Abstract: An aircraft wing includes a center wing section having a continuous structure that spans beyond a first side of an aircraft fuselage and beyond a second side of the aircraft fuselage. The aircraft wing also includes a first outboard wing section attached to a first end of the center wing section by a first truss system that is accessible via a first closeout panel. The first end of the center wing section in on the first side of the aircraft fuselage. The aircraft wing also includes a second outboard wing section attached to a second end of the center wing section by a second truss system that is accessible via a second closeout panel. The second end of the center wing section is on the second side of the aircraft fuselage.

Abstract: A deployable attendant seat assembly that is configured to deploy in a vehicle cabin from a stowed position as an attendant seat into a deployed position configuring the deployable attendant seat assembly into a lockable barrier to prevent passengers from moving along an aisle in a vehicle cabin into a vehicle area forward of the lockable barrier.

Abstract: A device for deployment and actuation of a control surface for a maneuverable object, including an actuation shaft arranged for rotation about a longitudinal axis of the device; an output gear arranged concentric with the actuation shaft and configured to unlock the control surface when rotated about the longitudinal axis; and a pin integral with, or attached to, the actuation shaft and protruding through an opening in the output gear, wherein the output gear is operable to rotate about the longitudinal axis independent of the actuation shaft when the pin is in a circumferentially extending portion of the opening, and the output gear and actuation shaft are operable to rotate together about the longitudinal axis when the pin is in a longitudinally extending portion of the opening.

Abstract: A parachute assembly may comprise a canopy and one or more reefing lines. The one or more reefing lines may limit inflation of the canopy to attenuate impulse load or otherwise mitigate forces exerted by the parachute assembly on cargo or an occupant during deployment of the canopy. The one or more reefing lines may be broken in stages to selectively limit inflation of the canopy followed by selectively permitting inflation of the canopy in stages.

Abstract: A system and a method for securing a portion of a fuselage of an aircraft to a portion of a wing of the aircraft include a longeron having a first end and a second end, a first moveable coupling interface that moveably secures the first end to the portion of the fuselage, and a second moveable coupling interface that moveably secures the second end to the portion of the wing.

Abstract: A system for controlling a tension of a tether between an object and a load tethered to the object comprises magnetorheological (MR) fluid actuator unit(s) including at least one torque source and at least one MR fluid clutch apparatus coupled to the at least one torque source to receive torque from the at least one torque source, the MR fluid clutch apparatus controllable to transmit a variable amount of torque via an output of the MR fluid actuator unit. A tensioning member is connected to the output so as to be pulled by the output member upon actuation of the magnetorheological fluid clutch apparatus, a free end of the tensioning member adapted to exert a pulling action when being pulled by the output member. Sensor(s) provide information indicative of a relation between the object and the load tethered to the object. A controller controls the at least one MR fluid clutch apparatus in exerting the pulling action based on said information.

Abstract: A detachable device for closing a space inside an airplane includes: a frame comprising at least one upright, the frame comprising at least one attachment interface with a structural element, a curtain assembly comprising a flexible curtain, a roller around which the flexible curtain can be wound, and at least one guide device comprising an electric-motor actuator, the guide device-being capable of translationally guiding the flexible curtain relative to the upright such that the flexible curtain can be moved in a direction of movement parallel to a longitudinal direction of the upright between a stowed position in which the flexible curtain is mainly wound around the roller and an extended position in which the flexible curtain is mainly unwound relative to the roller.

Abstract: The present disclosure relates to a leaf spring type landing gear mounted on a lower portion of a fuselage of an aircraft, and more particularly, to a leaf spring type landing gear having improved performance for mitigation and absorption of shocks, including: a first frame connected to the fuselage and bent to have a circle center below; a second frame connected to the first frame; and a third frame connected to the second frame and at least partially bent to have a circle center below, wherein the second frame includes a 2-1st frame and a 2-2nd frame having circle centers formed in opposite directions and is formed to be bent in an S shape.

Abstract: A vehicle includes a body, at least one propulsion system including an electric component, a strut extending between the body and the at least one propulsion system, and a cooling system operably coupled to the electric component of the at least one propulsion system. A portion of the cooling system is arranged within the strut.

Abstract: Double-curved aircraft door having a pair of stops in contact over a contact area. The isobarycentre (31A) of each contact area of a first lateral edge is substantially arranged in a first plane perpendicular to the longitudinal axis (21) and the same applies to a second lateral edge. For each contact area, the normal to the contact area passing through its isobarycentre (31A, 31B) substantially passes through the axis (41) of a medium cylinder (42). For each contact area, the normal to the contact area passing through its isobarycentre (31A, 31B) forms a deflection angle with a plane perpendicular to the longitudinal axis (21), the deflection angles of all the contact areas being equal.

Abstract: A pet collar. A plurality of connecting rods is pivotally connected via a ball-and-socket connection to a plurality of socket segments. A center section is pivotally connected via a ball-and-socket connection to two innermost socket segments. A collar connector is pivotally connected via a ball-and-socket connection to two outermost socket segments. In a preferred embodiment the collar connector includes a slidable magnet for locking the collar connector. Also, in a preferred embodiment the center section includes a NFT tag for pet safety and identification.

Abstract: Presented is a small, unmanned aircraft systems (aka drone) configured for amphibious use in water environments. Also presented is a capture device for the capture and recovery of a small, unmanned aircraft system.

Abstract: An aircraft lavatory is disclosed herein. The aircraft lavatory includes a standard access door providing access to the aircraft lavatory from at least one of an aisle, a cross aisle, or a passageway of an aircraft, a first moveable wall adjacent the standard access door, the first moveable wall having a first end and a second end and configured to move between a closed position and an open position, the first end of the first moveable wall configured to rotate about a first pivot point, and a second moveable wall adjacent the first moveable wall, the second movable wall having a first end and a second end and configured to move between a closed position and an open position, the first end of the second moveable wall configured to rotate about a second pivot point.

Abstract: An aircraft thruster includes at least a first propeller provided with a plurality of radial blades extending about an axis of rotation of the said first propeller, which is driven in rotation by a first electric motor. An electrical supply of the first electric motor includes power circuits carried by a fairing of the thruster characterized in that the power circuits are arranged in an annular manner in an annular part integral with the fairing of the thruster, this annular part being arranged around the said first propeller.

Abstract: A primary structural assembly for an aircraft outside-skin heat exchanger, the assembly comprising an outer-skin portion which defines an outer shape of the aircraft and forms a portion of a hull of the aircraft, wherein the outer-skin portion comprises at least one recess, a thermal-transfer fluid connection which is designed to convey a thermal-transfer fluid into the recess, a component which closes the recess, and at least one retaining element which is arranged in or on the recess and is configured to hold the component closing the recess, in the recess. Further, an aircraft including such a primary structural assembly and a method for attaching the aircraft outside-skin heat exchanger are disclosed.

Abstract: A payload retrieval apparatus including a support structure having an upper end and a lower end; a first sloped surface secured to the support structure and a second sloped surface positioned adjacent the first sloped surface; an opening between the first and second sloped surfaces leading to a space to allow a payload retriever attached to a tether suspended from a UAV to travel into the space; an angled channel positioned beneath the first sloped surface having a tether slot to allow for passage of the tether as the payload retriever is drawn through the angled channel; and a payload holder positioned at the end of the angled channel.

Abstract: An aircraft cabin section with an aircraft door, a cabin floor, and at least one lining mounted to the aircraft door. The aircraft cabin section further comprises at least one seal that is mounted to the at least one lining and seals a space between the at least one lining and the cabin floor. This prevents a cold air draft from entering the aircraft cabin.

Abstract: A rotating pylon assembly for aircraft thrust vectoring control. In embodiments, the rotating pylon assembly of embodiments includes a rotating sleeve disposed within a fixed boom of the aircraft, and configured to support a rotor assembly. The rotating pylon assembly includes a bearing assembly configured to functionally couple the rotating sleeve against an inner surface of the fixed boom. The bearing assembly enables the rotating sleeve to rotate against the inner surface of the fixed boom and about a longitudinal axis of the fixed boom. An actuator is configured to rotate the rotating sleeve about the longitudinal axis of the fixed boom. The rotating sleeve may cause the rotor assembly to be rotated or swung about the longitudinal axis of the fixed boom to position the rotor assembly in a position to vector the thrust provided by the rotor assembly based on a control command.

Abstract: An aerial vehicle including a main body having a leading edge. An inlet is recessed aft from the leading edge. Forward protrusions extend from the main body on opposite sides of the inlet. An outlet nozzle is proximate to an aft end. The inlet is in fluid communication with the outlet nozzle. Wings extend from the main body.

Abstract: A morphing aerodynamic structure includes a body with an outer covering, a bridle attached to the body, and a light-response polymer disposed on at least one of the outer covering and the bridle. The light-responsive polymer is configured to change shape when illuminated with a laser such that at least one of an angle of attack, roll, pitch and yaw of the morphing aerodynamic structure is at least partially controlled without the use of a mechanical or pneumatic control unit.