Abstract: A system and method determine a size and a shape for identical geodesic modules that are used to form a structure. The system and method may include analyzing input data regarding a size and a shape of the structure to be formed, and determining the size and the shape for each of the identical geodesic modules based on the size and the shape of the structure to be formed. The structure may include a framework including the identical geodesic modules. Each of the geodesic modules has a size and a shape that are the same as all of the other of the geodesic modules. A forming system and method position a framework and a covering skin of the structure in relation to a mandrel, and drill and rivet the framework to the covering skin with a plurality of operating heads.

Abstract: A plate-shaped workpiece forming method of post-machining a pocket (3) on a curved inner surface of a plate-shaped workpiece (2) in a state where the plate-shaped workpiece (2) curved by a curving machine (10) is spread flat. The method includes a curving step (A) of setting a net curve radius (R0) obtained by adding a curve radius contraction amount (R1) due to spring-in to a finished curve radius (R) of a plate-shaped workpiece (2), taking into account an amount of contraction of the curve radius of the plate-shaped workpiece (2) between before and after machining of a pocket (3) due to spring-in, and curving the plate-shaped workpiece (2) so as to achieve the net curve radius (R0); and a pocket machining step of post-machining the pocket (3) by flatly spreading the curved plate-shaped workpiece (2).

Abstract: In order to reduce the time and the cost of manufacturing an aircraft fuselage, the subject matter disclosed herein provide an aircraft fuselage frame element comprising a core provided with at least one through-opening intended for the passing of a fuselage stiffener, and further comprising, associated with each opening, a tab for the fastening of the frame element onto the fuselage stiffener, with the tab being a single piece with the core and connected to the latter by a fold that delimits the opening.

Abstract: An aircraft and method of operating the aircraft are provided. The aircraft includes a fuselage including a nose, a tail, and a hollow, elongate body extending therebetween, a wing extending laterally away from the fuselage, the wing including a leading edge in a direction of motion of the aircraft during normal flight and a trailing edge on an opposing edge of the wing, and an engine configured to drive a bladed rotatable member, the engine coupled to at least one of the wing and the fuselage. The aircraft further includes at least one of a forward chine member and an aft chine member extending from the fuselage at a point forward of the engine aftward to a point aft of the bladed rotatable member.

Abstract: An aircraft window has an inner window assembly retained on an outer window assembly by a plurality of interlocking clips and receptacles positioned around the perimeter of the window. The interlocking clips and receptacles produce a retention force that compresses a seal against an outer structural the window to seal an internal cavity between the inner and outer window assemblies.

Abstract: This stiffener is intended for a fuselage. It comprises a hollow section that can be trapezoidal, with a base attached to the fuselage or to the floor, high enough rising sides and a top side contributing to the rigidity and cohesion of the stiffener. A direct assembly with the fuselage is possible. The base is made of two edges provided one on the other or in front of the other. This rigid stiffener, in spite of its discontinuous section, can be manufactured by simple foldings of a planar metal sheet at the beginning.

Abstract: In one embodiment, a stiffener may be formed by inserting a plurality of flexible mandrels into a channel of a tool having a three-dimensional contour, placing a vacuum bag over the flexible mandrels and the tool, with the mandrels disposed between the vacuum bag and the tool, and applying vacuum pressure between the vacuum bag and the tool. A hardening substance may be inserted into each of the plurality of flexible mandrels and then may be hardened while the plurality of mandrels are inserted in the one or more channels of the tool. Finally, the mandrels may be wrapped with a stiffener material with stiffeners being formed from the stiffener material.

Abstract: A joint including first and second rib components, the first rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface; and the second rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface, wherein the abutment surfaces of the respective ribs are abutting and joined with a tension joint, and wherein the lugs are pinned to form a pinned lug joint by aligning respective holes in the plurality of lugs such that the lugs of the first and second ribs are interleaved and have one or more pins passing through the aligned lug holes. The joint may be used for attaching a wing tip device to the outboard end of an aircraft wing.

Abstract: The invention relates to a subfloor structure with an integral hull, for a rotary wing aircraft. The subfloor structure comprises an integral subfloor hull that defines in one piece, upward web portions acting as longerons and a bottom central portion offering both load bearing capabilities and aerodynamical loft features. The subfloor structure is useful for rotary wing aircrafts such as helicopters, and is e.g. made of composite and/or light alloy such as aluminum.

Abstract: A system, apparatus, and method for the measurement, collection, and analysis of radio signals are provided. A transport host device, including an unmanned aerial vehicle, can transport a scanning device into desired locations for autonomously collecting radio data for a wireless network, thereby enabling the rapid interrogation and optimization the wireless network, including in locations and spatial areas where previously known systems and methods have been impractical or impossible.

Abstract: In some embodiments, an aircraft includes a structural assembly, a skin, and a snubber. The structural assembly comprises a first rigid element and a second rigid element. The first and second rigid elements are separated from each over by a void. The skin is disposed proximate to the structural assembly and adjacent to the void such that the skin would deflect into the void in response to an impact force received by the skin. The snubber is disposed in the void between the first and second rigid elements and positioned such that, when the skin deflects in response to the impact force, the skin contacts the snubber and the snubber reduces further deflection of the skin into the void.

Abstract: A segment and a method for producing such a segment, in particular for an aircraft, having a skin field and a skin field stiffening structure. The skin field and stiffening structure are made from fiber-reinforced plastic materials. The stiffening structure is bonded to an inner surface of the skin field and comprises a multiplicity of first stiffeners and mounts which are formed integrally with the first stiffeners and extend in a transverse direction of the first stiffeners for the connection of second stiffeners to form an integral lattice structure. Reinforcement elements are provided for mechanically fixing the mounts to the skin field. Each reinforcement element has a connection section and a blocking section having an extension in a direction inclined to the connection section. The connection section penetrates the skin field and the mounts, and the blocking section is in contact with an outer surface of the skin field.

Abstract: An aircraft of which the transversal section of the fuselage is reduced optimally at the price of a reduced carrying capacity of luggage or merchandise but adapted to short- and medium-haul type routes. The fuselage has for this purpose lateral protuberances defining storage areas arranged on either side of a passenger cabin and able to house luggage and/or merchandise, and/or onboard service equipment, and/or removable fuel tanks.

Abstract: An aircraft includes a fuselage, an aircraft propulsion system including an open rotor, and a pylon mounting the propulsion system to the fuselage. The fuselage includes an acoustic panel configured to attenuate noise generated by the open rotor.

Abstract: An energy absorbing liner system and method of making it, preferably by thermoforming. A helmet has an energy absorbing inner system positioned inside the shell. The liner has thermoformed interconnected energy absorbing modules that non-destructively rebound after one or more impacts. At least some of the modules in the layer have a basal portion with upper and lower sections when viewed in relation to the wearer's head. The upper section has one or more energy absorbing units. At least some of the units are provided with a wall with a domed cap that faces the outer shell. The units at least partially cushion the blow by absorbing energy imparted by an object that impacts the outer shell. The lower comfort section has a tiered arrangement of layers. The layers are relatively compliant and thus provide a comfortable yet firm fit of the helmet upon the wearer.

Abstract: An aircraft fuselage panel system for an aircraft of the type having a tubular fuselage frame includes a plurality of generally U-shaped frame members are each adapted to receive a portion of the tubular fuselage frame therein. Each frame member includes a plurality of apertures therethrough. A plurality of metal tabs are fixed to the tubular fuselage frame and include at least one aperture therethrough axially aligned with one of the apertures of one of the frame members. A rigid panel is adapted for fixing between each metal tab and the frame members. Each panel has a plurality of apertures therethrough each axially aligned with one of the apertures of the metal tabs and the frame members. A plurality of mechanical fasteners are adapted for fixing the panel between each metal tab and one of the frame members. The panel and frame member are fixed to the fuselage frame thereby.

Abstract: An aircraft fuselage structure having a first fuselage barrel section and a second fuselage section barrel which are joined by tension fasteners extending through frame holes. A shank diameter of the fasteners is smaller than a respective frame hole diameter. A first positive locking element and a second positive locking element is provided forming a form-fit area with the first positive locking element in the circumferential direction. A method for producing such an aircraft fuselage section is also provided.

Abstract: An aircraft includes a fuselage including a plurality of frame members disposed at predetermined intervals in a longitudinal direction of the fuselage and a plurality of stringers extending substantially linearly in the longitudinal direction. The fuselage defines an aircraft interior. A compartment is located in the interior of the fuselage. The compartment defines an interior area. A first one window assembly is mounted to an upper portion of the fuselage for introducing daylight into the interior area. The first window assembly is flanked by adjacent frame members of the plurality of frame members and adjacent stringers of the plurality of stringers. The first window assembly includes a window pane, an inner cover and a retainer. The inner cover introduces daylight from the window pane into the interior area. The retainer secures the window pane and the inner cover to the fuselage.

Abstract: In one embodiment, a controller instructs an unmanned aerial vehicle (UAV) docked to a landing perch to perform a pre-flight test operation of a pre-flight test routine. The controller receives sensor data associated with the pre-flight test operation from one or more force sensors of the landing perch, in response to the UAV performing the pre-flight test operation. The controller determines whether the sensor data associated with the pre-flight test operation is within an acceptable range. The controller causes the UAV to launch from the landing perch based in part on a determination that UAV has passed the pre-flight test routine.

Abstract: A fuselage for an airplane including a frame comprising an upper truss and a lower truss extending from a front end of the fuselage towards the rear end of the fuselage, wherein the lower truss comprises one or more forward box beams, a plurality of support rings attached to the upper truss and lower truss, a front bulkhead connected to a first end of the upper truss and lower truss, a main bulkhead connected to the upper truss and lower truss, a pressure vessel adapted to fit within the frame between the front bulkhead and main bulkhead, and a skin adapted to fit over the frame.

Abstract: A pressurized aircraft fuselage includes a pressure bulkhead installed on a fuselage structure, which forms a barrier between an internal pressurized cabin area and an outside area. The edge of the pressure bulkhead is circumferentially attached to the fuselage structure. In particular, at least one clamping element is arranged inside a mounting bracket having an open trapezoidal-shaped channel formed by a base section of the mounting bracket and non-parallel sides of the mounting bracket. An edge of the pressure bulkhead is inserted in the trapezoidal shaped mounting bracket, in order to form a clamping connection for the pressure bulkhead towards the fuselage structure.

Abstract: Embodiments of the present disclosure relate generally to systems and methods for manufacturing an airfoil component. The system can include: a geometrical mold; an elongated flexible sleeve having a closed-off interior and positioned within the geometrical mold, wherein the elongated flexible sleeve is further positioned to have a desired geometry; an infusing channel in fluid communication with the closed-off interior of the elongated flexible sleeve and configured to communicate a resinous material thereto; a vacuum channel in fluid communication with the closed-off interior of the elongated flexible sleeve and configured to vacuum seal the closed-off interior of the elongated flexible sleeve; and a glass fiber layer positioned within the closed-off interior of the elongated flexible sleeve.

Abstract: A cargo beam assembly for an aircraft including a carbon fiber reinforced polymer (CFRP) cargo beam and a plurality of CFRP stanchions and CFRP c-splice plates each connected to the CFRP cargo beam by overlapping CFRP plies. The flanges of the cargo beam assembly may all be facing a single direction. The components of the assembly may all be formed with CFRP plies configured in a traditional and non-traditional layup. The CFRP stanchions and CFRP c-splice plates are configured to connect the cargo beam assembly to a keel frame of an aircraft. The upper flange of the CFRP cargo beam may include a pad up above each CFRP stanchion connected to the CFRP cargo beam. The interface between each CFRP stanchion and the CFRP cargo beam may be a flange radius that includes a ramped pad up. Darting may provide load transfer between a CFRP stanchion and the CFRP cargo beam.

Abstract: A computer-implemented method of communicating with an unmanned aerial vehicle includes transmitting a first message via a communications transmitter of a lighting assembly for receipt by an unmanned aerial vehicle. The first message includes an identifier associated with the lighting assembly, and the lighting assembly is located within a proximity of a roadway. The method also includes receiving a second message from the unmanned aerial vehicle via a communications receiver of the lighting assembly. The second message includes an identifier associated with the unmanned aerial vehicle. The method further includes transmitting a third message via the communications transmitter of the lighting assembly for receipt by the unmanned aerial vehicle. The third message includes an indication of an altitude at which the unmanned aerial vehicle should fly.

Abstract: A wind turbine blade has upper and lower shell members with a respective spar cap configured on an internal face of the shell members. A shear web extends between the spar caps along a longitudinal length of the blade. A connection assembly is configured between the transverse ends of the shear web and the spar caps and includes a channel structure configured on the spar cap. The channel structure includes side walls that extend from the spar cap along the longitudinal sides of the shear web. A pliant actuation line is attached between the side walls of the channel structure and bond paste is deposited in the channel structure. Movement of the transverse end of the shear web into the channel structure results in the actuation line pulling the side walls of the channel structure against the longitudinal sides of the shear web.

Abstract: A joining structure for an interior panel for an aircraft includes two interior panels, each provided with a corner portion formed on an internal-side surface plate by an edge of an end portion of an external-side surface plate and an edge of an end portion of an internal-side surface plate being attached, the corner portion extending in the direction the edges extend. Strip-shaped connection pieces are provided at the corner portion and are formed across an entire length of the corner portion by a portion, with gaps between the strip-shaped connection pieces. The two interior panels are joined when brought together, with the connection pieces of the two interior panels passing through the gaps between the connection pieces of the other interior panels and being adhered to the external-side surface plate of the other interior panels by an adhesive.

Abstract: A joint assembly is that includes a first component and a second component that includes a first portion and a plurality of flexible members extending therefrom for coupling the second component to the first component. The plurality of flexible members are preloaded in a predetermined direction and are configured to flex in a direction opposite to the predetermined direction when coupling the second component to the first component.

Abstract: A joint comprising first and second rib components, the first rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface; and the second rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface, wherein the abutment surfaces of the respective ribs are abutting and joined with a tension joint, and wherein the lugs are pinned to form a pinned lug joint by aligning respective holes in the plurality of lugs such that the lugs of the first and second ribs are interleaved and have one or more pins passing through the aligned lug holes. The joint may be used for attaching a wing tip device to the outboard end of an aircraft wing.

Abstract: The fuselage of an aircraft comprises a floor structure, a roof structure, a first lateral side structure, a second lateral side structure, and a middle structure. The floor structure, the roof structure, the first lateral side structure, and the second lateral side structure define a fuselage space between them. The middle structure spans at least part way between the floor structure and the roof structure, and runs between the first lateral side structure and the second lateral side structure such that the middle structure partitions the fuselage space into an occupant space and a cargo space. A seat for a pilot is disposed in the occupant space lateral to a portion of the middle structure and a portion of the cargo space.

Abstract: An all-composite assembly such as a composite laminate aircraft empennage has vertical and horizontal stabilizers with differing sets of interlaminar fracture toughnesses and differing stiffnesses to improve flight characteristics. Composite laminate skins are bonded to unitized and stiffened understructure to reduce weight and improve damage containment.

Abstract: In accordance with the present invention an aircraft stringerless fuselage structure is provided comprising an impact compliant outer skin having a plurality of resin impregnated skin fibers forming an outer skin surface, an inner stringerless skin surface, and a skin thickness. A plurality of stiffeners is included, each comprising a plurality of resin impregnated stiffener fibers integrated into the inner stringerless skin structure. The plurality of resin impregnated skin fibers are not aligned with the plurality of resin impregnated stiffener fibers.

Abstract: Internal shield in the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it; the rear fuselage having at least a vertical symmetry plane; the rear fuselage being made of a composite material; the internal shield being located in said vertical symmetry plane and extended in an area that covers the possible trajectories of a set of pre-defined fragments detached from one of said engines in a failure event that would impact on critical elements of the opposite engine; the internal shield having a flat shape and an energy absorption capability that allows stopping said fragments. The invention also refers to a method for determining the area of an internal shield and to an aircraft having said internal shield.

Abstract: A toilet arrangement for a vehicle includes a first toilet compartment, an adjacent second toilet compartment and a partition wall situated between the first toilet compartment and the second toilet compartment, wherein the partition wall is movably supported and designed for being transferred into an open position, in which the partition between the first toilet compartment and the second toilet compartment is removed. This makes it possible to convert two relatively small toilet compartments into a larger toilet compartment that is suitable for use by persons with limited mobility.

Abstract: A composite sandwich structure comprises a core sandwiched between composite laminate facesheets. The core includes a plurality of core sections spliced together at joints that incorporate integral features for arresting the propagation of irregularities in the facesheets.

Abstract: Anisotropic pressure panels are disclosed. The pressure panels include at least two distinct regions, with one region yielding to lateral deformation more than at least one other region. The regions each independently may include a plurality of beads, such beads optionally integrally formed in the body of the pressure panel. In aerospace applications, the pressure panel may be coupled to load-bearing structures, such as wings, and may at least partially define a wheel well.

Abstract: A modular utility cart comprising a body defining a door opening; wheels attached to a lower portion of the body for supporting the body; and a door operatively attached to the body and adapted to mate with the door opening, wherein the body is adapted to receive a utility module thereto is provided. A method of assembling a modular utility cart is also provided. A kit of utility cart and utility module(s) is equally provided herein.

Abstract: A shell component for an aircraft or spacecraft. The shell component includes a skin panel, a plurality of stringers which are arranged on the skin panel, a former which includes a fiber composite material and is arranged over the stringers so as to cross the stringers, and a former connection structure which includes a ductile material and a plurality of foot portions fixed to the skin panel. The foot portions each transition integrally into a shoulder portion fixed to the former over an associated fixing span, the fixing spans associated with the foot portions extending along the former substantially continuously over the stringers.

Abstract: Apparatus and methods provide for the reinforcement of various components of an aircraft utilizing vertically-oriented circumferential stringers. According to embodiments described herein, barrel skin of an aircraft fuselage may be reinforced using stringers that are vertically-oriented and circumferential. According to additional embodiments, the wing stringers of a wing can be aligned with circumferential stringers. According to further embodiments, the wing may also have one or more wing spars having an elliptical aperture. The shape of the elliptical may be configured for attachment to a fuselage so that an outer surface of the aperture is disposed proximate to an inner surface of the fuselage.

Abstract: A lightweight structure at least sectionally composed of a plurality of connected mosaic elements and/or skin mosaic elements. The lightweight structure allows an essentially load-appropriate arrangement of the mosaic elements and/or the skin mosaic elements including the optional skin. The lightweight structure requires a significantly reduced number of connecting elements, such that the assembly effort can be reduced and an additional weight reduction can be achieved. Also, two variations of a method for manufacturing a lightweight structure are provided. Large-format lightweight structures such as, for example, an aircraft fuselage cell or partial shells thereof can also be manufactured in a reliable and dimensionally accurate fashion because only mosaic elements and skin mosaic elements, with relatively small dimensions, need to be handled.

Abstract: A vibration isolation assembly for an aerodynamic object comprises a viscoelastic inner layer disposed on the aerodynamic object and being configured to attenuate vibration. The vibration isolation assembly further comprises a rigid or stiff outer layer disposed on an inner layer. The vibration isolation assembly may attenuate the transmission of aerodynamically-induced vibration to components contained or mounted to the aerodynamic object.

Abstract: An assembly of longitudinal structural stiffeners for an aircraft including, in a front portion of the fuselage, a windscreen that is slightly recessed relative to the airplane nose, and a fuselage portion extending in alignment with the airplane nose up to the base of the windscreen. The stiffeners include a bending-resistance main plane and are arranged under the flap and connected to the fuselage along a force transfer line. For one or more of the stiffeners, the bending resistance main plane substantially coincides, at at least a certain number of points of the fuselage force transfer line, with the plane predetermined by the local normal to the fuselage surface and the longitudinal axis of the airplane. A method is also provided for calculating the shape of the stiffeners.

Abstract: An aircraft capable of carrying passengers and cargo includes a fuselage, having a crown section and a keel, a first passenger cabin, having a first floor, located in a forward portion the fuselage, and a first cargo deck, located below at least a portion of the first passenger cabin. A split level cabin is located in an aft portion of the fuselage, the split level cabin including an upper second cabin having a second floor above the level of the first floor, and a lower third cabin beneath the upper second cabin and having a third floor below the level of the first floor. A second cargo deck is located in the aft portion of the fuselage and beneath at least a portion of the lower third cabin. The crown section has a substantially constant cross-sectional shape fore-to-aft above the first passenger cabin and the split level cabin, and the keel below the second cargo deck is lowered compared to the keel below the first cargo deck.

Abstract: A curved composite aircraft frame comprises a multi-ply composite laminate having a generally Z-shaped cross section. At least certain of the laminate plies include unidirectional reinforcing fibers that are substantially tangent at substantially all points along the curvature of the frame.

Abstract: A vortex generation device for reducing drag on an upswept aircraft fuselage afterbody and including a vortex generator vane that extends longitudinally from along an outer mold line of the fuselage of an aircraft adjacent an upswept afterbody of the fuselage and that is configured and positioned to reduce drag on an upswept aircraft fuselage afterbody by developing vortices that counteract vortices generated along such an upswept fuselage afterbody. The vane is disposed aft of a side paratrooper jump door of the aircraft fuselage and has a spine and leading end that are faired smoothly into the mold line of the fuselage.

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 pressure bulkhead made of fiber composite material for an aircraft fuselage for the pressure-tight axial closure of a fuselage region configured to be put under internal pressure. The bulkhead comprises a first area element, at least one second area element and a plurality of core elements. The first area element has a plurality of receptacles. Each receptacle is configured to receive a core element. The core elements are received in the receptacles between surfaces facing one another of the first area element and of the at least one second area element. The surfaces facing one another of the first area element and of the at least one second area element are connected to one another in regions without core elements.

Abstract: In conventional aircraft cargo compartments panels or similar flat floor elements are fastened to floor beams or similar supporting elements that are installed in the body of the aircraft. Subsequently functional units such as roller elements, latches or PDUs are mounted and connected to one another by way of appropriate control conductors. It is proposed to fasten the floor elements permanently to the supporting beams so as to form prefabricated floor modules and to install these floor modules in the aircraft.

Abstract: The invention provides an arrangement and methods for thermally insulating aircraft, particularly but not exclusively for when the aircraft is operating in extremely hot or cold conditions, and describes an aircraft skin construction including a foam-stiffened CFC sandwich panel forming part of the aircraft outer skin mounted to an underlying load bearing aircraft structure, wherein the panel at the mounting to the structure includes two outer layers of CFC material with an inner layer of foam material sandwiched therebetween.

Abstract: A rotary wing aircraft airframe (2) with a longitudinal axis comprising: a subfloor structure (15) for supporting cabin floor panels (13) and/or at least one fuel tank bladder (12). Said subfloor structure (15) has a bottom shell (16), longitudinal support beams (21), ribs (20), main frames (23) and floor panels (13). The bottom shell (16) has a flat shell portion (17) and two lateral shell portions (18) extending integrally from said flat shell portion (17) along its longitudinally oriented sides and being curved towards respective front edges of said ribs (20) and main frames (23). The longitudinal support beams (21) are provided with attachments for the floor panels (13), the longitudinal support beams (21) are attached at least partially to the ribs (20) and/or the main frames (23) and the longitudinal support beams (21) are featuring along at least ? of their longitudinal extension a height 2 to 20 times smaller than any distances of any of the floor panels (13) to the bottom shell (16).

Abstract: A fuselage panel made of composite material having a skin with an opening, at least part of the contour of which is reinforced by an integrated reinforcement made of composite material. The fuselage panel includes at least one liner made of composite material which is attached to and superposed on the reinforced skin portion and participates at least partially in defining the contour of the opening, the panel additionally including consolidating members, each passing at least partially through the liner and at least partially through the reinforced skin portion.