Abstract: Provided is a seat system which can change a surrounding environment of a user including illumination according to the movement of the user's body. A seat system comprises a seat body on which a user can be seated; a plurality of sensors provided on or in the seat body or on a structure arranged around the seat body and configured to detect a touch operation by the user seated on the seat body; an output device configured to output at least one of sound, light, and vibration; and a control device configured to control the output device such that, when one or more of the sensors detect a touch operation, the control device causes the output device to generate a corresponding predetermined output.

Abstract: A T-divider includes a housing defining a proximal end, a distal end, and at least one cavity extending therebetween. The housing extends along a longitudinal axis. The T-divider includes a moveable portion disposed in the housing and extending between the proximal end and the distal end. The movable portion is configured to rotate about the longitudinal axis from a stowed orientation to a removal orientation.

Abstract: A sensor lift mechanism for deploying a sensor from a tail cone of an aircraft includes a frame mounted onto a side wall of the tail cone via a mounting assembly. The frame includes a first roller track and a second roller track aligned with the first roller track. A roller carriage assembly includes a plurality of rollers configured for rolling along the first and second roller tracks. A sensor platform is mechanically coupled to the carriage assembly and configured for mounting the sensor thereto. A drive unit is operatively coupled to the frame. The drive unit translates the roller carriage assembly vertically between the first and second roller tracks to move the sensor platform between a stowed position and a deployed position. A floor of the tail cone includes a track door configured to open for deploying the sensor beneath the tail cone.

Abstract: A cladding element having a heating layer in a sandwich construction. In the case of a cladding element in a sandwich construction for an interior space of an aircraft, the cladding element includes a core layer and a first cover layer. The first cover layer forms a visible side of the cladding element. An electrically heating layer extends at least across a sub-face of the first cover layer and serves for generating heat for emission through the first cover layer is disposed between the core layer and the first cover layer.

Abstract: To provide a seat system that allows the information of the user seated in the seat to be acquired by another user, a seat system includes: a seat main body; at least one sensor provided in the seat main body; a control device for processing a signal from the sensor; and a first user interface communicating with the control device and notifying information based on a signal from the control device. Preferably, the sensor acquires information obtained from a seated person who is seated on the seat main body. Preferably, the seat system includes a camera for capturing an image of the seated person who is seated on the seat main body, and the control device causes the first user interface to display the image captured by the camera.

Abstract: A sanitizing system includes a plurality of ultraviolet (UV) lamps mounted at various locations within an internal cabin of a vehicle. The UV lamps are configured to receive electrical power from a power source onboard the vehicle and to emit UV light into the internal cabin on a continuous basis during a trip of the vehicle. The UV lamps are positioned such that the emitted UV light disinfects air within the internal cabin.

Abstract: A vehicle control device includes a sleep depth estimation unit that estimates a sleep depth of an occupant seated in a seat provided in a vehicle, and a control unit that controls the vehicle such that a magnitude of the external force to be applied to at least one of a plurality of the occupants is equal to or less than a first threshold value when the estimated sleep depth of the occupant is equal to or lower than a predetermined reference depth or when the occupant is awake, and that controls the vehicle such that the magnitude of the external force to be applied to each of all the occupants is equal to or less than a second threshold value larger than the first threshold value when the sleep depth of each of the occupants is greater than the reference depth.

Abstract: A drain assembly includes a drain tube and a flapper assembly. The drain tube extends between a first tube end and a second tube end. The first tube end is configured to fluidly attach to an inlet plenum assembly of an engine system of a rotorcraft. The flapper assembly is positioned along the second tube end and comprises a flapper door that is configured to allow fluid to drain from the drain assembly to an engine compartment of the engine system of the rotorcraft. The flapper door is configured to prevent fluid, engine compartment gases, or flame from flowing into the drain assembly through the second tube end of the drain tube.

Abstract: A robot includes a housing including a first shell and a second shell and having a first configuration and a second configuration, a rack disposed in an inner cavity of the housing, a telescopic assembly disposed on the rack and connected between the first shell and the second shell, and a rotary wing assembly disposed on the rack and having a folded configuration and a flight configuration. The rotary wing assembly includes: a folding arm with one end rotatably connected to the rack, a rotary wing, and a tilting arm connected between the rotary wing and the folding arm, the tilting arm and the rotary wing are extended to an outside of the housing to be adapted to drive the robot to fly in the flight configuration, and the tilting arm is rotatable relative to the folding arm to adjust a rotation direction of the rotary wing.

Abstract: For sealing at the transition between high-lift devices and fairings, a shutter assembly can be installed in a high-lift system, thereby forming the shutter arrangement. The shutter assembly includes the shutter panel and possibly the driving member. The shutter assembly can be installed in the high-lift system, to form any embodiment of the shutter arrangement. The shutter arrangement covers the trunnion opening and is moveable in correspondence with the movement of the high-lift device in a continuous and strictly monotone manner.

Abstract: An environmental control system for use in an aircraft includes at least one component positioned along a length of the aircraft and a decompression panel assembly comprising an array of apertures. The array of apertures is based on a location of the decompression panel assembly along the length of the aircraft relative to the at least one component.

Abstract: An aircraft has retractable landing gear configured to reciprocate between a deployed position and a stowed position. A landing gear door installation includes a first door rotatably coupled to the aircraft about a first axis for movement between a raided position and lowered position. The door installation further includes a second door located aft of the first door and coupled to the aircraft for movement between a first position when the landing gear is in the stowed position, and a second position when the landing gear is in the deployed position. A portion of the first door overlaps a portion of the second door when the first door is in the raised position and the second door is in the first position so that the first door blocks deployment of the second door to the second position.

Abstract: An airframe-mounted package launching system including a package launching device mounted in an interior portion of an airframe structure proximate an external airframe opening, the package launching device including a launch bed configured to support a package during a launching process, and a launch assembly configured to impart a launching force to the supported package on the launch bed during the launching process.

Abstract: A simple and lightweight system for discharging water that can flow out through an orifice in an insulation blanket lining the walls of a fuselage of a transport vehicle such as an aircraft. The blanket has an impermeable collection plate having at least partially the shape of a channel, container or the like for collecting and discharging condensation water under the effect of gravity through an orifice.

Abstract: A gas turbine engine is provided having: a turbomachine; a fan section having a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an engine controller positioned within the nacelle. The nacelle defines an inner surface radius (r) along the radial direction inward of the engine controller, wherein the engine controller defines a radial height (?r) along the radial direction, a total volume (V), and a normalized radius (r?). The normalized radius (r?) is a ratio of the inner surface radius (r) to the total volume (V) to cube root, and wherein these parameters are related by the following equation: 0 . 1 ? ( r ? ) - 1 < ? ? r r < K ? ( r ? ) - 4 / 3 , wherein the normalized radius (r?) is between 1.25 and 8 and K is equal to 40%, or the normalized radius (r?) is between 2.75 and 4.5 and K is equal to 65%.

Abstract: A system is provided. The system includes a translucent display positioned such that a first face is a display face and that a second face is a projection face and at least one projector configured to project an image on the second face of the translucent display. The image is displayed on the first face. The system also includes at least one sensor configured to transmit a signal when triggered and a projector controller in communication with the at least one projector and the at least one sensor. The projector controller is programmed to receive a signal from the at least one sensor and instruct the at least one projector to project at least one image on the translucent display in response to the signal from the at least one sensor.

Abstract: An assembly having an aircraft door and auxiliary equipment. The aircraft door and the auxiliary equipment are connected by a flexible deformable bellows having creases. The door comprises a passing through hole and a support joinable to the first end of the bellows. The auxiliary equipment comprises a support joinable to the second end of the bellows and a projecting part. The projecting part is configured to have elevation movement and/or azimuth movement, and the projecting part crosses the interior of the bellows and the hole of the door and protrudes out of the door. At both ends of the bellows a clamp joins and tightens each end of the bellows with the corresponding support. There is a fixed joint between the first end of the bellows and the door and a movable joint between the second end of the bellows and the auxiliary equipment.

Abstract: A hard landing indicator mountable to a landing gear of an aircraft is provided. The landing gear has components displaceable toward each other upon the aircraft experiencing a landing. The hard landing indicator includes a first portion securable to one of these components and a second portion that projects outwardly from the first portion and oriented toward another component of the landing gear to be positioned within a path of displacement of the second component toward the first component. The second portion is impacted by this component upon this component being displaced during a hard landing of the aircraft. The impact leaves a visual mark on the second portion of the hard landing indicator to indicate that a hard landing has occurred. A landing gear equipped with and a method of installing such indicator are also provided.

Abstract: A system for rapid securement and disengagement of a battery assembly-type power source element is provided herein. The system can include a battery assembly that includes a battery element having opposite, opposing surfaces and configured to provide power to at least a portion of a vehicle. On the surface of the battery assembly a pin element can be disposed. The system also includes a receiver assembly configured to mechanically couple the battery assembly. The receiver assembly can include an insertion opening having a size configured to receive the battery assembly and a hook assembly. The hook assembly can include a hook configured to mechanically couple to the pin element of the battery assembly and shaft configured to drive the hook such that a distance between the insertion opening and the battery assembly is changed.

Abstract: A tie-down for attachment to an aft tail section of an aircraft for inhibiting damage to the aircraft when the aircraft is on the ground is disclosed. The tie-down has a mount member configured to attach to the aft tail section and a projection member supported by the mount member. The projection member extends in a generally downward direction from the mount member so as to provide a contact surface with the ground that is lower than the aft tail section.

Abstract: A heater panel includes a core and a heater/dielectric layer including a positive thermal coefficient (PTC) heater layer between a pair of dielectric layers. A structural facing is included, wherein the heater/dielectric layer is bonded directly between the core and the structural facing. A second structural facing can be bonded to the core opposite the heater/dielectric layer. An impact layer can be bonded to the structural facing, e.g., the first structural facing described above, opposite the heater/dielectric layer. The heater layer can be formed by direct writing a heating element pattern onto a dielectric layer bonded to the core.

Abstract: An attachment housing is for fastening to an exterior side of an aircraft. The attachment housing has a functional compartment. The functional compartment is divided in two, and has a ventilation compartment and a protective compartment. A surrounding wall is configured to separate the ventilation compartment from an environment. The surrounding wall has at least one ventilation opening for air exchange between the ventilation compartment and the environment. A dividing wall is arranged between the ventilation compartment and the protective compartment. The dividing wall has at least one passage opening for air exchange between the ventilation compartment and the protective compartment. The passage opening is configured to counter act a penetration of water, moisture, or particles into the protective compartment.

Abstract: Automated apparatus for performing maintenance functions on airfoil-shaped bodies having short chord lengths, the apparatus being movable in a spanwise direction along the airfoil-shaped body. In accordance with various embodiments, the apparatus comprises a blade crawler capable of supporting any one of a plurality of end effectors for performing a set of maintenance functions on an airfoil-shaped body, such as a blade component. Included in these functions are multiple options for nondestructive inspection, drilling, grinding, fastening, appliqué application, scarfing, ply mapping, depainting, cleaning, and painting devices that are attached as the end effector for the blade crawler. As a whole, the blade crawler reduces maintenance time, labor hours and human errors when robotic maintenance functions are performed on blade components.

Abstract: In one possible embodiment, an amphibious unmanned aerial vehicle is provided, which includes a fuselage comprised of a buoyant material. Separators within the fuselage form separate compartments within the fuselage. Mounts associated with the compartments for securing waterproof aircraft components within the fuselage. The compartments each have drainage openings in the fuselage extending from the interior of the fuselage to the exterior of the fuselage.

Abstract: A passenger door arrangement for an aircraft segment, which arrangement comprises a passenger door, which is configured to assume a raised state and a lowered state, and a “girt bar,” for arming and disarming an escape slide, the girt bar not altering its position relative to the passenger door in the transition from disarming to arming, when the passenger door is in the lowered state. Additionally an aircraft segment, which comprises the passenger door portion and a fuselage portion, an external engagement arrangement being fixed to the fuselage portion.

Abstract: Ventilation systems and methods for controlling moisture in a vehicle. The ventilation systems include one or more inlet ducts and outlet ducts that extend through an inner wall and into a gap formed at an outer wall. The ventilation systems provide for passive air flow with air moving into the one or more inlet ducts and into the gap. The air is cooled against the outer wall and vertically drops along the gap. Moisture in the air freezes against the outer wall while the air is in the gap. The less humid air then moves through the one or more outlet ducts and back into the interior space.

Abstract: A fairing for an aircraft is disclosed in which the fairing comprises a first fairing portion configured to be fixedly attached to a first structural component and having a first edge; a second fairing portion configured to be fixedly attached to a second structural component and having a second edge, wherein the first edge and the second edge define an interface configured to enable relative movement between the first fairing portion and the second fairing portion.

Abstract: A door opening system with a deceleration mechanism may be adapted to control an opening of a door module that includes a door panel and a door frame. Deceleration mechanism may include strap that connects door panel with door frame, spool, and spool. Spool may receive one end of strap, is biased to roll up a first portion of strap, and adapted to perform a first unwinding of the first portion of strap. Spool may receive a second end of strap, is biased to roll up a second portion of strap, and adapted to perform a second unwinding of the second portion of strap from spool. Spool may include a braking apparatus that is adapted to decelerate the second unwinding when a velocity of the second unwinding is above a predetermined threshold.

Abstract: An apparatus configured to reduce acoustic interactions between a propeller and a surface of an aircraft positioned downstream of the propeller includes a surface modification element of the surface of the aircraft. The surface modification element defines a modified contour of the surface. The modified contour is configured to decorrelate a phase distribution of a plurality of sound sources within a source field positioned on at least a portion of the surface.

Abstract: An apparatus for covering an opening in a fuselage of an aircraft includes a track and a plurality of panels, coupled to the track. At least one of the panels is movable along the track relative to an adjacent one of the panels between a first position and a second position.

Abstract: A wing or stabilizer of an aircraft. The wing or stabilizer comprises a box portion, comprising at least one spar and an outer skin coupled to the at least one spar. The wing or stabilizer also comprises at least one panel, comprising an outer face-sheet and an inner face-sheet. In a fore-aft direction the outer face-sheet terminates at an outer free edge. In the fore-aft direction the inner face-sheet terminates at an inner free edge. The at least one panel also includes a core sandwiched between the outer face-sheet and the inner face-sheet. The inner face-sheet comprises a cantilevered portion. The cantilevered portion defines the inner free edge. The cantilevered portion is fastened to the outer skin of the box portion.

Abstract: A foil hinge system for a hydrofoil or airfoil includes a main foil body 1, substantially extending in a longitudinal direction L and a transverse direction T, a flap 2 hinged to the main foil body 1 arranged on a longitudinal end side of the main foil body 1, and a flexible element 3 connecting the main foil body 1 and the flap 2. Several rigid structures 4, 5 are arranged in such a manner on the flexible element 3, that they provide a dead stop when the flap 2 is in a maximum deflection with respect to the main foil body 1.

Abstract: Some embodiments are directed to an unmanned vehicle for transmitting signals. The unmanned vehicle includes a transmitting unit that is configured to transmit a signal towards an object. The unmanned vehicle also includes a control unit that is in communication with at least one companion unmanned vehicle. The control unit is configured to determine a position of the at least one companion unmanned vehicle relative to the unmanned vehicle. The control unit is further configured to control the transmitting element based on at least the position of the at least one unmanned vehicle such that the transmitting element forms a phased-array transmitter with a transmitting element of the at least one companion unnamed vehicle, the phased-array transmitter emitting a transmission beam in a predetermined direction.

Abstract: A method, an apparatus, and a computer program product for wireless communication are provided. The apparatus receives reference timing information, determines one or more timeslots for transmitting a beacon based on the reference timing information, and transmits the beacon during a timeslot of the one or more timeslots. The beacon is transmitted in one or more directions respectively corresponding to a number of subslots of the timeslot. In another aspect, the apparatus determines a timeslot for receiving at least one beacon respectively from at least one connection point based on the reference timing information, wakes during the timeslot, monitors for the at least one beacon in one or more directions respectively corresponding to a number of subslots of the timeslot, and receives the at least one beacon in the at least one timeslot in at least one direction of the one or more directions.

Abstract: An aircraft wing has a fixed wing portion and a trailing edge flap movable with respect to the fixed wing portion to define a gap between the fixed wing and the flap. A seal assembly has a first rigid seal member fixed to the fixed wing portion and a second resilient seal member fixed to an upper surface leading edge portion of the flap. The trailing edge flap is deployable between a first flap position in which the trailing edge flap conforms to a profile of the fixed wing portion, a second flap position in which the trailing edge flap is deflected upwardly from the first flap position, and a third flap position in which the trailing edge flap is deflected downwardly from the first flap position. In the first flap position the first seal member contacts the second seal member to at least partially seal the gap, and in the second flap position the first seal member presses against the second seal member and deflects the second seal member to at least partially seal the gap.

Abstract: There is provided a training system capable of performing work. The system has a shape memory alloy (SMA) actuator exhibiting a generally planar transformational behavior. The system further has one or more heating elements for transforming the SMA actuator from an original shape to a trained shape, thereby performing work.

Abstract: Device for draining liquids for an aircraft engine, comprising a collector designed to collect liquids drained from the engine, said device comprising means for pumping the liquids held in the collector and for discharging said liquids, and monitoring means designed to indicate when the liquids have been collected by the collector in an anomalous manner, said monitoring means being designed to be activated when the flow rate of collected liquids is greater than the delivery of the pumping means.

Abstract: Disclosed are various embodiments of a structural reinforcement system. The system reinforces hollow cavities within various products to increase the structural rigidity of the product. The system generally includes a rigid carrier, a bonding material, and an insert. The rigid carrier provides the primary structural reinforcement within the cavity, and also serves as a substrate to carry the bonding material. The insert is provided to increase the structural rigidity of the reinforcement system.

Abstract: A grounding clip for an organic matrix composite guide vane with a metallic sheath comprises the organic matrix composite guide vane includes a body having a leading edge and a trailing edge opposite the leading edge and a root end extending between the leading end edge and the trailing edge. The metallic sheath is attached proximate the leading edge and extends to the root end. A metallic attachment fitting has a receiver configured to receive the root end of the organic matrix composite guide vane for coupling the organic matrix composite guide vane to the metallic attachment fitting. The grounding clip is coupled to the sheath proximate the root end; wherein the grounding clip is electrically connected to the metallic attachment fitting and the metallic sheath.

Abstract: A connecting rod assembly for a flight control surface actuation system, the assembly comprising a connecting rod for connecting a flight control surface to a rotary actuator and a position sensor mounted to the connecting rod for sensing the position of the connecting rod relative to a rotary actuator.

Abstract: An HUD unit is equipped with a first display and a second display. The light irradiating directions of the first display and the second display are adjusted so that the first image irradiated from the first display, reflected by the front window of a vehicle and visually recognized by the driver of the vehicle and the second image irradiated from the second display to the eye point of the driver and visually recognized by the driver are visually recognized in a state of being arranged side by side.

Abstract: A device for extraction of bleed air from flowing air at or in an aircraft engine includes an adjusting device for adjustment of an inlet cross section of an opening for the bleed air in or at a wall during operation of the aircraft engine. The opening for the bleed air is arranged in or at a deformable base and the adjusting device acts on the deformable base for modifying the inlet cross section of the opening relative to the flowing air. The deformable base is part of a metallic housing in the aircraft engine.

Abstract: The present disclosure relates to a centering device for a nacelle of a turbojet engine providing the flush centering of an outer downstream panel of a thrust reverser with respect to a cowl of a fan casing. The centering device includes, in one single piece: a sub plate allowing the fixing of the centering device to the fan casing; a first positioning arm integrally formed with the sub plate, protruding upstream, in such a manner as to form, with respect to a directing axis (A) of the nacelle; a first radial abutment designed for guiding the cowl of the fan casing; and a second positioning arm, integrally formed with the sub plate, protruding downstream, in such a manner as to form, with respect to the directing axis (A) of the nacelle, a second radial abutment designed for guiding the outer downstream panel.

Abstract: The invention relates to a valve (10) for controlling the internal pressure p in a cabin of an aircraft, comprising a first flap (11) and a second flap (12), wherein the flaps (11, 12) control a pressure-changing fluid flow (L) between the surroundings and the cabin through an opening (15) of a limiting element (14) of the cabin. In order to increase the inflow volume of the fluid, according to the invention at least one of the flaps (11, 12) is adjustable in the inflow position in respect of the opening (15) in the direction of the surroundings, such that the flow surface of the flap (11, 12) is increased for the air flow (L). Furthermore according to the invention at least one of the flaps (11, 22) has a closure device (21) which reduces an outflow of the fluid that had previously flowed in during an inflow process.

Abstract: A self-aligning structural attachment and a corresponding method are disclosed. The self-aligning structural attachment includes a main body having a proximal end and a distal end, wherein the main body is attached to (i) a CIP of a support system and (ii) a clevis on an airframe of an aircraft. Further, the self-aligning structural attachment includes a first attachment fitting disposed on the proximal end, wherein the first attachment fitting is a slide-and-swivel attachment fitting. Still further, the self-aligning structural attachment includes a second attachment fitting disposed on the distal end, wherein the second attachment fitting is a slide attachment fitting. Yet still further, the self-aligning structural attachment includes a pivoting hinge disposed between the first attachment fitting and the second attachment fitting.

Abstract: An exhaust nozzle liner assembly of a gas turbine engine includes a first liner, a second liner spaced from the first liner by a gap, a seal assembly located at least partially within the gap to provide a continuous surface defined by the first liner, the seal assembly and the second liner, and a seal retainer to retain the seal assembly.

Abstract: A method for installing an electric system into an aircraft fuselage. The object to provide a method for simply and quickly installing an electric system into an aircraft fuselage, wherein the electric system is as little heavy and space consuming as possible, and wherein a wide range of customized alternatives of the electric system is possible, is achieved by the steps of providing a fuselage element extending along an aircraft longitudinal axis and including an outer skin and an interior surface, providing a foil sheet of an electrically insulating substrate material, attaching said foil sheet on the inner side of said fuselage element, applying particles of electrically conductive material onto the inner surface of said attached foil sheet opposite the outer skin in a predetermined pattern, such that the accumulated particles of electrically conductive material form electric conductor elements along said inner surface of said foil sheet.

Abstract: A titanium seat track may include a track plate formed of one of cold and hot rolled titanium. The track plate may include a top surface and a bottom surface. The titanium seat track may also include a titanium U-shaped channel formed of cold worked titanium sheet. The titanium U-shaped channel may include a first side wall and a second side wall extending from a base and terminating in a first channel edge and a second channel edge, respectively. The first channel edge and the second channel edge may be continuously welded to the bottom surface of the seat track.

Abstract: A fairing transition is provided for covering a gap between a movable body and a fixed body on a vehicle that includes, but is not limited to a base plate that is attachable to a vehicle, a cover plate that is attachable to the base plate. The base plate and the cover plate include, but are not limited to a correspondingly formed connecting profile having positive fit on surfaces that face each other, with the connecting profile configured to slide the cover plate onto the base plate. Furthermore, the cover plate is lockable to the base plate in an end position.

Abstract: An aircraft having an aircraft fuselage that has an outer skin includes an air sucking fuselage component with an outer surface that is perforated at least in some regions, and a suction profile body. The suction profile body is arranged on the outer skin, forms a local bulge in the outer skin, and further includes a suction opening that is arranged at a location at which there is the lowest pressure, for example at a position furthest away from the outer skin. The suction opening is connected to a suction connection of the air sucking fuselage component. In this way laminarization of the flow at the air sucking fuselage component may take place without the use of active air conveying devices.