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.

Abstract: A safety device capable of rapidly inflating a float, having sufficient buoyancy at the time of landing on water, and being lighter than a conventional safety device, and a flight vehicle including the safety device. A safety device includes a parachute, a bottomed cylindrical container that accommodates the parachute, and an ejection device that is provided in the container and ejects the parachute to the outside of the container. The parachute includes an umbrella body, a plurality of lines, a center cord, and a bag-shaped member. The bag-shaped member including an intake port connected to a ventilation port is provided outside a top portion of the umbrella body. The intake port of the bag-shaped member is provided with a check valve including a hinge portion and a plate member.

Abstract: An auxiliary storage box is detachable and storable in a storage box provided in a vehicle interior. The auxiliary storage box includes: an auxiliary box body; and an auxiliary box attachment. The auxiliary box body is storable inside the storage box. The auxiliary box attachment is detachably attached to the auxiliary box body and capable of supporting an auxiliary item used in combination with the auxiliary box body outside the auxiliary box body.

Abstract: An aircraft structure having a fuselage, an engine and an air inlet for receiving air for the engine. The air inlet has a cowl which surrounds an inlet opening. The air inlet has a compression surface and a transition shoulder. The air inlet additionally has a flow guide surface, which is arranged as a local elevation in a region of the transition shoulder and extends into the inlet opening. This flow guide surface designed as a local elevation contributes to improving the displacement of the boundary layer of a fluid flowing along the aircraft structure at the air inlet.

Abstract: Retrofittable satellite systems for an in-orbit host satellite comprising an enhancement module for adding a capability to the in-orbit host satellite, modifying the function of the in-orbit host satellite, and/or extending the function of the in-orbit host satellite. The in-orbit, retrofittable satellite system comprises a transfer vehicle for transferring the enhancement module from a first to a second location and a service vehicle for receiving the enhancement module from the transfer vehicle and installing the enhancement module on the in-orbit host satellite.

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: Hybrid propulsion systems that utilize liquid natural gas solid oxide fuel cells in a manner practical for use in aircraft that avoid the use of heavy batteries, provide transient response times suitable for use in aircraft, and/or simplify reactant pre-conditioning systems using a compressor and turbine pair operatively coupled to the solid oxide fuel cell. Such hybrid propulsion systems for an aircraft may include a liquid natural gas solid oxide fuel cell, a motor driven by electric power from the solid oxide fuel cell, a gearbox operatively coupled to the motor, and a turbofan engine configured to generate thrust for the aircraft. The turbofan engine may be configured to provide electric power and shaft power and may include a duct fan that is operatively coupled to the motor via the gearbox, with the duct fan being driven by mechanical power from the gearbox and by the motor.

Abstract: An aircraft, including a wing having an exterior with an exterior surface, a first power supply structure disposed in the wing, an electric motor electrically connected to the first power supply structure, a first heat exchanger disposed in the wing, where the first heat exchanger is disposed adjacent to, and in thermal contact with, at least a portion of the exterior of the wing, where the first heat exchanger is configured to transfer heat to the exterior surface, and a first coolant pump in fluid communication with the first heat exchanger and the first power supply structure.

Abstract: A vehicle front structure includes: an upper beam to which a headlight is fixed; a bracket installed side by side with the upper beam and formed to extend outward in a vehicle width direction from one end thereof fixed to a bulkhead of a vehicle, curve rearward at a point halfway to an outer end in the vehicle width direction of the vehicle, and extend rearward to the other end thereof fixed to a lower member of the vehicle; and an airbag sensor provided on the bracket.

Abstract: A seat mounting system having a seat rail and a seat fitting, wherein the seat rail has an upper flange with a plurality of heads thereon. The seat fitting comprises a main body having a void configured to receive the upper flange and at least some of the plurality of heads.

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: Provided is a neck supporting device including a housing capable of being attached to or detached from a seat, a main body capable of being withdrawn from the inside of the housing, the main body including two support portions disposed at two opposite sides of one surface of the main body, respectively, and configured to protrude toward a neck of an occupant, and a strap coupled to the two opposite support portions of the main body while having tension and having a neck support portion positioned between the two opposite support portions and configured to support the neck of the occupant.

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.