Abstract: A pressure bulkhead may include a bulkhead wall having a radially inner disk and a radially outer compression ring, the outer compression ring being reinforced to balance meridional and hoop stresses sustained by the bulkhead wall in response to a pressure differential across the pressure bulkhead; and the radially inner disk being unitary with the outer compression ring and being made of the same material as the outer compression ring.

Abstract: An airframe leading edge part designed to be replaceable fixed to a structural portion which during use moves through the air. The airframe leading edge part includes first and second longitudinal joint edges adapted to fit the structural portion. At least one joint is provided between the structural portion and at least one of the longitudinal joint edges. The joint is adapted to break in the event of a object strikes and deforms the airframe leading edge part during use. The joint is designed to break at beforehand determined maximum joint strength of the joint. Also a repair method for exchanging a damaged leading edge.

Abstract: A cabin space dedicated to passengers and, beneath said cabin space, an under-cabin space which extends along the longitudinal axis of said aircraft. The under-cabin space comprises, distributed along two lines parallel to the longitudinal axis of the aircraft, two sets of systems which are able to carry out functions necessary for the operation of the aircraft. The two lines of sets of systems are disposed respectively in two lateral zones of the under-cabin space which are spaced apart transversely from one another and enclose a free central zone which extends along the longitudinal axis of the aircraft. This arrangement thus eliminates any technical zone from the under-cabin space, thereby facilitating the internal layout and maintenance.

Abstract: A single, common, fuselage and wing design of an aircraft structure provides for two different aircraft models or configurations. A fuselage (12) has a center section cutout area (212). Each wing (16) has an airfoil over substantially its entire span. In one configuration (2A), a center section component (212), such as a wingbox, is inserted into the center section cutout and the wings are connected to opposing sides of the center section component by a side-of-body join. In another configuration (2B), the wings are moved inwardly, joined to the fuselage, and also joined to each other in a centerline join at the centerline (218) of the aircraft wherein a portion (16A) of the airfoil of each wing is then inside the fuselage. Different flaps (210, 220), spacers (222), and/or different engine mount locations (402, 404) may be provided for the wings for the two configurations.

Abstract: A wedge frame for an aircraft that provides tailstrike angle enhancement. The wedge frame has converging, non-parallel faceplanes that tilt a rear portion of the aircraft fuselage upward in order to prevent or reduce risk of the tail of the aircraft striking the ground during takeoff and landing. A method to prevent or reduce risk of the rear portion of an aircraft from striking the ground during takeoff and landing by using a wedge frame having converging, non-parallel faceplanes to tilt upward the rear portion of the aircraft.

Abstract: A method and system for datacasting and content management. Such a system may have, as its core, a dashboard system for managing data feeds. A dashboard system may receive data feeds from one or more associated devices, such as the hardware devices of first responders or other public safety officers, and may aggregate and prioritize them. The dashboard system may then manage, prioritize and encrypt the video, files and other data in preparation for broadcast over the television or satellite transmitter, via, for example, a television broadcasting station, and may then broadcast the video, files, or other data to a plurality of users. Alerts and notifications may be created, files attached and links to video streams distributed over this same broadcast network. The broadcasting system may be able to send multiple streams of content simultaneously, may be able to target specific users to be broadcast to, and may be able to incorporate data from public data sources, such as public security cameras.

Abstract: Provided is a joint and an aircraft structure wherein it is possible to position a member relative to a preform with high accuracy. A groove into which a plate member (30) is inserted is formed in a pi-shaped joint (20) provided on the preform (21), and the preform (21) and the plate member (30) are connected by being bonded. Moreover, a fitting shape (32A-1) into which the plate member (30) is fitted is formed on the pi-shaped joint (20) on the whole groove bottom face. Additionally, a fitting shape (32A-2) into which the plate member (30) is fitted is formed on a portion of the groove bottom face. Furthermore, fitting shapes (32B-1, 32B-2), into which the groove bottom face that is formed on the pi-shaped joint (20) is fitted, are formed on the surface of the plate material (30) that is fitted with the pi-shaped joint (20).

Abstract: An aircraft comprising a fuselage which has a central part with a cross section of constant geometry which comprises a floor. The floor comprises two lateral portions which are fixed respectively to two opposite lateral edges of the fuselage and which enclose a central portion to which they are fixed. One of the lateral floor portions is fixed to the central portion so as to allow a relative lateral movement between the two portions in the event of a modification in pressure inside the fuselage. The cross section thus deforms homogeneously when the fuselage is pressurized and the floor is not involved in maintaining the shape of the fuselage.

Abstract: A mechanical fitting for connecting structures may include a base structure and a plate member. The mechanical fitting may also include a support structure for supporting the plate member at a predetermined spacing from the base structure. The support structure may include a truss structure.

Abstract: A composite stiffener is provided with an integral conductive element extending longitudinally through an entire length of the composite stiffener to form a portion of an electrical ground/return system in a composite structure. The integral conductive element provides both structural strength and conductivity, and may be formed from graphite nanotube filaments, carbon nanofibers or nanoparticles, or a metallic filler material. The integral conductive element is disposed in a terminal portion of the composite stiffener and may include a terminal tab for connecting to the ground/return system.

Abstract: A solar power panel failure search and detect system to search and detect malfunctioning or failed sites of a solar power panel. A search unit is installed in a remotely controllable aerial vehicle. The search unit maintains a constant distance between a solar panel and a failure detector, and maintains the failure detector at an optimum angle. A control unit controls a flight path and a flight angle of the aerial vehicle and controls/regulates an angle of the failure detector, a receiver, a processor, and the search unit. The search unit has an angle sensor, the failure detector, an angle adjuster and an imaging device. The control unit has a transmitter to transmit the search result data.

Abstract: A thrust reverser torque box assembly for an aircraft engine is constructed with a torque tube having a cross section configuration tailored and conducive to carrying torsion and discrete major fittings at opposite ends of the torque tube that connect the torque tube and thrust reverser actuation and reacts loading due to reverse thrust operation to the aircraft engine fan case.

Abstract: This description relates to a strapped windshield assembly for a rotorcraft. In some implementations, the rotorcraft includes an airframe, a windshield, and a plurality of independent straps connected to the airframe and the windshield, the straps operative to move independently with respect to one another. The independent movement of the straps allow relative movement of portions of the windshield in response to a strike. In some implementations, the straps are spaced every 4-6 inches along an edge of the windshield. In some implementations, the straps are over an edge of the windshield. The straps can have a modulus of elasticity of 8-12 millions of pounds per square inch (MSI). The windshield can include polycarbonate material.

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: An aircraft rear structure that comprises a rear pressure bulkhead, and a lifting surface located at both sides of the fuselage of the aircraft. The lifting surface comprises spars extending in the longitudinal direction of the lifting surface. The pressure bulkhead is aligned with one of the spars of the lifting surface.

Abstract: Embodiments include method, systems and computer program products for route planning and management with a drone. Aspects include receiving a destination for an individual and determining multiple routes between a position of the individual and the destination. Aspects further include deploying the drone to determine safety and accessibility risks associated with the multiple routes and determining a preferred route from the multiple routes based on the safety and accessibility risks associated with the multiple routes.

Abstract: The invention is directed to methods for radio frequency spectral analysis. Accordingly, flight instructions are executed on a first UAV to fly in a first flight pattern relative to a signal source. The first UAV detects radio signal(s) from the signal source and associated signal data. Flight instructions are concurrently executed on a second UAV to fly in a second flight pattern, relative to the first flight pattern of the first UAV. The second UAV also detects radio signal(s) from the signal source and associated signal data. The stored signal data from the drones may then be processed for visualization.

Abstract: A pressure bulkhead of an aircraft with a fuselage shell and a pressure bulkhead disposed therein preferably in the rear region for forming a fuselage-internal pressure region, which pressure bulkhead is attached on the edge in the interior of the fuselage shell, wherein the pressure bulkhead has a lenticular cross-section and a sandwich construction that comprises a foam core sandwiched between two opposing exterior shells.

Abstract: A method of forming an iso-grid structure may include filling multiple pockets of the iso-grid structure with a filler material, attaching a support structure to the perimeter of the iso-grid structure, shaping the iso-grid and support structures, and removing the support structure from the iso-grid structure. The support structure may be thinned and stretched during the shaping process.

Abstract: A thin, cured gel gasket is disclosed, including methods of making the thin gel gasket and the use of the thin gel gasket in an aircraft joint. In one embodiment, the thin gel gasket has no skeleton or other structure and is comprised of only a cured polyurethane gel and has a thickness of less than about 12 mill. It is manufactured using a release film that is adapted in a number of ways to make release from the gel prior to use easier. In one method of making and using the thin gel gasket. it is applied to a joint which is subject to compression, in one embodiment, a lap joint of an aircraft fuselage.

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: 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: 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 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: 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: 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 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: 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: 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.