Abstract: The invention provides a kit of parts for assembling an aircraft seat unit, comprising a frame with a slot, a panel for forming a shell of the aircraft seat unit and defining a footprint of the aircraft seat unit, having a first end and a second opposite end, the first end configured to be slid in and out of the frame slot to provide a variable dimension from the frame to second opposite end of the panel, and a fixing mechanism for fixing the panel within the frame slot, in a configuration providing a desired value of aircraft seat unit variable dimension. The invention also provides a plurality of such kits of parts, an aircraft seat unit and an aircraft cabin comprising a plurality of such aircraft seat units or made from such kit of parts, and methods of installing an aircraft seat unit.

Abstract: An assembly for an aircraft including a pylon having a lateral wall with a window passing through it, at least one reservoir, each reservoir being in the shape of an elongate ellipsoid with three semi-axes. The dimension of the reservoir along a first semi-axis differs from the dimension of the reservoir along at least one other semi-axis. The reservoir extends parallel to the semi-major axis, between a first end and a second end. The reservoir is equipped with a discharge head at the second end. The reservoir is equipped with a fastening arrangement disposed on the side of the second end and fastening the reservoir to the pylon. The reservoir is positioned through the window with the first end housed in the pylon and the second end outside the pylon.

Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a thermal energy storage reservoir positioned within the vapor chamber contains a phase change material for absorbing thermal energy.

Abstract: A nose structure of an aircraft includes an airframe. A wheel well assembly is coupled to the airframe and forms a portion of a nose landing gear bay. The wheel well assembly includes a pressure deck that extends from a right side of the airframe to a left side of the airframe and that forms a portion of a pressure boundary delimiting a pressurized space and a non-pressurized space. A floor-panel support is supported by the pressure deck in the pressurized space. The pressure deck and the floor-panel support form a portion of a flight deck floor of a flight deck of the aircraft. A plurality of transport elements is located between the floor-panel support and the pressure deck. The plurality of transport elements is associated with at least one high-level system of the aircraft.

Abstract: Disclosed is a wing in which, while a continuous surface is maintained, a chord length and camber of an airfoil may be modified via only a rotational drive alone, whereby a structure is simple and aerodynamic efficiency may be improved.

Abstract: A starboard wing of an aircraft includes various movable aerodynamic surfaces, such as a spoiler, slat, aileron, flap or the like. An actuator is provided for moving each such surface. The location and mounting of the actuator of the starboard wing is symmetrical about the centreline of the aircraft to that of the actuator of the port wing. The location of the piston, arm or other mechanical output of the actuator is at a centre portion of the actuator (i.e. at or near the midline of the actuator. The input port(s) for power is/are also at the centre portion. The actuator for the starboard wing may thus be substantially identical to the actuator for the port wing.

Abstract: Fuel systems, apparatus and associated methods for preventing or hindering unwanted fuel transfer between fuel tanks of aircraft are described. An exemplary apparatus comprises a conduit portion disposed inside a fuel tank for receiving fuel in the first fuel tank. The conduit portion includes an orifice through a wall of the conduit. The orifice permits venting an interior of the conduit portion to an interior of the fuel tank to prevent unwanted fuel transfer due to siphoning. A deflector is disposed and configured to deflect a stream of fuel discharged from the orifice during fuel transfer.

Abstract: Systems and methods for pivoting main landing gear of a cargo aircraft. One embodiment is a main landing gear of an aircraft that includes a shock strut coupled to a truck with one or more wheels, and a trunnion coupled to a bulkhead and configured to pivotally couple the shock strut with the bulkhead. The main landing gear also includes a folding brace extending from the shock strut in a forward direction toward a nose of the aircraft and configured to stabilize the shock strut. The main landing gear further includes a retraction actuator configured to pivot the shock strut about the trunnion to retract the one or more wheels in the forward direction toward the nose and up toward a fuselage of the aircraft.

Abstract: A system for controlling an electromechanical actuator of an aircraft includes a locking device configured to mechanically lock said actuator in a first fixed position and to mechanically unlock said actuator from said first fixed position and a controller configured to be in bi-directional communication with both said locking device and said actuator. The controller is configured to monitor a position of said actuator during flight and to detect when said actuator has not moved for a set amount of time, said controller further being configured to instruct said locking device to lock said actuator in said first, locked position when said set time has been reached. In addition, there is provided a method for controlling the thermal properties of an electromechanical actuator of an aircraft.

Abstract: A mobile machine includes a fuselage having at least one door, inside which is located a unit for processing measurements taken by at least one measurement device installed outside said fuselage. The system for communication between the processing unit and the measurement device includes a flex circuit that is affixed at least partially flat in the door corner between the door and the rim of the opening formed in the fuselage with which the door is associated and one of the ends, the internal end, of which is located inside the fuselage and the other, external, end of which is located outside. Since the flex circuit makes it possible to pass through the wall of the fuselage via the opening for doors, the need to make substantial modifications to the aircraft is avoided.

Abstract: Aspects of the disclosure relate to flight termination systems for tethered aerial vehicles. For instance, a flight termination system for a tethered aerial vehicle including an envelope may include a tool and a tether. The tool may include a first piece configured for attachment to an interior surface of the envelope and including a cutting blade. The tool may also include a second piece configured for attachment to an exterior surface of the envelope. The tether may be attached to the first piece such that when in use, a force on the tether causes the tool to cut an opening into the envelope.

Abstract: Systems and methods for wide set retracting landing gear of a cargo aircraft. One embodiment is an aircraft that includes a fuselage including a nose, and a pair of main landing gears comprising a pair of main posts disposed across the fuselage, each main post having a main wheel and configured to pivot forward toward the nose to retract the main wheel. The aircraft also includes a pair of nose landing gears comprising a pair of nose posts disposed across the fuselage, each nose post having a nose wheel and configured to pivot inboard to retract the nose wheel.

Abstract: Systems and methods for bipedal nose landing gear of an aircraft. One embodiment is a nose landing gear of an aircraft. The nose landing gear includes a shock strut coupled to an axle with a nose wheel, and a folding side brace extending from the shock strut inboard toward a belly of the aircraft and configured to stabilize the shock strut. The nose landing gear also includes a trunnion configured to pivot the shock strut forward toward a nose and inboard toward the belly of the aircraft to retract the nose wheel.

Abstract: A main landing gear assembly for an aircraft has an upper beam and a lower beam. The proximal ends of the upper and lower beams are each connected to a trunnion assembly that is mounted on the fuselage or wing of the aircraft. The distal ends of the upper and lower beams are each affixed to an axel support structure on which a main wheel of the landing gear assembly is mounted. In the gear assembly, the upper beam and the lower beam are coplanar and act together, in combination, to accommodate a planar flexure of the gear assembly during aircraft takeoffs and landings.

Abstract: Systems and methods for folding landing gear of a cargo aircraft. One embodiment is a main landing gear of an aircraft that includes a shock strut coupled to a truck with one or more wheels, and a yoke pivotally coupled with the shock strut via a lower trunnion, and pivotally coupled with an aircraft structure via an upper trunnion. The yoke is configured to pivot about the upper trunnion in a direction back toward a tail of the aircraft and up toward a fuselage of the aircraft, and the shock strut is configured to pivot about the lower trunnion in a direction forward toward a nose of the aircraft and up toward the fuselage of the aircraft to retract the one or more wheels.

Abstract: A vibration attenuator for a rotor of an aircraft has a track housing adapted for rotation relative to the rotor and configured for rotation at a second angular velocity greater than a first angular velocity of the rotor. A track is located within the track housing and has a reaction surface, a pair of weights being configured for movement within the track and in contact with the reaction surface. A stop assembly has a pair of stops spaced 180 degrees apart, the stops separating the weights from each other, and each weight being allowed to travel within the track between the stops. A motor rotates the track housing relative to the rotor. The weights are free to travel relative to each other between a minimum-force configuration, in which the weights are positioned 180 degrees apart, and a maximum-force configuration, in which both weights are adjacent one of the stops.

Abstract: Aircraft nacelles having adjustable chines are described. An example apparatus includes a multi-segment chine coupled to a nacelle. The multi-segment chine includes a first segment and a second segment. The first segment is oriented along a fore-aft direction. The first segment is rotatable relative to the nacelle about an axis of rotation. The axis of rotation is substantially perpendicular to a plane of the first segment defined by an outer mold line of the first segment. The second segment is fixedly coupled to the nacelle. The second segment is oriented along the fore-aft direction. The second segment is substantially coplanar with the first segment.

Abstract: Provided is a flight vehicle operating method including: mooring a flight vehicle to a mooring unit by a cable; reducing a weight of the flight vehicle, increasing the flotage of the flight vehicle, or increasing the flotage of the flight vehicle while reducing the weight of the flight vehicle, by using a first flotation adjuster; floating the flight vehicle at a suitable altitude in the air; increasing the weight of the flight vehicle, reducing the flotage of the flight vehicle, or reducing the flotage of the flight vehicle while increasing the weight of the flight vehicle, by using a second flotation adjuster or a propelling unit of the flight vehicle; and releasing the connection between the flight vehicle and the mooring unit and withdrawing the cable.

Abstract: Braking systems for aircraft are disclosed. An example braking system includes a brake pad movably coupled to a lower section of a fuselage of the aircraft. The brake pad is movable between a stowed position and a deployed position. An actuator is configured to deploy the brake pad from the fuselage during an emergency braking event. The brake pad to engage a surface of a runway and increase frictional force to reduce a speed of the aircraft during the emergency braking event.

Abstract: Aircraft nacelles having adjustable chines are described. An example apparatus includes a multi-segment chine having a first segment and a second segment. The first segment is fixedly coupled to a nacelle. The second segment is rotatable relative to the first segment about an axis of rotation. The axis of rotation is substantially perpendicular to a local area of an outer surface of the nacelle.