Abstract: A wing-to-body fairing for reducing noise due to wing-to-body fairing vibrations in an aircraft, spacecraft, or vehicle may include a honeycomb center having a cavity which is at least partially filled with particle material.

Abstract: The connection of a rudder unit on the fuselage of an aircraft frequently leads to an inhomogeneous flow of forces in the connecting region between the rudder unit and the fuselage or even to an offset of the flow of forces relative to the centroidal axis, e.g., due to multiple-bolt connections. This is extremely disadvantageous with respect to static considerations. One embodiment of the present invention proposes a connection for a rudder unit on an aircraft fuselage, in which the flow of forces resulting from the connection between the rudder unit spars and the fuselage frames extends in a largely homogenous fashion from the rudder unit spars to the fuselage frames and into the fuselage. The connecting elements are advantageously arranged within the rudder unit and the fuselage in such a way that no additional enveloping aerodynamic fairings are required that would result in an additional increase in the aerodynamic drag.

Abstract: An improved vent system for venting an internal cavity of an aerospace vehicle to an exterior surface of the aerospace vehicle generally includes a substantially concave vent inlet surface recessed with respect the exterior surface, and a duct opening formed therein. The vent inlet surface has a major axis substantially parallel to the local external flow direction. The upstream surface contour and the downstream surface contour of the vent inlet surface are substantially oblique to the local external flow direction. The placement and orientation of the duct opening, as well as the geometry of the vent inlet surface, may be selected to achieve a particular pressurization of the internal cavity with respect to the external environment under a variety of conditions.

Abstract: The invention relates to a floor plate for bearing upon a floor framework in an aircraft. The floor framework is formed with a multiplicity of transverse beams which are arranged like a truss, and a multiplicity of longitudinal profiles, especially seat rail profiles, which extend transversely to the transverse beam. At least one sub-assembly, for example a kitchen module and/or a sanitary cell, can be fastened on the floor plate. The floor plate bears upon at least four longitudinal profiles and has at least one connecting point, especially an insert, for fastening of the sub-assembly. In addition, at least one system port is provided for the tool-less, pluggable connecting of the sub-assembly to any on-board systems of the aircraft, especially to electrical systems, to feed-air systems, to exhaust air systems, to fresh-water systems or to waste-water systems.

Abstract: An aircraft (1000) includes multiple servicing levels (1014, 1016) and a flight deck level (1040) that is isolated from the servicing levels (1014, 1016). An aircraft security system (1001) includes a passive system (1030) and an active system (1032) that is in operation with said passive system (1030). The passive system (1030) includes a service opening (1050) for both passengers and cargo and the flight deck (1040) that is isolated from the service opening (1050).

Abstract: A method for manufacturing a structural component includes a first step of attaching at least one conductive member to a surface of a base material made of a composite material and a second step of forming the base material by conducting electricity to part or the whole of the conductive member to generate heat and/or making an assembly of the structural component by conducting electricity to part or the whole of the conductive member to generate heat. Part or the whole of the conductive member contained in the structural component produced in the first and second steps serves as a member giving to the aircraft at least one of a lightning strike protection function, an anti-icing and deicing function and an electromagnetic interference shielding function.

Abstract: A system for displaying at least one virtual future journey to at least one passenger onboard a mobile platform (such as a train, marine vessel, aircraft or automobile) is provided. The system includes a display device that displays the virtual future journey. The system further includes a journey futuring control module that generates the journey data that includes at least one future journey for the passenger. The future journey is selected from the group that includes a journey from the mobile platform to a baggage claim, a journey from the baggage claim to a transportation means, a journey via the transportation means to a destination, and combinations thereof. The system further includes a graphical user interface control module that displays the future journey for the passenger on the display device to enable the passenger to virtually view the future journey.

Abstract: A handle for use in operating a door of an aircraft. The handle is fixed to a shaft and rotates the shaft about an axis. The handle includes multiple separately movable sections, the sections arranged so that each section has a limited range of movement separate from the other. The handle is capable of operating the door when the sections are moved substantially in unison. The handle also provides positive actuation of movable door components.

Abstract: A system for anticipating the needs of at least one passenger onboard a mobile platform (such as a train, marine vessel, aircraft or automobile) is provided. The system includes a passenger seating area for receipt of the passenger. The passenger seating area includes a seat that has a seat back that moves into a reclined position, a tray table that is operable to be positioned to provide a surface for use by the at least one passenger, and a light source disposed for illumination of at least a portion of the passenger seating area. The system includes a camera that acquires an image of the passenger, and a gesture control module that generates activity data that includes at least one activity that the passenger is performing as recognized in the image of the at least one passenger acquired by the camera. The system further includes a smart control module that moves the seat back, positions the tray table, activates or deactivates the light source and performs combinations thereof based on the activity data.

Abstract: The present invention relates to a circuit breaker box and monitoring system. The circuit breaker box includes a circuit breaker panel and a door allowing the circuit breaker panel to be hidden from view. The circuit breaker monitoring system will inform the pilot if a circuit breaker has tripped.

Abstract: An aircraft landing gear is arranged such that in its deployed position it is configured to reduce, during the approach on landing, the noise generated by the interaction of the landing gear and the air flowing past the landing gear. Various means are described to reduce the amount of turbulent air flow generated in the region of the landing gear, including inverting and fairing the nose-gear shock-absorbing leg, providing faired twin in-line oleos and providing fairings that produce shielding air curtains.

Abstract: An aircraft the propulsive units of which include engines, and which is distinguished by reduced noise emissions, includes a wing structure fixed to an upper region of the fuselage, and a vertical tail system having at least two vertical stabilizers which are generally vertically fixed to the fuselage aftwardly of the wing structure. The engines are disposed side by side in a propulsive package disposed above the fuselage, which propulsive package includes the following, air inlet openings for the propulsive package, which openings are disposed above the fuselage between a point at the leading edge and a point at the trailing edge of an aerodynamic root chord of the wing structure; and exhaust nozzle conduit outlets associated with exhaust nozzle conduits, which outlets are formed by the structure (cowling structure) of the propulsive package, and are disposed above the fuselage forwardly of an aft terminus of the fuselage and between the vertical stabilizers.

Abstract: One embodiment of a seal removal tool may include a handle, a seal grasping member, and a biasing member. The handle may have an end with a curved surface to roll back a seal. The seal grasping member may be adapted to move from an open extended position into a closed position in order to grasp and secure a seal. The biasing member may bias the seal grasping member towards the closed position.

Abstract: A personal user control device suitable for use in cooperation with information systems, such as vehicle information systems, and methods for manufacturing and using same. The personal user control device provides a user-friendly interface system for interacting with the information system. Unlike conventional control devices, the user interface system includes no dedicated buttons and provides a customizable environment for interacting with the information system. When in communication with the information system, the personal user control device can automatically detect system status information, such as available system functionality, available viewing content, and/or a current system operation mode, of the information system and provides a user interface system that instinctively adapts for use with the information system in light of the detected system status information. The personal user control device thereby provides a versatile and intuitive manner for interacting with the information system.

Abstract: A visor for shielding the interior of a vehicle from the light or glare from a light source includes a visor that can be rotated about an axis from a stowed position to a shielding position. The visor may also be translated along a track so that the placement of the visor along the length of a large window may be chosen with precision.

Abstract: The invention relates to a cooling system for an electronic box capable of releasing heat. It comprises a passive cooling device able to be connected to the electronic box and an element consisting of a heat-conducting material, and this element comprises at least one contact region connected to the passive cooling device, this contact region being arranged on the element so as to dissipate the heat coming from the cooling device toward the whole of the element.

Abstract: An aircraft with an outer surface from which flows an aerodynamic stream of cold air and includes at least one hot gas outlet, characterized in that it includes at least one device (16) for generating aerodynamic disturbances so as to mix hot gas and cold air, whereby the at least one device is connected to an outer surface (10) for protection against the heat and/or close to a hot gas outlet (12).

Abstract: Aircraft with reduced environmental impact. According to the invention, the engines (6) are mounted at the rear (2R) of the fuselage (2) of said aircraft in such a way that the propellers (8, 9) of said engines (6) are plumb with non-structural removable surfaces (14).

Abstract: Under one step of one embodiment of a solid state method for joining structures, angled edges of at least two structures are disposed adjacent to one another. In another step, a plurality of angled joining members are disposed adjacent to one another between the adjacent angled edges of the at least two structures. In still another step, the angled joining members are welded between the adjacent angled edges of the at least two structures. In yet another step, at least one hole is formed into and extended between adjacent edges of the welded angled joining members. In an additional step, a plug member is forced at least partially into the at least one hole.

Abstract: An exemplary embodiment of the present invention indicates an installation system for an airplane for securing interior equipment, which exhibits longitudinal and transverse rails. The transverse rails are designed as peripheral rails, and exhibit perforations to which the interior equipment can be secured.

Abstract: In one embodiment, an apparatus is provided for covering and uncovering a flap opening in an aircraft. The apparatus comprises a door member, a torque tube roller member, at least one roller member, and a biasing member. The door member may be adapted to cover and uncover a flap opening. The torque tube roller member may be attached with the door member, and may be adapted to be pushed by a torque tube member attached with a flap of an aircraft. The door member may be adapted to be driven from a closed position covering a flap opening into an open position uncovering a flap opening. The roller member may be attached with the door member and may be adapted to follow at least one track member. The biasing member may be attached with the door member for biasing the door member towards a closed position covering a flap opening.

Abstract: An aircraft structural element having a cavity. The structural element has an opening in a wall of the cavity through which moisture located in the cavity can escape into the surroundings, wherein a drainage element for sealing the opening in the wall of the cavity is provided in the opening. In order that the structural element can be produced with a low expenditure on components and assembly equipment, the drainage element comprises a hollow cylinder which connects the cavity of the structural element to the surroundings, which is provided with an external thread having a predefined external diameter, and a head at one end which has a predefined diameter, wherein the external diameter of the thread is smaller than the head diameter.

Abstract: A fairing system developed to reduce the flow disturbance around sensor elements allowing accurate measurement of the pressure distribution on an object surface. The fairing also protects the sensors and electronics of the pressure belt from direct exposure to airflow.

Abstract: Embodiments provide a cargo floor, a system, and a method adapted to be made integral with or complementary of the aircraft fuselage. Cargo floor members may be adapted to be coupled with a flat fuselage bottom inner skin of an aircraft fuselage to serve as the main orthotropic stiffeners to the flat fuselage bottom inner skin such that a portion of the in service loading experienced by the aircraft are shared by a combination of the fuselage and the cargo floor.

Abstract: Lightweight structural component including at least one panel and at least one stiffening element oriented one of lengthwise and crosswise. The at least one stiffening element includes two side pieces. Each of the two side pieces is at least partially connected to the panel in a material-locking manner. The two side pieces are connected to the panel at two separate joint zones. A method of producing the lightweight structural component includes milling the at least one panel to form at least one thickened region and joining the two side pieces to the at least one panel at the two separate joint zones. This Abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way.

Abstract: An energy absorbing apparatus and system for leading edge structures includes an impact member, such as a “bird-band”, of a plastically deformable material of a predetermined configuration positioned with the structure in an area of the leading edge of the structure to absorb energy of an impact of a projectile with the leading edge of the structure, and to redistribute the energy of the impact to the structure, and can break up the projectile, and can increase the impact area. The structure can have one or more sheet members, such as a single sheet, or an inner face sheet and an outer face sheet with a core positioned between the inner face sheet and the outer face sheet. One or more impact members of the plastically deformable material can be positioned with one or more of the single sheet, the inner face sheet, the outer face sheet or the core.

Abstract: The present invention provides a non-threaded insert operable to transfer or couple a mechanical load to a structure. This non-threaded insert includes an upper insert having a noncircular cross section and a lower insert. The coupled upper and lower insert are received within the structure and are operable to receive a mechanical load which is then distributed to the structure. The noncircular cross section of the upper insert is received within a noncircular receptacle wherein rotation of the upper insert within the receptacle is inhibited by mating the noncircular cross section of the upper insert within the noncircular receptacle. This allows mechanical loads to be distributed to be better coupled to materials such as composite materials wherein traditional thread fasteners would intensify mechanical stresses within the coupled threads.

Abstract: Sealing device for the flap track for the flap-actuating shaft, in the belly fairing of an aircraft, with a top hollow body 1 and a bottom hollow body 7 which are flexibly compressible, each comprising at least one interior chamber 2, 8 with open sides 2a, 2b, a wall 3, 9 with respective external contact surfaces 3a which are in flexible contact with each other, the outer surfaces 4a, 10a of the front walls 4, 10 of the hollow bodies 1, 7 jointly forming an outer sealing surface 11 which covers the flap track 19, said hollow bodies 1,7 having jointly a vertical compression flexibility such that the contact surfaces 3a, 9a retract around the actuating shaft 20, the interior chambers 2, 8 extending between the front walls 4, 10 and rear walls 5, 11 of the hollow bodies 2, 7.

Abstract: A line of sight antenna supported in an upturned terminal winglet or similar vertical member of an aircraft is disclosed. An aperture is formed in the conductive winglet or vertical member, and the antenna is supported within the aperture by a support mechanism such that the antenna is exposed to the line of sight transmissions. A non-conductive covering may also be used for the aperture. Using the cover, the antenna within the winglet can be configured so that it does not alter the appearance or aerodynamic characteristics of the aircraft. Alternatively, the antenna can be coupled to the outside of the winglet or vertical member if cosmetics are not a concern. The frequency range of the antenna can be tuned to cover desired frequency ranges. The antenna position at the winglet maintains a large physical separation from fuselage-mounted antennas thereby reducing interference.

Abstract: A windblocker adapted to be anchored in the interior of an aircraft, comprising a tensioning device adapted to be centrally disposed in a cross-sectional area of the interior of the aircraft, securing straps that extend radially from the tensioning device to mounting points provided on a load-bearing skeleton of the aircraft and adapted to be secured to the mounting points when the windblocker is installed in the aircraft interior, and fabric segments supported on the supporting straps and filling spaces provided between the securing straps.

Abstract: The present invention provides a thrust recovery valve that is less expensive and lighter weight while maintaining required system safety. It utilizes valve doors made partially of plastic material and uses aluminum structure on the outer surface of the door, with a main structure made from fiber reinforced plastic material. The structure of the door is made from injection molded, fiber-reinforced plastic, called the “insert” having complex geometric features including the aerodynamic inner surface, the sculpted hollow inner surfaces for weight savings, and grooves required to hold seals and energizing springs. The “plate”, shaped to match the airplane skin contour, provides reinforcing structure on the external surface of the airplane.

Abstract: A surface-mounted fuselage skin appliqué panel having an aperture to a reference static air input port is rugged, replaceable, and independently calibratable. The static port skin appliqué generally conforms to the fuselage surface, and is held in place either with adhesive or with a mounting frame. The appliqué size enables airflow in the vicinity of the static port to be substantially uniform. Because the appliqué is not part of the fuselage structure, distorting stress loads are avoided. The appliqué material resists scratches and bumps that can distort flow. A static port skin appliqué and its mounting provisions can be made using a range of materials, and can receive finishes to meet user preferences.

Abstract: Disclosed is a floor panel, in particular for covering floors of cargo holds of aircraft. The floor panel is formed by a plurality of milled profiles, which are friction stir welded in each case along their longitudinal edges, with preference continuously to form longitudinal (butt) seams. The milled profiles each form a beam “of equal stress”, with an upper flange and a lower flange which are spaced apart from one another along their extent. The milled profiles have in each case a double-T-shaped cross-sectional profile, the upper flanges and the lower flanges being respectively connected by webs. With preference, the milled profiles are milled out in one piece from solid material of a sufficiently tough aluminium alloy.

Abstract: A latch device is provided for attaching interior linings, panels, or other surface components to an interior structure or part, such as the passenger compartment of an aircraft, without using any tool. The latch device has a latch base, a support member having a latch groove positioned rearwardly of a forwardly projecting tongue, a latch pawl above the latch groove movable under spring pressure between a pawl-detent position and a pawl-release position, and an actuator member having a striker pin retained between spaced-apart arms and an actuator end part at its opposite end. An edge portion of an interior lining is aligned with the striker pin and fed onto the tongue and into the latch groove against the spring pressure on the latch pawl, and can readily be removed by levering the actuator end part to unlatch the pawl from the striker pin.

Abstract: In the case of apparatuses which are intended in particular for aircraft construction and have a movement device for objects such as films, cloths, lids or the like, expanding band drives are in each case used for this purpose, whose expanding bands carry out limited linear movements, in which case the apparatuses can be used as waterless toilets, supply containers for hand towels which can be rolled up and/or unrolled, as a sun protection device for aircraft cabin windows, as a conveyor belt for luggage or transport containers with closable lids for on-board luggage.

Abstract: Sealing system for the gap (2) existing between the fuselage (3) and the elevator (4) of the orientable horizontal stabiliser (5) of an aircraft which comprises a main body (1) formed by an upper surface (18) and a lower surface (19) and at least one longitudinal vertical element (22) arranged between the two surfaces (18,19) which grants rigidity to the main body (1), and a plurality of first elastic sealing profiles (9) between the first surface (11) of the main body (1) and the outer surface of the fuselage (3) and making contact with them, and a plurality of second elastic sealing profiles (13) between the second surface (12) of the main body (1) and the first end of the elevator (15) and making contact with them, in such a way that the sealing of the gap (2) takes place and an aerodynamic continuity is produced between the fuselage (3) and the elevator (4) when the elevator (4) is at rest in the plane of the orientable horizontal stabiliser (5) for any of the orientation positions of the orientable horiz

Abstract: The invention relates to an electric connector assembly comprising a plug (10) having primary contacts (20) and a base (12) having secondary contacts (24) capable of interacting with the primary contacts. The connector assembly also comprises a closure flap (30) fixed to the base and capable of pivoting between a closed position in which it closes off an axis to the secondary contacts (24) and an open position in which it frees an access to the secondary contacts to make it possible to connect the plug to the base, and an annular sleeve (40) fixed to an electric cable (14) connected to the plug (10) and capable of being moved between two extreme positions, a bottom position in which it covers the closure flap (30) when the plug and the base are connected and a top position in which it frees an access to the plug.

Abstract: Helicopter reduced vibration axial support struts and aircraft suspension system are disclosed with at least one vibration controlling fluid containing strut. The powered struts include an outer rigid housing containing an inner rigid member and first and second variable volume fluid chambers. Fluid pressure differentials are created between the first and second variable volume fluid chambers to control motion between the strut ends. The powered fluid containing struts, support isolators, suspension systems, and methods of operation provide reduced helicopter aircraft vibrations.

Abstract: A roll-on/roll-off, aircraft-borne sensor pod deployment system having an operator station and a sensor pallet system and method of using same. The operator station has a base platform, a shelter box mounted on the base platform for accommodating a human operator, and a computer installed inside the shelter box. The sensor pallet system has a base platform, a linear system mounted on the base platform, a rotational system mounted on the linear system, a mechanical arm attached to the rotational system, a sensor pod attached to the mechanical arm, and an electrical control system that provides power to the deployment system and controls movements of the sensor pallet system. In operation, the sensor pod can be retracted into a compact, stowing position, or extended out an opening in the aircraft for an unobstructed field of view. The deployment system optionally includes an apparatus and method for sealing the aircraft opening.

Abstract: An arrangement (10) for installing a component (12) in an aircraft comprises a guide device (14) which is connectable to an aircraft structure or is formed integrally with the aircraft structure, as well as an elastically deformable damping element (16; 16a, 16b, 16c) which is adapted to enable the component (12) to be mounted in the guide device (14) in a self-supporting manner. A locking mechanism (26) is adapted to fasten the component (12) in a desired position in the guide device (14) in a releasable manner.

Abstract: A thermal insulating element (10?; 10??) comprises a first plate (24) forming at least a part of an outer face of the insulating element (10?; 10??) and a second plate (26) forming a further part of the outer face of the insulating element (10?; 10??). The first and the second plate (24, 26) are connected to each other via a frame structure (12) which establishes a geometry of the insulating element (10?; 10??). The first and the second plate (24, 26) and the frame structure (12) define a cavity filled with air, wherein at least one vent opening (28) is formed in the first and/or the second plate (24, 26) and/or the frame structure (12). A projecting edge portion (34, 36) is formed along an edge of a portion of the insulating element (10?; 10??) which is provided with the at least one vent opening (28), the projecting edge portion (34, 36) being adapted to at least partially cover a gap between two insulating elements (10?; 10??) disposed side by side.

Abstract: A receptacle for a fastener is provided that may be relatively light weight and compact, may reduce the number of parts required for mounting an object to a surface, and may allow for greater flexibility in positioning the fastener. Additionally, a corresponding method for installing a receptacle and mounting an object is provided. The receptacle has an outer housing and a floating insert, and the floating insert is positioned within an internal cavity of the outer housing. A fastener may be inserted into an internal cavity of the floating insert through apertures in the outer housing and the floating insert. The floating insert is configured such that it is movable within the outer housing. As a result, the location of the aperture of the floating insert is adjustable, providing greater tolerances during the installation process.

Abstract: An acoustical and thermal insulation product suitable for use in an aircraft is provided, comprising an insulation layer formed from a sheet of insulation material, wherein the sheet of insulation material is arranged to form a series of undulations defining a series of alternating upper ridges and lower ridges of the sheet.

Abstract: A system for distributing signals between a first seat and a second seat of a platform. The system generally includes an elongated bus and a connector operable to provide a connection between the bus and the passenger seats. Signals can be transmitted between the bus and the passenger seats, via the connector, at any point along the power bus, thus eliminating the need to run separate connections between the signal source and each seat. The bus is connected to the connector by depressing the bus upon the connector. This system and method significantly reduces the amount of time, energy, and expense necessary to individually wire each passenger seat to receive signals, such as power and/or data.

Abstract: An acoustical and thermal insulation product suitable for use in an aircraft is provided, comprising: an insulation layer formed from a sheet of insulation material, wherein the sheet of insulation material is arranged to form a series of undulations defining a series of alternating upper ridges and lower ridges of the sheet, and a plurality of elongated reinforcing members for reinforcing the insulation product.

Abstract: Disclosed is an improved aircraft window having RF shielding. In one embodiment, a window shield comprises an electrically conductive, transparent, flexible film, which is applied by known processes to a window pane. This shield is grounded to the aircraft frame or exterior by a “tail” of conductive material, which is secured to a ground point in the vicinity of the window pane.

Abstract: A fairing system developed to reduce the flow disturbance around sensor elements allowing accurate measurement of the pressure distribution on an airplane exterior surface. The fairing also protects the sensors and electronics of the pressure belt from direct exposure to airflow.

Abstract: Described herein is a computer design-aided shield for exposed surfaces on aircraft, a method for manufacture, and kits derived from collections of shields, each kit appropriate for use on a single aircraft type. The shield is contemplated for first use on general and corporate aviation aircraft. The kits are designed for convenient distribution to private pilots, and easy use by them on their aircraft. The shields can be transparent, or can bear lettering or insignia.

Abstract: An aircraft fuselage element (26) with a fuselage body (30) which forms an internal cavity (40) and which includes a viewing window (32, 34). To provide for taking substantially distortion-free high-resolution pictures in the infrared wavelength range and from a large angular range the fuselage body (30) is mounted for rotation about an axis of rotation (36).

Abstract: For use on board a mobile means of transport (eg. aircraft, bus, ship), a heating system and method are described which lead to a reduction of peak demand in the on-board kitchen energy supply system relating to the integrated heating appliances for the warming or heating of food. For this, latent or thermochemical heat storage units are used which are fully integrated into the structural elements of the heating appliance in question and heats the product in such a way that there is sufficient heat output, while at the same time, the absolute temperature is limited by means of an appropriate choice of heat storage material for product enhancement.