondence; associating, for each one of the second plurality of surfaces corresponding to one of the first plurality of surfaces. The method also comprises 0 selecting the configuration setting of the 3D model; determining the unique identifier of the 3D model to which the configuration setting is to be applied; and propagating, the configuration setting to the other 3D models.

Abstract: Systems and methods for deploying adjacent trailing edge flaps that are part of different flap assemblies of different stiffnesses are disclosed. An exemplary method comprises: deploying a first flap of a first flap assembly having a first stiffness by a first deployment amount and deploying a second flap adjacent the first flap by a second deployment amount where the deployment amount of the first flap part of the flap assembly of lower stiffness is greater than the second deployment amount of the second flap part of the flap assembly of higher stiffness. The difference in deployment amounts may be adapted to improve continuity between the first flap and the second flap when the first and second flaps are deployed and subjected to an aerodynamic load.

Abstract: Systems and methods for operating an aircraft door including an airstair are disclosed. In one embodiment, the system includes a hinge configured to pivotally couple a lower portion of the door to a fuselage of an aircraft, a lift mechanism and an interlock. The lift mechanism causes a movement of the door relative to the hinge between a lowered position and a lifted position. The interlock is configurable between: a locked configuration where the movement of the door relative to the hinge is prevented; and an unlocked configuration where the movement of the door relative to the hinge is permitted.

Abstract: A system for operating a configuration platform. The system comprising a conversion pipeline, the conversion pipeline allowing converting a first set of data associated with a computer-aided design (CAD) system into polygon meshes suitable for rendering of the portion of a monument and configuration data. The system also comprising a content management system, the content management system storing the polygon meshes and the configuration data; and a 3D real-time engine, the 3D real-time engine allowing to determine, based on the configuration data, at least one of the positioning of the monument, the material surface associated with the monument, the material grain direction associated with the monument, the lighting associated with the monument, the annotations associated with the monument, the alternate states associated with the monument and the kinematic sequence associated with the monument; and to render the portion of the monument by the 3D real-time engine.

Abstract: A noise attenuating device for reducing acoustic resonance in a cavity of an aircraft with an opening in a skin of the aircraft defining a first surface area and an opening peripheral edge includes a connection mechanism for securing the noise attenuating device in proximity to the opening in the skin of the aircraft and an exterior surface. The exterior surface defines a second surface area that is less than the first surface area of the opening and a device peripheral edge, which has a first section having an edge profile complimentary to at least a portion of the opening peripheral edge and a second section having an indented edge profile in relation to the first section such that when the noise attenuating device is secured within the opening, at least one gap is formed between the device peripheral edge and the opening peripheral edge.

Abstract: There is disclosed an emergency door positionable in an exit opening of an aircraft. The door has door supports mountable to the lower wall and each having a pivot point. A first pivot axis is defined between the pivot points. A block is mountable to the lower wall and is offset from a center of the lower wall. A door body is mountable within the opening to the door supporting structure and pivotally mountable to the door supports. The door body is pivotable about the first pivot axis from an initial position in which the door body is within the opening, until the door body is disengaged from the door supports. A bottom portion of the door body abuts against the block to define a removal pivot point. The door body is pivotable about the removal pivot point to remove the door body from the exit opening.