Abstract: An assembly of an attachment pylon with an aircraft engine comprising a front engine mount comprising a front tang and a front clevis, a lower tang and a lower clevis connecting the attachment pylon and the engine via a front pin mounted in the front tang and clevis and a lower pin mounted in the lower tang and clevis, and port/starboard links mounted between the attachment pylon and the engine via mounting pins, wherein the front and lower pins are orthogonal to a mid-plane, and wherein the mounting pins of the links are parallel to the mid-plane.

Abstract: Container receiving apparatus for a vehicle interior having a carrier structure mounted so as to be secured to a vehicle, and a container receiving frame displaceable in height relative to the carrier structure and bordering at least one container receiving member and guided for linear displacement by a linear guiding device in a vertical direction. The apparatus also includes a cover supported on the carrier structure for pivoting movement between a closed position to cover the container receiving frame and an open position to release the container receiving frame for a linear displacement in a vertical direction. For linear displacement of the container receiving frame in a vertical direction between a rest position and a functional position, a rotationally effective, mechanical forced control apparatus is provided.

Abstract: An aircraft panel is disclosed having a ply of composite material, the ply of composite material curved around an axis such that a free end of the ply extends more than 180 degrees around the axis and defines a wall of a channel for receiving a hinge member of an aircraft component.

Abstract: Provided in this disclosure is a fitting for engaging an L-track mounted to a surface and a connection component for connecting the fitting to an external component. The fitting includes a bottom portion including circular disks configured to be received within corresponding circular apertures formed in a surface of the L-track. The fitting is configured to slide along a longitudinal length of the L-track to enable the circular discs to be retained within a channel beneath opposing ledges formed in the surface of the L-track. A retractable lock mechanism is configured to retract along the fitting in a direction perpendicular to the longitudinal length, retracting between a locked position and an unlocked position. The retractable lock mechanism has circular engagement portions for engaging the circular apertures of the L-track when in the locked position, to thereby prevent the fitting from sliding along the longitudinal length.

Abstract: A selectively deployable ottoman includes a base member including an adjustment axis and an ottoman assembly connected to the base member. The ottoman assembly includes a first member having a first end and a second end. The first end being connected to the base member. A second member has a first end portion and a second end portion. The first end portion being pivotally connected to the second end of the first member. A third member includes a first end section and a second end section. The first end section is pivotally connected to the second end portion of the second member. A connector member operatively connects the first end of the first member to the base member. The connector member being shiftable along the adjustment axis of the base member to selectively deploy the ottoman assembly.

Abstract: An aircraft includes actuators coupled to a lift device. The aircraft also includes a lift device control interface disposed on a flight deck of the aircraft. The lift device control interface is configured to receive a pilot input. The aircraft further includes a flight control system configured to generate a command corresponding to a target lift device position. The flight control system is also configured to send the command to the lift device control interface to cause the lift device control interface to indicate the target lift device position. The flight control system is further configured to send a control signal to the actuators to set the lift device to the target lift device position.

Abstract: A pickup bed storage system for storing and organizing objects in a bed of a pickup truck includes a mat that is positionable on the bed and extends between a front end and a rear end of the bed. A pair of rails is coupled to the mat. A container movably coupled to the pair of rails is slidable between the front end and the rear end of the bed. The container has a front wall, a back wall, and a peripheral wall that is coupled to and extends between the front wall and the back wall to define an interior space. The peripheral wall is expandable to adjust a volume of the interior space. A pulley mechanism is coupled to the container and the pair of rails to slide the container along the pair of rails.

Abstract: A cavity system for use on a vehicle is provided. The cavity system comprises a cavity having at least one of a front edge and a rear edge arranged orthogonally to the actual or intended direction of travel of the vehicle, and longitudinal edges. The front and/or rear and longitudinal edges define an opening. The cavity system also comprises at least one shock stabiliser protruding from a surface adjacent each longitudinal edge of the cavity into the ambient flow outside of the cavity. An aircraft comprising the cavity system is also provided.

Abstract: An aircraft wing (3) comprising an aerofoil structure (5) is disclosed. The aerofoil structure (5) comprises a load-carrying member (10) having stiffness properties selected such that the load-carrying member (10) twists in a predefined manner in response to bending of the load-carrying member (10). The aerofoil structure (5) further comprises an actuator (15A, 15B) which is fixedly mounted to the load-carrying member (10) and which is operable to bend the load-carrying member (10) to thereby cause the load-carrying member (10) to twist. An aircraft comprising the aircraft wing and a method of adjusting the twist in an aircraft wing are also disclosed.

Abstract: A seat armrest is provided. The seat armrest includes a support unit, having a fixed seat and a support rod extending upward from the fixed seat; wherein the support rod has an accommodation space, and the support pole is provided with a positioning slot section composed of a vertical displacement slot and a plurality of horizontal displacement slots communicated with each other; a casing unit, sleeved around the support rod and having an installation groove communicated with the accommodation space; and an adjusting rod, having a positioning protrusion and being pivot disposed on the installation groove of the casing unit.

Abstract: A landing system for a fixed-wing unmanned aerial vehicle (UAV), the system comprising a parachute arranged in a parachute compartment that is secured to a fuselage tail section, and suspension lines for securing to the fuselage are fixed in four points on a fuselage lower part symmetrically relative to the UAV's center of gravity. The parachute compartment interacts with a detachment mechanism secured on a bulkhead of the tail section and comprises pins that are hinged to rods secured on a central rotatable disc coupled to at least one servomotor by means of a spring-loaded rod, the pins are mounted in guides, free ends of the pins fit into corresponding holes along a parachute compartment perimeter. The system further comprises an airbag coupled to an impeller and arranged in an onboard compartment that is arranged in a fuselage upper part and closed with a hinged hatch cover.

Abstract: A seat system for use in a crew escape system of a space transport vehicle comprises a seat having a backrest with a supporting surface. The seat is configured to be installed in a cabin area of the crew escape system so it can rotate about a first axis between a first position where the seat faces a first direction, and a second position where faces a second direction that is opposed to the first direction. The seat system further comprises a control unit configured to control a rotation of the seat at least between the first position and the second position in dependence on at least one signal which is indicative of a trajectory of the crew escape system.

Abstract: An adjustable armrest assembly for a seat such as a pilot seat. In embodiments, the armrest assembly includes an armrest frame, a leadscrew rotatably mounted in the armrest frame, a control wheel mounted to the leadscrew, an armpad subassembly pivotally attached to the armrest frame, and a tilt link subassembly coupled between the armrest frame and the armpad subassembly. In use, rotating the leadscrew synchronizes rotational motion of the armrest frame relative to the seat, and armpad subassembly motion relative to the armrest frame. In embodiments, the adjustment capability of the armrest assembly facilitates use with a flight controller positioned forward of the armrest.

Abstract: An aircraft comprising a fuselage and an unducted turbine engine. The fuselage having a divot with an upstream edge and a downstream edge. The divot is defined by a straight reference line having a length (L) and a maximum depth (h) relative to the straight reference line. The unducted turbine engine having an engine core, a nacelle, and a set of blades. A first flow ratio (FR1) is equal to: h L .

Abstract: An aircraft comprising a fuselage and an unducted turbine engine. The fuselage having a divot with an upstream edge and a downstream edge. The divot is defined by a straight reference line having a length (L) and a maximum depth (h) relative to the straight reference line. The unducted turbine engine having an engine core, a nacelle, and a set of blades. A first flow ratio (FR1) is equal to: h/L.

Abstract: The invention relates to an air intake lip of an aircraft engine nacelle extending along an axis X, in which an air flow circulates from upstream to downstream, the lip extending annularly about the X-axis and having an inner wall facing the X-axis and an outer wall which is opposite the inner wall, the inner wall and the outer wall being connected by an upstream wall and a partition so as to delimit an annular cavity, in which at least one infrared emission source is housed, wherein at least one wall, selected among the inner wall, the outer wall and the upstream wall, is made of a material configured to transmit on an outer face at least 30% of the infrared received on an inner face.

Abstract: An aircraft or aircraft body having an airframe structure, a pylon, a protrusion, and a nacelle. The airframe structure is a wing or a fuselage. The pylon has a first end, a second end opposite the first end, a first surface extending between the first end and the second end, and a second surface opposite the first surface. The first end is fixed to the airframe structure. The protrusion extends outward from the first surface and/or the second surface. The nacelle is located at the second end of the pylon and has a leading end, a trailing end, and a tapered boattail at the trailing end. The protrusion is located between the airframe structure and the tapered boattail. The protrusion is sized, shaped, and positioned between the boattail and the fuselage or wing to mitigate boundary layer separation.

Abstract: An aircraft wing apparatus includes a plurality of wing-skin sections, an extendable spar assembly, and a controller. The plurality of wing-skin sections includes a first wing-skin section and a second wing-skin section. The extendable spar assembly includes a first spar member coupled with the first wing-skin section and a second spar member coupled with the second wing-skin section. The controller is constructed and arranged to move the second spar member to predefined positions relative to the first spar member to place the plurality of wing-skin sections into predefined configurations. The predefined configurations including a stowed configuration, a first deployed configuration, and a second deployed position that is different from the first deployed position.

Abstract: An assembly comprising a wing and a reactor mast fixed to the wing. The primary structure of the reactor mast comprises a first fixing lug and starboard and port fixing lugs, the wing carries a first fitting and starboard and port fittings, the fixing lugs being joined to the fittings with shackles having three fixing points, and the first lug being fixed to the first fitting.

Abstract: Described herein is a method of constructing a landing pad using a rocket engine while in-flight. Among other benefits, this method can reduce ejecta that otherwise would occur during landing on an unimproved surface. While a spacecraft is hovering over an unimproved surface, the spacecraft can inject particles into its rocket engine, after which the particles absorb heat from the engine and are projected at ballistic speeds toward the unimproved surface to create a landing pad. After constructing the landing pad and waiting for the landing pad to cool, the spacecraft can land on the landing pad. Also described herein are landing pads created from such particles as they impact the surface in a disc splat mode into the unimproved surface.