Abstract: A method of designing and manufacturing apparatus. The method comprises: creating a design space; analysing expected loads acting on the design space to calculate a first load path within the design space; analysing expected loads acting on the design space when the apparatus is in a damaged state to calculate a second load path within the design space; selecting a region of the second load path which falls outside the first load path; and creating a final design which includes: a primary structure falling within the first load path; and a damage indication feature falling within the selected region. The damage indication feature is designed to provide a visual indication when the load transmitted by the damage indication feature exceeds a threshold.

Abstract: An avionics equipment carrier system for slide-in modules with data processing, data transmitting, data storage or data displaying devices, such as for example electronics printed circuit boards, network components, storage devices, display devices and the like, or power supply devices, includes a housing, at least one module rack for accommodating the slide-in modules and at least one backplane board with Ethernet connection architecture. When the dimensions of the housing comply with ARINC standards, and the housing is arranged for installation in an avionics module rack as a quick-mount housing, and any desired circuit boards of a specific standard format can be used in the slide-in modules which are designed as quick-mount modules.

Abstract: A composite frame includes a plurality of truss elements covered by a cap. The truss elements are flexibly coupled with each other and with the cap. The frame flexes to conform to a contoured surface to which it is attached. Once attached, the installed frame provides the required rigidity to the structure.

Abstract: The invention relates to an aircraft comprising: a drainage system for condensation water formed in the aircraft between an upper zone thereof where the condensation water is formed and a lower zone where it is collected, a thermal insulation blanket (16) having two opposite faces, a first face (16a) of which is arranged facing the fuselage. The drainage system includes a drainage duct (18, 24) which extends into the upper zone along the second opposite face (16b) of the insulation blanket and which is connected to a pass-through device (30; 40) for the blanket placed beneath the upper zone. In this way, the drained condensation water passes through the blanket through the pass-through device and then is drained to the lower zone, between the first face of the blanket and the fuselage.

Abstract: A holder assembly for a line installation in an opening of a support structure of an aircraft, includes at least one holder element to mount a line that is guided through the opening, with the line featuring a clamping section, arranged radially on the outside, to be attached to the opening as well as at least one central receiving section to fix the line, wherein the receiving section of a first holder element encompasses the line hook-like, and the receiving section of at least a second, oppositely positioned holder element also encompasses the line hook-like such that both hook-like receiving sections encompass the line.

Abstract: Vibration-damping blankets are attached to the back surfaces of fairing panels of a flight vehicle (e.g., an aircraft or spacecraft) to reduce vibration, fatigue, structure and airborne transmitted energy, and cabin noise. In one case, the flight vehicle fairing has an exterior comprising exterior surfaces of a multiplicity of removable panels. A method of retrofitting the flight vehicle with vibration-damping blankets comprises: removing a panel from the flight vehicle exterior; attaching a vibration-damping blanket to a back surface of the removed panel; and installing the panel with attached vibration-damping blanket on the flight vehicle with the exterior surface of the panel forming part of the flight vehicle exterior. In one embodiment, the vibration-damping blanket comprises polymeric (e.g., aromatic polyamide) fibers in a nonwoven structure.

Abstract: A device for protecting and guiding at least one cable (22) that connects a direct-vision window (10) of an aircraft cabin that is provided for blocking an opening, and connects its support (14), includes a cable chain (26) that can deform along a winding plane and protect and guide the cable (22), on both sides of the cable chain (26), a first support (28) that is articulated relative to the direct-vision window (10) so as to be able to pivot around an axis of articulation (36) that is essentially parallel to the release translation and a second support (30) that is articulated relative to the support (14) so as to be able to pivot around an axis of articulation (38) that is essentially parallel to the release translation and the first and second supports (28, 30) have a square cross-section.

Abstract: A gas turbine engine has a nacelle, a plurality of pipes and a drains assembly, the drains assembly including a drains mast that extends through the nacelle and provides an outlet for the pipes. The engine is characterised in that drains assembly has a connection block defining internal passages and is arranged to connect between the pipes and the drains mast. The connection block also has lateral connections to the pipes enabling the nacelle to have a lower profile; thereby reducing aerodynamic drag.

Abstract: An apparatus is disclosed which includes an aircraft wing and a sensing unit. The sensing unit includes: a blister on an underside of the aircraft wing; a first and second sensor, at least part of each sensor being either housed in the blister or mounted on or integrated with an outer surface of the blister; wherein the first sensor is arranged to measure a first parameter; the second sensor is arranged to measure a second parameter; a measured value for the first parameter is dependent on a speed of the aircraft in a first direction; a measured value for the second parameter is dependent on a speed of the aircraft in a second direction; the first direction is in a plane perpendicular to an aircraft lateral axis; and the second direction is in a plane perpendicular to an aircraft roll axis.

Abstract: An apparatus comprises a composite elongate member, a channel, and a number of composite structures. The composite elongate member has a side configured for attachment to a surface of a structure. The channel is on the side and extends along a length of the composite elongate member. The number of composite structures is configured for placement in the channel and configured to attach a portion of the side of the composite elongate member to the structure. The number of composite structures has layers oriented substantially perpendicular to the surface of the structure. The number of composite structures is configured to increase a capacity of the composite elongate member to withstand forces that pull the composite elongate member away from the structure.

Abstract: A foam mount of an aircraft window has a groove to receive an electro chromic window. The foam mount is painted by placing a blank in the groove to divide the foam mount into a first section designated to face the exterior of the aircraft and an opposite second section. The groove and the first section are coated with an electric conductive paint, and the second section is covered with a decorative paint. The conductive coating on the foam mount and the conductive coating of the electrodes of the electro chromic window provide an RF shielding to prevent electronic signals from personal electronic equipment from passing through the cabin and door windows of the aircraft. A mask is also provided to coat one section of the foam mount while covering the other section.

Abstract: An equipment element for transportation means, in particular an airplane, includes, but is not limited to a retractable line, the length of which can be set using a retraction mechanism.

Abstract: A fastening element includes, but is not limited to at least one first body, at least one second body, and at least one locking device. The first body and the second body in each case on one end include, but are not limited to a pressing element for pressing an insulation package against an object. The first body and the second body movably engage each other so that the pressing elements are located at opposite ends of the fastening element. The at least one relative position of the first body to the second body may be fixed by means of the locking device. In this way effective fastening of insulation packages to objects in an aircraft cabin may be ensured without all the insulation packages having to comprise openings for accommodating fastening pins.

Abstract: Embodiments include an assembly comprising: (a) a camera support structure comprising: a masthead disposed on the distal end of a mast wherein the masthead is configured to receive an imaging element; where a proximal end of the mast rotatably engaging an azimuth-elevation joint assembly wherein the azimuth-elevation joint assembly comprises a first angular actuator of a first rotational degree-of-freedom and a second angular actuator of a second rotational degree of freedom; and (b) a camera support structure housing comprising an aperture and a hatch wherein the hatch is resiliently biased to close the aperture; and wherein the camera support structure is configured to overcome the hatch resilient bias by at least one of: the release of a pin restraining a loaded spring and a rotational actuation of the mast via at least one of the first angular actuator and the second angular actuator.

Abstract: According to one embodiment, a bracket configured to hold a pressure transducer comprises a body, a face plate, and one or more pressure fitting connectors. The body has a rear portion and a front portion that meet to form an angle less than 180 degrees. The face plate is coupled to the front portion of the body, and has a surface defining a plate aperture configured for a cable to pass through. The pressure fitting connectors are coupled to the rear portion of the body. Each pressure fitting connector is configured to receive a pressure hose.

Abstract: A potable water system capable of being drained in flight. The system provides positive separation between the potable and gray water systems. The design of the system will allow draining of components such as water tanks or interconnect lines that are below the level of the drain point. The systems will allow draining of components such as water tanks or interconnect lines that would not gravity drain due to the routing of their interconnect lines. This invention would apply to aircraft that need the capability to drain their potable water system in flight.

Abstract: The disclosure provides in one embodiment a method of insulating a structural frame member of a transport vehicle. The method comprises providing at least one flexible insulation member. The method further comprises providing at least two self-retaining foam insulation members. The method further comprises wrapping the flexible insulation member over a first end of a structural frame member of a transport vehicle and over at least portions of two sides of the structural frame member. The method further comprises positioning one self-retaining foam insulation member on each side of the wrapped structural frame member and in compression fit between each side of the wrapped structural frame member and adjacent structural frame members, such that the self-retaining foam insulation members impart one or more compression forces on the flexible insulation member to secure the flexible insulation member in place without use of any fastener device.

Abstract: Quasi-isotropic chopped prepreg is used to make parts found in aerospace vehicles. Exemplary aerospace parts that are made using quasi-isotropic chopped prepreg include aircraft window frames, wing fairing supports, flange supports, frame gussets, rudder actuator brackets, shear ties, seat pedestals, cargo floor flange supports, storage bin fittings, antenna supports, torque tube pans, handle boxes, side guide fittings, wing box covers and intercostals.

Abstract: A method for improving the conspicuity of aircraft is described that includes determining onto which exposed portions of an aircraft surface a retro-reflective material is to be placed, and attaching the retro-reflective material to the exposed portions such that an observer of the retro-reflective material is provided with an indication of a size, location, and orientation of the aircraft.

Abstract: A drainage device for letting out a fluid that is present between the exterior skin and the interior lining of an aircraft, wherein the drainage device comprises a collecting vessel and an outlet line. The collecting vessel is designed to collect the fluid that is present between the exterior skin and the interior lining and the outlet line is connected to the collecting vessel and is designed to let out the collected fluid.

Abstract: A system for single wire secondary distribution comprising a spacecraft platform; a central bus interface unit coupled to the spacecraft platform; a payload unit coupled to the central bus interface unit; and a centralized power supply for powering the central bus interface unit and the payload unit; wherein the spacecraft platform provides a command to the central bus interface unit; wherein the central bus interface unit interrupts the power to the payload unit in a manner corresponding to the commands received by the central bus interface unit; wherein the payload unit decodes the interruption to the power and executes the command from the spacecraft platform.

Abstract: A fireproof, bi-directional decompression panel includes a frame member and a pressure relief panel member that is releasably retained to the frame member to removably cover a decompression vent opening of an aircraft partition, such as a sidewall of an aircraft cargo compartment. During a decompression event, the pressure relief panel member is released bi-directionally in either of two opposing directions from the frame member when a predetermined pressure differential exists across the partition. The decompression panel assembly is fire resistant, and has reduced weight and fewer parts than prior conventional decompression panel assemblies.

Abstract: The invention is a mount for an electronic display device. The mount comprises a mount member that has a top face and a bottom face. Portions of the mount member are configured to engage portions of a mounting surface within the cockpit of an airplane. The mount also comprises a containment member spaced therefrom the mount member. A joint member is disposed in frictional contact with portions of the respective mount member and containment member. A base member, which can be configured for engagement with a portion of the electronic display device, can be connected to the joint member.

Abstract: A system and method for mounting engine control units. The engine control unit (ECU) mounting system is placed within a compartment of the light aircraft, aft of the firewall. The ECU mounting system uses a bracket that holds the electrical control units. The electrical control units are mounted through a firewall and are accessible via the adjacent compartment.

Abstract: An articulating yoke mount includes a support plate, a first bracket assembly mounted to the support plate, and a second bracket assembly spaced from the first bracket assembly. A positioning of the support plate is selectively adjustable relative to the first bracket assembly and the second bracket assembly to position the support plate at a desired viewing angle.

Abstract: The invention relates to a decompression element for pressure equalization in a cabin of an aircraft, with a decompression element frame, a flap, and a hinge element or at least one bearing element for fitting the flap to the decompression element frame. The hinge element or the bearing element can be produced from a plastics material. A decompression device for decompressing a cabin area includes a decompression device frame, a first opening which enables a flow to take place between a line of an air-conditioning system of the aircraft and the interior space of the decompression device, a second opening which enables a flow to take place between the cabin area and the interior space of the decompression device, and a third opening receiving the decompression element with the flap.

Abstract: A method of manufacturing an aircraft component such as a wing rib. The method comprises: providing a body with two or more connectors arranged in a line on the body, each connector having an arm extending from the body, a first flange positioned on a first side of the line, and a second flange positioned on a second side of the line; and attaching a separate connector to the body, the separate connector having an arm extending from the body, a first flange positioned on a first side of the line and a second flange positioned on a second side of the line.

Abstract: The method of fabricating an aircraft part comprises the steps of placing in a stack comprising a preform at least one layer of a material that presents permeability to a predetermined resin that is less than the permeability of a portion of the preform that is the closest to the layer; and placing a resin presence sensor on a side of the layer that is remote from the preform.

Abstract: A structural, energy absorbing composite element for aircraft structures includes a metallic or nonmetallic skin shell with a porous filler material insert positioned within the skin shell. The porous filler material is a material having ligaments that collapse resulting in a densification of the porous filler material in response to impact loading or a compression force sufficient to cause failure of the combined assembly.

Abstract: A communication system for supporting communications with a target market area. The system includes one or more solar-powered aircraft maintained in, or successively passing through, flight stations or flight patterns around the market area. Each of the aircraft targets limited beamwidth communication antennas on a substantial portion of the target market area. The control system is configured to fly selective flight patterns depending on the aircraft characteristics and the flight conditions. The flight patterns may emphasize high-power-generation patterns such as flying away from the sun for aircraft with wing-mounted solar cells.

Abstract: A slider apparatus integral with a slidable member and a method for integrating the slider apparatus with the slidable member. The slider apparatus integrated with the slidable member may be configured to slidably couple with and be structurally supported by a fixed structure. The slider apparatus may comprise a primary slider component made of composite material and at least one chamfered element bonded to the primary slider component. The slidable member may comprise the slider apparatus, a core assembly, a plurality of composite material plies wrapped around the slider apparatus and core assembly and cured therewith, and at least one low-friction slider shoe removably attached to the primary slider component outward of the plurality of composite material plies.

Abstract: The disclosed sensor includes a frame having a base and a plurality of arms integral with the base. The arms are biased to a relaxed position, which may be an extended position. A fuse is fastened between the arms to hold the arms in a non-relaxed position. When incorporated into an aircraft, for example, the disclosed sensor may be connected to a first panel, and a pin connected to a second panel may be positioned between the arms.

Abstract: The subject of the invention is a surround for an opening made in a panel of an aircraft, notably a fuselage panel of the aircraft. The panel comprises at least one exterior surface, the surround is fixed to the panel, forming an interface for fitting a closing-off device, and comprises at least one lip extending towards the centre of the opening. The lip supports the closing-off device and has at least one external face interposed between the external surface of the panel and the closing-off device. The surround is characterized in that it is made of at least two independent components joined together, a first component comprising the lip and a second component being fixed to the panel.

Abstract: A rod for supporting components in a fuselage cell structure, in particular produced with fibre-reinforced composite materials, of an aircraft, in particular for supporting at least one floor frame on at least one annular former and/or at least one further component of the fuselage cell structure. In accordance with the invention the rod is formed, at least in portions, with a metal foam, in particular for the absorption of crash loads. The metal foam can transform, irrespective of its inherent weight, the high mechanical loads produced in the event of an accident into work of plastic deformation at the microcavities within the metal foam. A first variant of the rod is almost completely formed by a metal foam, whereas a second embodiment comprises merely a core made of the metal foam with a relatively small diameter, which core is surrounded coaxially by a support casing and an outer sleeve.

Abstract: A fitting for trimming the horizontal stabilizer of an aircraft, made of composite material, the fitting including side walls of a torsion box as well as joining elements which join the fitting to the frames of the tail fuselage of the aircraft, the side walls being joined together by a central element which includes a first end part joined to the first side wall of the fitting, a second end part joined to the second side wall of the fitting and a central part which joins together the end parts, the fitting includes end elements which are joined to the side walls on their outer face, the fitting having, owing to its greater rigidity in response to side load and vertical load stresses which tend to close the side walls, its greater integration and the simplicity of the load path, an optimum structural behavior in response to the aircraft stresses.

Abstract: Fasteners, such as bolts, nuts and screws, rivets, pins, and retaining rings, made of a highly kinked rigid-rod polyarylene exhibiting outstanding characteristics, notably a high torque and a high tensile elongation, a measure of practical toughness.

Abstract: A foam mount of an aircraft window has a groove to receive an electro chromic window. The foam mount is painted by placing a blank in the groove to divide the foam mount into a first section designated to face the exterior of the aircraft and an opposite second section. The groove and the first section are coated with an electric conductive paint, and the second section is covered with a decorative paint. The conductive coating on the foam mount and the conductive coating of the electrodes of the electro chromic window provide an RF shielding to prevent electronic signals from personal electronic equipment from passing through the cabin and door windows of the aircraft. A mask is also provided to coat one section of the foam mount while covering the other section.

Abstract: A device for securing installed equipment in an airplane, with one or more oblong attachment rails, one or more attachment means for securing the attachment rails to an airframe structure, and one or more bracket units that can be attached to or in the attachment rails, wherein the bracket units can be attached to the built-in apparatuses to be secured.

Abstract: A method for making a window frame for installation in the exterior shell of an aircraft, which comprises at least one outer flange, an inner flange, and a vertical flange arranged perpendicular to and between these two flanges, contemplates that first a semifinished part comprising multiple, individual substructures is made, which next is inserted into a molding tool, into which, under pressure and temperature, resin is injected, and that the component made in this manner subsequently is hardened in the molding tool. The semifinished part has a layer structure, which comprises a web material, fiber bundles, or a combination of fiber bundles and web material.

Abstract: An antenna system for an airborne radar system with a dorsal unit having two opposing long sides extending in a height direction (Z) and a longitudinal direction (X), and two opposing short sides extending in a lateral direction (Y) and the height direction (Z), and an upper side opposing a bottom side each extending in the longitudinal direction (X) and the lateral direction (Y). The antenna system comprises antenna devices being interspaced and mounted in connection to one of the short sides or both the short sides and extending in the height direction (Z). Each of the antenna devices comprises a waveguide board.

Abstract: An aircraft carrying oxygen, gases, and/or fluid advancement tanks is flown to heights greater than ground level and released out to the atmosphere, or gathered in tanks contained in the fuselage. The system is regulated by the atmospheric height or by an attendant such as the pilot or automation on the aircraft. The device includes a supply of oxygen, gases, and/or fluid advancements tanks, release or capture device, hoses, hose regulators and a relay switch. The idea here is to equip all aircraft with this utility system of oxygen, gases, and/or fluid advancement tank capabilities. As each aircraft flies to its intended destination, it helps the environment by feeding oxygen, gases, and/or fluid advancements into the atmosphere to promote cleaner, clearer, better-used atmospheric layers and maintained surface viabilities.

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: An airframe attachment fitting includes a fitting base having a base attachment surface and a flange attachment surface, at least one attachment post extending from the base attachment surface of the fitting base and at least one attachment flange carried by the flange attachment surface of the fitting base. An aircraft fuselage and a method of attaching a system or subsystem component to an airframe are also disclosed.

Abstract: The invention relates to a method for installing an inertial reference unit in an aircraft, in which: a reference unit support (1) is fixed to a structural element of the aircraft; support installation angles—in heading, roll and pitch—representative of angular errors of positioning of the reference unit support relative to an aircraft coordinate system are determined, this determination being based on the measurement of coordinates of points of a previously defined reference coordinate system and of characteristic points of the reference unit support; the said support installation angles are recorded in memory means, for the purposes of subsequent correction of data measured by the inertial reference unit. Preferably the reference coordinate system used is defined by means of targets formed on the structure of a segment of the aircraft for the purposes of joining this segment with an adjacent segment.

Abstract: An aircraft cockpit that includes an information display device with a screen having a display surface and a rear surface opposite the display surface, and a cable harness connected to the screen. The rear surface includes a mechanism for retaining the cable harness substantially wound against the rear surface. The information display device is mobile within the cockpit.

Abstract: A traffic collision avoidance system device is provided. The device includes a radome having an antenna contained therein. A chassis is bonded to the radome by a layer of bonding material about the chassis periphery. A housing is provided having a substantially flat bottom portion and a wall extended about a periphery to define a interior portion. A second bonding layer disposed between the housing and the radome within the interior portion to form a seal.

Abstract: An aircraft includes a fuselage and at least one engine provided with at least one propeller and mounted at a rear part of the fuselage, on the back thereof, with the at least one engine having an axis substantially parallel to the longitudinal axis of the fuselage, where the at least one engine is mounted on the rear part of the fuselage so that the propeller lies forward of the tails, and provided at the rear part of the fuselage, symmetrically with respect to the fuselage, are removable noise masking surfaces configured to occupy either a deployed position in which the removable noise masking surfaces project laterally with respect to the rear part of the fuselage and are positioned plumb with the propeller, or a retracted position in which the removable noise masking surfaces are incorporated into the rear part of the fuselage.

Abstract: An overhead video system for an aircraft is disclosed. The overhead video system comprises a wireless overhead video unit; and at least one mounting rail detachably coupled to the wireless overhead video unit. The mounting rail provides structural support and electrical power to the wireless overhead video unit. A system in one embodiment may use mounting rails that double as power rails supplying power to the wireless overhead video unit. Video control and content streaming is accomplished over a wireless link. The power rail control may be accomplished remotely via a standard or solid state relay. Normal rail power for the rail mounted video system may come from the utility bus.

Abstract: Vehicular sensor systems are provided. The vehicular sensor systems includes a support, first, second, and third sensors, and a support actuator. The first sensor is coupled to the support and configured to rotate about a first sensor axis. The first sensor has a first field of detection with a first central axis. The second sensor is coupled to the support and configured to rotate about a second sensor axis. The second sensor has a second field of detection with a second central axis. The third sensor is coupled to the support and configured to rotate about a third sensor axis. The third sensor has a third field of detection with a third central axis. The support actuator is coupled to the support and configured to rotate the support about a support axis. The first, second, and third central axes are substantially within a plane.

Abstract: This invention relates to improving the tolerance of composite laminate structures to damage and/or delamination, resulting in weakening of the structure and/or to reducing the possibility of such damage and/or delamination. In particular, but not exclusively the invention relates to protecting the end surfaces of composite laminate structures present on aircraft from impact damage. The invention provides an aircraft component comprising a composite laminate structure, the composite laminate structure including an end surface at which a multiplicity of the layers of the laminate structure terminate, wherein the aircraft component further comprises a deformable strip mounted to protect the end surface of the composite laminate structure from direct impacts.