Abstract: An assembly with a continuous structural element for aircraft and a fitting. The continuous structural element has an outer flange, an inner flange and a web between the flanges. The inner flange has at least one portion with a wavy shape such that the height of the web increases or decreases in that portion. The fitting has at least one through hole and is configured to fit the web at the portion of the inner flange with a wavy shape so that in an assembled state the fitting is joined to the web in such a way that the at least one through hole of the fitting is not covered by the web.

Abstract: A wind harness for a vehicle includes a low profile duct intake that extends along a roof and sides of a vehicle. At least one duct extends from the duct intake on each side of the vehicle. The ducts are positioned in the rear pillars directing air and through along the pillars. A wind turbine is positioned inside a body panel of the vehicle. The ducts have an exhaust nozzle directed at the turbine for delivering an air flow to rotate the turbine.

Abstract: A screen system for use in a window of a vehicle. The screen system includes a screen, a spool mounted to a leading edge of the screen, a housing configured to be mounted at a first edge of the window, and one or more bands that are operatively connected to the screen and configured to apply a biasing force to the screen. The screen is movable between a retracted position and an extended position. The retracted position includes the screen rolled onto the spool and with the screen and the spool positioned in the housing at the first edge of the window. The extended position includes the screen extending across the window.

Abstract: A wing assembly has a flexible cover which is movable between an extended position and a retracted position. In the extended position the flexible cover covers the leading edge of the wing assembly, thereby protecting the front of the wing assembly from impact by dirt or debris and preserving the smoothness of its surface. In the retracted position the flexible cover does not cover the leading edge of the wing assembly.

Abstract: A rotorcraft with a fuselage and a tail boom, comprising: a horizontal stabilizer mounted to the tail boom; rotor blades with rotor blade tips which form a virtual blade tip circle upon rotation around a rotor head; luminescent components provided on the rotor blade tips; and a blade tip illumination device comprising at least one light source integrated into the horizontal stabilizer and configured to emit a light beam toward the virtual blade tip circle for excitation of the luminescent components; wherein the luminescent components emit light in response to excitation via the emitted light beam, and wherein the emitted light forms during rotation of the rotor blade tips around the rotor head on the virtual blade tip circle a luminous ring.

Abstract: An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A source of electric power is disposed within or attached to the closed wing, fuselage or one or more spokes. A plurality of electric motors are disposed within or attached to the one or more spokes in a distributed configuration. Each electric motor is connected to the source of electric power. A propeller is operably connected to each of the electric motors and proximate to a leading edge of the one or more spokes. One or more processors are communicably coupled to the plurality of electric motors. A longitudinal axis of the fuselage is substantially vertical in the vertical takeoff and landing and the stationary flight, and substantially in a direction of flight in the forward flight.

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: A jet engine exhaust assembly 20 is disclosed. The exhaust assembly comprises a double-walled exhaust duct 22 comprising an inner wall defining the inner profile of the duct and an outer wall spaced apart from the outer surface of said inner wall to define a cooling space 21 therebetween. The double-walled exhaust duct 20 is a structural load bearing component.

Abstract: The invention relates to an assembly (10) for a bumper device of a motor vehicle, comprising at least one bumper beam (12) and two absorbers (14); the bumper beam (12) is formed by an elongate hollow body comprising two ends at which the absorbers (14) are attached; the assembly (10) further comprises two modular extension pieces (18); each modular extension piece comprising a body (20) with a first portion attached to one end of the bumper beam (12), and a second portion projecting from the end in a longitudinal direction of the bumper beam (12). A lateral absorption plate (24) is further arranged at the end of the second body part (20) of each modular extension piece (18) and extends laterally to the absorbers (14), preferably parallel to the absorbers.

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: A head restraint unit is configured to restrain the movement of a head of a user, and to be fixed to or to be integral with a vehicle seat. The head restraint unit includes a headrest member and two side portions extending therefrom. A restraining member is pivotally coupled to the two side portions to allow rotation between a maximal upward position and a maximal downward position. The head of the user is intended to be positioned within the confined space that is formed within the loop defined by the back portion, side portions and the head restraining member. In result to an extreme maneuver of the vehicle, the head of the user can maneuver in a non-safely manner that can damage his/her head or spine. The head restraining member is configured to restrain this extreme movement and to reduce of its risk.

Abstract: Disclosed is a product that may include a vehicle seatback having a back face and an opposite front face and a first side face extending between the back face and a front face, the seatback having a frame, and a lock component connected to the frame, the lock component moveable from a first position wherein the first end of the lock component is a first distance from the first side face to a second position wherein a first end of the lock component is a second distance from the first side face, and wherein the second distance is shorter than the first distance.

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: In many embodiments of the invention, a space-based data center includes orbital server modules configured to be deployed in space, each module including a communication subsystem for module-to-module communications to form a data center, tiles arranged in a planar array, where each tile has a layered structure including solar cells forming a layer across a first surface, thermal radiator panels forming a layer across a second surface, electronic components distributed laterally in a layer between the layer of solar cells and the layer of thermal radiator panels, where each electronic component receives power locally from solar cells and rejects heat to the thermal radiator panel beneath it, where a first subset of tiles are compute tiles in which the electronic components include one or more computing processors and memory, and where a second subset of tiles are support tiles in which the electronics components include network switches and energy storage.

Abstract: Systems and other embodiments described herein relate bull-bar assemblies with an easy access latch. In one embodiment, a bull-bar assembly for a vehicle includes a panel defining a component aperture through which a vehicle component is accessible. The panel further defines a latch aperture. The bull-bar assembly also includes a cover attached to the panel and movable between a closed position, in which the cover blocks the component aperture, and an open position, in which the cover unblocks the component aperture. The bull-bar assembly further includes a latch accessible through the latch aperture and movable between an actuated position, in which the latch disengages the cover to unblock the component aperture, and an unactuated position, in which the latch engages the cover to block the component aperture.

Abstract: An aircraft comprises a fuselage, first and second wing segments each having a leading edge and a trailing edge, a plurality of spokes coupling the fuselage to the first and second wing segments, one or more motors disposed within or attached to the plurality of spokes, and three or more propellers proximate to a leading edge of the plurality of spokes, distributed along the plurality of spokes, and operably connected to the motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight. When the aircraft is in vertical takeoff and landing and stationary flight, the fuselage is approximately vertical. When the aircraft is in forward flight, the fuselage is approximately in the direction of the forward flight and extends forward beyond the leading edges of the first wing segment and the second wing segment.

Abstract: The present invention is a powered electric lift augmentation systems (ELAS's) to add drag while minimally reducing or enhancing the lift augmentation of an airplane. At least one ELAS is attached to an airfoil, and each ELAS comprises: a nacelle; and electric duct fan (EDF) housed within the nacelle; an optional pylon perpendicularly connected beneath the nacelle; an optional slat; and one or more drag elements, pivotably connected through a range of angles to airflow. Each drag element comprises a hinged plate, or a pair of opposing plates, connected to a pilot's control element able to rotate the plates to create a range of drag levels or to stow away. The drag elements are connected to the airfoil leading edge, the nacelle, pylon, or slat; and may further comprises holes. As ELAS assembly may comprise one or more ELAS systems attached to an airfoil (aerodynamic lifting element—ALE).

Abstract: A vehicle-body frame structure including a floor tunnel includes a cross member floor front and a transmission cross member. The cross member floor front is disposed at a vehicle front end of the floor tunnel and has a vehicle-widthwise cross-sectional shape that includes a first slant, a second slant and a third slant. The first slant extends from the vehicle bottom part toward an inward-and-upward side in a vehicle width direction of the vehicle. The second slant extends from a vehicle upper part of the first slant toward an outward-and-upward side in the vehicle width direction. The cross member floor front is formed by joining to each other members divided in a vehicle up-down direction of the vehicle on a vehicle upper side of the second slant. The transmission cross member is fixed to the cross member floor front on a vehicle upper side of the first slant.

Abstract: The present invention relates to a vertical take-off and landing module (200) for a fixed-wing aircraft (110), which includes at least one vertically-acting propulsion unit (240), actuator means (245) and support means (230), so as to be adapted to be operatively connected to said aircraft (110). The actuator means (245) can move the propulsion unit (240) from the inside of the module (200) towards the outside, and vice versa, so that the propulsion unit (240) is adapted to generate a substantially vertical propulsive force during the aircraft take-off and landing phases.