Abstract: A partition including, but not limited to, a first body comprising a planar, foldable material. The partition further comprises a plurality of flat substrates resistant to folding. The partition further comprising an adhesive. The substrates are adhered to the first body by the adhesive and arranged in a repeating pattern that defines a plurality of columns and rows. Each column and each row is spaced apart from its neighbor, thus defining longitudinal gaps between the columns and lateral gaps between the rows. The first body folds laterally along the longitudinal gaps in an accordion-like manner and contemporaneously folds longitudinally along the lateral gaps in an accordion-like manner. The partition contracts both laterally and longitudinally when first body contemporaneously folds laterally and longitudinally. The partition extends both laterally and longitudinally when the first body contemporaneously unfolds laterally and longitudinally.

Abstract: Flight control systems, flight control laws, and aircraft are provided. An flight control system includes an input configured to receive a pitch rate command, a processor operative to receive the pitch angle command, to calculate a pitch angle saturation limit, to compare the sum of the pitch rate command, the scaled pitch rate, and the scaled pitch angle to the pitch angle saturation limit, to convert the pitch rate command system to the pitch angle command system in response to the sum exceeding the pitch angle saturation limit value to limit the pilot pitch-up pitch rate command, and to couple the pitch rate command to an aircraft control surface for the failure case of one of control surface, and the aircraft control surface configured to adjust an aircraft control surface setting in response to the pitch rate command and/or pitch angle command to protect an aircraft from being in stall condition.

Abstract: A nozzle assembly includes a sleeve defining a pathway, the sleeve disposed within a nacelle. The pathway and an internal surface of the nacelle guides a mass flow from an engine to an exit of the propulsion system. The sleeve is configured to move between a forward position an aft position within the nacelle aft of the engine. The sleeve has a protruding portion that extends towards a center of the pathway and that defines a smallest internal diameter of the sleeve. The sleeve includes a plurality of sleeve segments that are longitudinally aligned and circumferentially arranged to form the sleeve. The sleeve segments are configured to move circumferentially closer as the sleeve moves in a first direction within the nacelle and to move circumferentially further apart as the sleeve moves in a second direction within the nacelle. An actuator is coupled with, and is configured to move the sleeve.

Abstract: An aircraft has a first principles takeoff processor (PCE), a predictive flight envelope protection processor (PFEP), and a maximum takeoff weight processor. The PCE is programmed to predict a liftoff location and an energy state of the aircraft at a liftoff on a runway. The PFEP is programmed to assess each of a plurality of potential trajectories for compliance with or violation of a predetermined flight envelope. The maximum weight processor is programmed to: indicate that the aircraft may takeoff at the aircraft weight when any one of the plurality of potential trajectories is in compliance with the predetermined flight envelope; iteratively reduce an input of the aircraft weight to the PCE until the PCE indicates that any one of the plurality of potential trajectories is in compliance with the predetermined flight envelope; and indicate that the input of the aircraft weight as reduced is a maximum allowable takeoff weight.

Abstract: A table extension assembly is disclosed herein. The table extension assembly is for use with a table assembly having a first table section having a first upper surface and a cavity situated below the upper surface, the cavity having an internal surface, and an opening to the cavity disposed proximate a first side surface of the first table section. The table extension assembly includes a second table section having a second upper surface. The table extension assembly further includes an engagement feature extending from a side surface of the second table section. The engagement feature is configured to fit within the cavity, to engage the internal surface and to support the second table section adjacent the first table section such that the second upper surface is flush and contiguous with the first upper surface when the engagement feature is disposed within the cavity and engaged with the internal surface.

Abstract: A reclining seat including, but not limited to, a seat bottom; a seat back, a leg support, and an arm support forming a seat assembly. The seat assembly is configured to be supported on a floor surface and to move between an upright configuration and a flat configuration. The seat back and the leg support are transverse to the seat bottom, and the arm support is transverse to the seat back, when the seat assembly is in the upright configuration. The seat back, the seat bottom, the leg support and the arm support are each longitudinally aligned with one another when the seat assembly is in the flat configuration. An upper surface of the seat back, the seat bottom, and the leg support are each coplanar with one another and substantially coplanar with the arm support when the seat assembly is in the flat configuration.

Abstract: The present application relates to providing mechanical and environmental protection to an electronics rack including a frame configured in a vertical orientation configured to receive an electronics rack, a front cover and a back cover, wherein the front cover and the back cover are configured to enclose the electronics rack when the front cover is attached to the frame and when the back cover is attached to the frame, a first fastener for mechanically coupling a top portion of the electronics rack to a top portion of the frame, a second fastener for coupling a bottom portion of the electronics rack to a bottom portion of the frame and a horizontal base for supporting the frame, the base including a mechanical interface for a material handling device, at least one castor and at least one floor lock.

Abstract: A reclining seat including, but not limited to, a seat bottom. The reclining seat further including, but not limited to, a seat back having an upper segment and a lower segment, the lower segment pivotally coupled with the seat bottom via a first pivotal coupling, and the upper segment pivotally coupled with the lower segment via a second pivotal coupling.

Abstract: A system onboard a vehicle, an aircraft, and a method of controlling actuation of a moveable control surface of a vehicle are disclosed here. An operating method involves: obtaining a force measurement and a deflection measurement responsive to manipulation of an inceptor for the moveable control surface; determining an issue associated with the inceptor, based on the obtained force and deflection measurements and vehicle data that characterizes expected operating behavior of the vehicle under current operating conditions; and, in response to the determining, activating a temporary backup control mode for the moveable control surface. While the temporary mode is active, control surface actuation signals are generated with an onboard system that disregards deflection measurements and processes force measurements of the inceptor. While the temporary mode is active, generated control surface actuation signals are communicated to an actuation system that is coupled to the moveable control surface of the vehicle.

Abstract: The present application relates to providing an aircraft storage container including a lower portion having a horizontal bottom and a plurality of vertical sides configured to form a storage volume, an upper portion rotationally coupled to one of the plurality of vertical sides, a gas piston having a locking mechanism wherein the gas piston is coupled between the lower portion and the upper portion, the gas piston being configured to support the upper portion when the locking mechanism is engaged, a rotational member operative to disengage the locking mechanism when rotated and to engage the locking mechanism when released, and a latch mechanism having a rotational lever, wherein the latch mechanism is operative to rotate the rotational member in response to a pressure on the rotational lever.

Abstract: A roller for a control surface of an aircraft includes a roller shaft, a primary roller coupled to the shaft, and a roller assembly coupled to the shaft. The shaft includes a longitudinal axis, a mounting end that couples with a roller fitting of the control surface, and a roller end. The primary roller can rotate about the longitudinal axis, and can engage and roll along a first surface of a track. The roller assembly includes a secondary roller having a longitudinal roller axis and configured to engage and roll along a second surface of the track. The roller assembly also includes a housing that retains the secondary roller while allowing the secondary roller to rotate about the longitudinal roller axis. The housing is movably coupled to the roller end of the roller shaft with three degrees of rotational freedom relative to the roller end of the roller shaft.

Abstract: A display system is provided for a vehicle having a windshield and vehicle structure outside the windshield. The vehicle structure is visible within a field of view defined by the windshield. Certain embodiments of the display system include: a camera to capture image data for a visually obstructed portion of an environment outside the vehicle, wherein the visually obstructed portion of the environment is hidden by the vehicle structure; a controller configured to process the image data captured by the camera into a head-up display (HUD) image that represents the visually obstructed portion of the environment; a HUD element configured to present projected images that are visible to an occupant of the vehicle; and a projector coupled to the controller and configured to project the HUD image toward the HUD element, such that the HUD image is visible overlying the vehicle structure.

Abstract: An aircraft includes a fuselage, a main entry door with an associated passenger loading zone, an auxiliary power unit (APU) in the fuselage, and an APU inlet assembly. The APU inlet assembly has an inlet duct, and inlet door, and means for redirecting sound waves coupled to or integrated with an interior side of the inlet door. The inlet duct has a first end coupled to the APU, and a second end associated with the inlet door. The inlet door moves between a closed position and an open position. The means for redirecting sound waves is positioned at a particular location on the interior side of the inlet door, and includes certain acoustic features and characteristics. The particular location and the acoustic features and characteristics cooperate to redirect sound waves generated by the APU away from the passenger loading zone when the inlet door is in the open position.

Abstract: An exhaust nozzle assembly includes, but is not limited to, a nozzle body configured to be fluidly coupled with an engine and to receive a jet produced by the engine. An outer cover covers the nozzle body. A movable component is disposed and configured to have an effect on either the jet or an exhaust plume when the movable component moves. A linkage is coupled to the movable component and adapted for coupling to an actuator. The linkage transmits the force to the moveable component from the actuator. There is a gap between an inner surface of the outer cover and an outer surface of the nozzle body. The linkage is smaller than the actuator. The gap is smaller than a smallest dimension of the actuator and larger than the linkage. The linkage is partially disposed within the gap, and the exhaust nozzle assembly is free of the actuator.

Abstract: The aircraft threat envelope protection system employs a threat envelope data structure in a computer-readable medium that stores at least one trigger condition for each of a plurality of different types of threats associated with the aircraft, and modeled using a common schema. A processor computes plural different projected trajectories representing different possible aircraft paths through spacetime. The processor associates at least some of the plurality of the threats to specific trigger points in spacetime along each of the projected trajectories. The processor will deprecate ones of the projected trajectories when they are deemed not viable to recover from a threat. The processor initiates an aircraft protective response when all projected trajectories but one have been deprecated and the aircraft is within a predetermined proximity to the closest trigger point in spacetime along the non-deprecated trajectory.

Abstract: An input device for providing user input to a computing device includes a seat portion allowing a user to sit on the device. The input device further includes several human interface devices having positional sensors that detect changes in rotation or translation of a movable tactile surface with respect to a fixed tactile surface and provide a signal indicative thereof. These signals are used are used by a computer to change an image of virtual fixed and movable surfaces within a head mounted display.

Abstract: A reclining seat including, but not limited to, a seat bottom; a seat back, a leg support, and an arm support forming a seat assembly. The seat assembly is configured to be supported on a floor surface and to move between an upright configuration and a flat configuration. The seat back and the leg support are transverse to the seat bottom, and the arm support is transverse to the seat back, when the seat assembly is in the upright configuration. The seat back, the seat bottom, the leg support and the arm support are each longitudinally aligned with one another when the seat assembly is in the flat configuration. An upper surface of the seat back, the seat bottom, and the leg support are each coplanar with one another and substantially coplanar with the arm support when the seat assembly is in the flat configuration.

Abstract: A throttle quadrant system for an aircraft includes: a first throttle handle to control a first engine of the aircraft, the first throttle handle having a first activatable visual indicator integrated therein; a second throttle handle to control a second engine of the aircraft, the second throttle handle comprising a second activatable visual indicator integrated therein; and at least one controller to control activation and operation of the first activatable visual indicator and the second activatable visual indicator. The at least one controller responds to first engine data related to operating status of the first engine to selectively activate the first activatable visual indicator. The at least one controller also responds to second engine data related to operating status of the second engine to selectively activate the second activatable visual indicator.

Abstract: A method of checking accuracy of an air data probe system onboard a vehicle is disclosed. An embodiment of the method involves: calculating airspeed measurements from air data provided by the probe system; calculating vehicle speed measurements based on sensor data collected from at least one sensor system onboard the vehicle, wherein the vehicle speed measurements are distinct and independent of the airspeed measurements, and the vehicle speed measurements are calculated without using the air data; comparing a calculated airspeed measurement against a calculated vehicle speed measurement to obtain a speed difference, wherein the calculated airspeed measurement and the calculated vehicle speed measurement correspond to a measurement time during which the vehicle is moving forward; and initiating at least one corrective action onboard the vehicle when magnitude of the speed difference exceeds a threshold value.