Abstract: Vertical short takeoff and landing (VSTOL) aircraft include primary airfoils extending outwardly from a forward region of the aircraft fuselage, and secondary empennage airfoils extending outwardly from an aft region of the aircraft fuselage so as to be separated from the forward primary airfoils and thereby define a space therebetween which accommodates non-cyclic controllable propellers operably driven by a respective engine of a propulsion unit. The propulsion units are mounted for pivotal movement within the defined space between the primary airfoil and the secondary empennage airfoils so as to achieve a first operational position wherein the thrust line of the propellers is orientated substantially parallel to the longitudinal axis of the fuselage and a second operational position wherein the thrust line of the propellers is oriented substantially perpendicular to the longitudinal axis of the aircraft. The propulsion units may be mounted aft of the aircraft center of gravity (CG).

Abstract: An aircraft comprises a hydrogen-fuelled propulsion system, a plurality of like generally cylindrical hydrogen storage tanks and a conveying system arranged to convey hydrogen from the hydrogen storage tanks to the hydrogen-fuelled propulsion system. The aircraft further comprises a fuselage having a cargo bay (502) including one or more (510A-G) of the plurality of hydrogen storage tanks, the longitudinal axes (511A-G) of the one or more hydrogen storage tanks within the cargo bay extending parallel to the longitudinal axis (501) of the fuselage and lying in one or more planes (595, 597) extending across the width dimension of the cargo bay. The hydrogen storage tanks within the cargo bay have a common aspect ratio R in the range 4.2?R?25.7, allowing the volume of space with the cargo bay occupied by stored hydrogen to be maximised or approximately maximised.

Abstract: Provided are methods of forming stiffened stringer panels with integrated plank structures. A skin member having an inner surface is provided. A plank is positioned onto the inner surface of the skin member. The plank extends from a first side to a second side, and each laminate ply of the set of layered laminate plies is sized to form a geometric profile for each of the first side and the second side. Each laminate ply of the set of layered laminate plies is arranged to extend from the first side to the second side. A stringer is placed onto a support tool. The support tool, and the stringer thereon, is positioned upon an uppermost laminate ply of the set of layered laminate plies. The skin member, the plank, and the stringer are joined.

Abstract: Image acquisition and analysis systems for efficiently generating high resolution geo-referenced spectral imagery of a region of interest. In some examples, aerial spectral imaging systems for remote sensing of a geographic region, such as a vegetative landscape are disclosed for monitoring the development and health of the vegetative landscape. In some examples photogrammetry processes are applied to a first set of image frames captured with a first image sensor having a first field of view to generate external orientation data and surface elevation data and the generated external orientation data is translated into external orientation data for other image sensors co-located on the same apparatus for generating geo-referenced images of images captured by the one or more other image sensors.

Abstract: Provided are stiffened stringer panels with integrated plank structures. An example composite panel comprises a skin member having an inner surface, and a plank on the inner surface. The plank comprises a set of layered laminate plies and extends from a first side to a second side. Each laminate ply of the set of layered laminate plies is sized to form a desired geometric profile for each of the first side and the second side. The composite panel further comprises a stringer including a cap portion that spans from the first side of the plank to the second side of the plank to form a first flange portion and a second flange portion, respectively, on the inner surface of the skin member. Base segments of the cap portion conform to the desired geometric profile of respective first and second sides of the plank.

Abstract: A method is proposed for installing system components in a portion of an aircraft fuselage. The method provides at least one planar structural arrangement to be secured on or in the aircraft fuselage, secures system components on the structural arrangement, couples system lines to the system components and arranges the system lines on the structural arrangement. The method includes positioning of the structural arrangement with the system components and system lines arranged thereon at a designated installation location of the structural arrangement, and mechanical coupling of the structural arrangement to the aircraft fuselage.

Abstract: Fuselage sections having tapered wing rib interfaces are disclosed. A disclosed example apparatus includes a rib associated with a fuselage section, and a wing interface surface defined by the rib, where the wing interface surface is tapered relative to a longitudinal axis of the fuselage section from an aft end of the fuselage section to a fore end of the fuselage section.

Abstract: The present disclosure corresponds to a floating floor attachment device connecting a flooring panel to a structural floor comprising a floor puck fixed to the structural floor and a puck housing connected to the flooring panel. The puck housing has a receptacle connected to the floor puck, wherein the receptacle forms with the floor puck a gap, which allows the floor puck to move within the receptacle. Additionally, the floating floor attachment device includes a gap control media, which is connected between the floor puck and the receptacle, wherein the gap control media allows aligning the floor puck with respect to the puck housing during non-load conditions and provide resistance to displacement to the floor puck during load conditions.

Abstract: An unmanned aerial vehicle (UAV) includes a vehicle body and a multi-ocular imaging assembly. The multi-ocular imaging assembly includes at least two imaging devices disposed in and fixed to the vehicle body.

Abstract: This disclosure describes an unmanned aerial vehicle (“UAV”) configured to autonomously deliver items of inventory to various destinations. The UAV may receive inventory information and a destination location and autonomously retrieve the inventory from a location within a materials handling facility, compute a route from the materials handling facility to a destination and travel to the destination to deliver the inventory.

Abstract: Disclosed herein is a method of repairing damage to a fuselage barrel, having a one-piece construction, of an aircraft. The method includes determining at least a first virtual splice line and a second virtual splice line along the fuselage barrel in a direction parallel to a longitudinal axis of the fuselage barrel. The method also includes detecting damage in a first section of the fuselage barrel between the first virtual splice line and the second virtual splice line. The method further includes cutting through the fuselage barrel along the first virtual splice line and the second virtual splice line to physically separate the first section from a main section of the fuselage barrel. The method also includes removing the first section from the main section of the fuselage barrel, and splicing a new section to the main section of the fuselage barrel in place of the first section.

Abstract: A flying device includes a propulsion unit, a restrictor and a releaser. The propulsion unit flies the flying device in air. The restrictor restricts the propulsion unit in an open state from rotating more than a predetermined angle during flight of the flying device, the propulsion unit in the open state being rotated from a closed state by the predetermined angle. The releaser releases a restriction by the restrictor.

Abstract: A composite article including fiber tows and a network including material drawn or pulled between the fiber tows. The network forms a physical barrier reducing propagation of cracks in the composite article. Exemplary structures described herein are the first to use a novel cellular architecture to toughen resin infused composites and create a continuous through thickness reinforcement that does not induce fiber breakage.

Abstract: The present disclosure provides an unmanned aerial vehicle (UAV). The UAV includes a main body; an inertial measurement unit (IMU) disposed in the main body; a mounting bracket for fixing the IMU; and a circuit board fixedly disposed at the main body and integrated with a plurality of functional modules. The IMU is fixed on the circuit board through the mounting bracket.

Abstract: An air input structure includes an air input lip and a front reinforcement frame placed inside the air input lip. The front part of the air input lip has a plurality of segments distributed angularly along the leading edge of the air input lip, two adjacent segments being separated by an intermediate part having an excess thickness. Each segment has four edges, each having an excess thickness relative to the rest of the segment.

Abstract: A method for joining two aircraft structural parts by a bolted or riveted joint and for preventing cracks at said joint includes providing a first metallic aircraft structural part and a second aircraft structural part, wherein the first aircraft structural part includes a first joint region and a second aircraft structural part includes a second joint region. Furthermore, the method includes inducing compressive residual stresses in a first area of the first joint region for preventing cracks by applying parallel crack retarding regions formed as stripes in the first area, drilling fastener holes in the first and second areas of the first. Finally, the method includes a step of fastening together the first and second aircraft structural parts at the first and second joint regions by a bolted or riveted joint.

Abstract: The present disclosure provides various embodiments of a multicopter-assisted launch and retrieval system generally including: (1) a multi-rotor modular multicopter attachable to (and detachable from) a fixed-wing aircraft to facilitate launch of the fixed-wing aircraft into wing-borne flight; (2) a storage and launch system usable to store the modular multicopter and to facilitate launch of the fixed-wing aircraft into wing-borne flight; and (3) an anchor system usable (along with the multicopter and a flexible capture member) to retrieve the fixed-wing aircraft from wing-borne flight.

Abstract: An aerial vehicle having a single wing is configured for vertical-flight and forward-flight operations. The wing has a substantially high aspect ratio. The aerial vehicle includes tilt motor assemblies disposed at a forward end and an aft end of a fuselage. The tilt motor assemblies are configured to orient motors and rotors vertically, horizontally, or at any angle between vertical and horizontal. A pair of parallel booms are mounted beneath the wing on either side of the fuselage. Each of the booms has at least one vertically oriented motor and rotor associated therewith, and a vertical fin extending thereunder. Additionally, a forward tilt motor assembly includes a rotatable extension that is deployed when the motor assembly is configured for vertical flight, enabling the aerial vehicle to land on the vertical fins and the landing rotatable extension.

Abstract: An aircraft propelled by a turbojet having contrarotating fans, the turbojet being incorporated at the rear of a fuselage of the aircraft and in line therewith and including two gas generators that feed a working turbine having two contrarotating turbine rotors for driving two fans arranged downstream from the gas generators, and distinct air intakes for feeding each gas generator, the air intakes being connected to the fuselage of the aircraft so as to take in at least a portion of the boundary layer formed around the fuselage of the aircraft.

Abstract: A new and improved system for interconnecting components in a vehicle body structure, and especially for interconnecting fiber-reinforced composite components in a fuselage structure of an aircraft. The system includes: a first adapter member having a first mating portion that is adhesively bonded with a profile of a first component of the structure in more than one plane, and a first attachment portion connected to the first mating portion; a second adapter member having a second mating portion that is adhesively bonded with a profile of a second component of the structure in more than one plane, and a second attachment portion connected to the second mating portion; and a connector member to securely interconnect the first and second attachment portions of the first and second adapter members.

Abstract: Composite layup tools for aircraft fuselage barrels, methods of assembling the layup tools, and aircraft fuselage barrels formed utilizing the layup tools are disclosed herein. A method of assembling the layup tools includes aligning an adaptor mating surface of a splice adaptor with a mandrel mating surface of a layup mandrel and initially attaching the splice adaptor to the layup mandrel at an initial attachment point. The methods further include attaching a lower lobe of the splice adaptor to a lower lobe of the layup mandrel. A method of forming a fuselage barrel assembly includes providing two fuselage barrel sections and a splice ring, aligning the two fuselage barrel sections, locating the splice ring within the two fuselage barrel sections, and attaching both fuselage barrel sections to the splice ring. The systems include a layup tool that is formed using the methods.

Abstract: The nose section for a flying machine according to the invention comprises an enclosure delimiting a nose cone extending along a longitudinal axis (A-A?), the enclosure delimiting a window, and a glass closing the window extending transversely relative to the longitudinal axis (A-A?). The nose section includes an optical sensor, in particular a camera, positioned in the enclosure behind the glass. The enclosure defines a recess, the window covered by the glass being at least partially positioned in the recess.

Abstract: An exhaust system for an aircraft includes an exhaust duct configured to be inserted within a plurality of leaf springs of an aircraft. The exhaust duct is configured to be in fluid communication with the auxiliary power unit for conveying exhaust from the auxiliary power unit to an exhaust exit, the exhaust duct including at least one exhaust bracket for movably mounting the exhaust duct to an airframe. An alignment system is configured to be operatively connected to the exhaust duct.

Abstract: A brake system comprises an inboard brake and an outboard brake. A primary control channel includes a primary outboard (POB) channel coupled to the outboard brake. The primary control channel includes a primary inboard (PIB) channel coupled to the inboard brake. A secondary control channel includes a secondary outboard (SOB) channel coupled to the outboard brake. The secondary control channel includes a secondary inboard (SIB) channel coupled to the inboard brake. The primary control channel is in communication with the secondary control channel.

Abstract: An aircraft rear structure comprising a substantially flat rear pressure bulkhead, with a first side and a second side, opposite to the first side. The aircraft rear structure also comprises a horizontal stabilizer and a vertical stabilizer which in turn comprises a first spar and a second spar. The first spar is attached to a first attachment zone of the second side of the rear pressure bulkhead via first attaching elements, and the second spar is attached to a second attachment zone of the second side of the rear pressure bulkhead via second attaching elements. The second attachment zone being different from the first attachment zone.

Abstract: Method and apparatus for aligning fastener holes of two components. An alignment fixture includes two mating fixtures. Each mating fixture includes a reference plate that is aligned to the fastener holes of one of the components. Each mating fixture also includes an alignment device. The alignment devices can be aligned with the respective reference plates such that the alignment between the reference plates and the fastener holes are transferred to the alignment devices. Once aligned, the alignment devices can be temporarily attached to the respective components at locations away from the fastener holes. The reference plates can then be removed. Thereafter, the components can be brought together such that mating features on the alignment devices engage. Engagement of the mating features aligns the two components such that the fastener holes on the components are aligned.

Abstract: A system and method for enhancing distribution logistics and surveillance ranges with unmanned aerial vehicles (UAV) and at least one dock in a dock network. The UAV remains in communication with the dock for enhancing distribution logistics of at least one package and increasing the range of surveillance for the unmanned aerial vehicle. From the dock, the UAV delivers the package to a destination point, obtains the package from a pick up point, recharges the unmanned aerial vehicle throughout the network of docks, and increases the range of distribution and surveillance. A logistics software controls the delivery and surveillance. A wireless communication device enables communication between the UAV and the dock. Light indicators indicate status of the package and the operational status of the UAV. A camera captures an image of the package in the dock. A motion detector detects the UAV for regulating access for loading/unloading and docking.

Abstract: An elongated structure comprising a web extending along a length of the elongated structure and a flange comprising a first flange portion, the first flange portion extending away from an area of the web. The first flange portion comprises a variable width along at least a portion of the length of the elongated structure. The first flange portion of the elongated structure may comprise the variable width the length of the elongate structure. The first flange portion may comprise a constant width along at least a portion of the length of the elongated structure. The elongated structure may further comprise a second flange portion. The second flange portion may comprise a variable width along at least a portion of the length of the elongate structure. The first flange portion may comprise a first top flange portion.

Abstract: An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

Abstract: Aerial vehicles may include one or more directional sensors embedded into wings, rudders, ailerons, flaps or other control surfaces. When the aerial vehicles are operating in modes that do not require the use of such surfaces, a surface having a directional sensor embedded therein may be repositioned or reoriented to align the directional sensor toward an area or axis of interest, and information may be gathered from the area or axis of interest using the directional sensor. One or more safety lights, running lights or other illuminators may cast light of a desired color, frequency or wavelength toward the area or axis of interest. The directional sensors may include cameras, radar or laser sensors, or any other reorientable sensors.

Abstract: Technology for securing a line, such as a fiber optic line, to a structure, such as a utility pole. In one aspect, a clamp is provided. The clamp includes a body, a first nub located at a first position on the body, and a first receptacle located at a second position on the body, wherein the first receptacle is connectable with a second nub that is secured to a pole-mount, and the first nub is connectable with a second receptacle that is secured to an aerial drone.

Abstract: Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.

Abstract: A remotely controlled or autonomously controlled UAV is disclosed. The UAV has both wings and a deployable parachute to enable both fixed wing flight and paraglider flight. The UAV can fly at a higher speed to a mission area as a fixed wing craft, and loiter over the area as a powered paraglider. In some embodiments, the wings are jettisoned over the mission area and the UAV configured as a powered paraglider completes its mission. In other embodiments the UAV flies to the mission area as a fixed wing craft, deploys the parachute to loiter as a powered paraglider and then jettisons the parachute to fly under a fixed wing back to a base. The former embodiment cannot fly back to a base, they may be used to carry and deploy bombs or grenades, while the latter may be used for surveillance, deliver supplies or the like.

Abstract: Improved methods, systems and apparatus for storing and repairing multimedia files are provided that overcome the limitations of existing multimedia file repair technologies. Backup copies of the multimedia container information associated with given multimedia content data are stored, along with the multimedia content data, on an external storage detachably coupled to a recording device. A primary copy of the multimedia container information is stored on an internal storage associated with the recording device. The recording of the primary container information and the content data is performed in real-time or nearly real-time as the content data is captured by the recording device. In the case of an abnormal event (e.g., battery failure, disconnect of storage media), container information may be selected from the primary copy or the backup copies of the container information, thereby increasing the likelihood that the container file can be successfully repaired or regenerated.

Abstract: A method for acquiring images of a photographic target from arbitrary perspectives with an unmanned aerial vehicle (UAV) equipped with at least one image acquisition device having a fixed acquisition direction with respect to the vehicle, said UAV having automatic navigation means allowing to reach an arbitrary location and automatic attitude control means allowing to transiently reach an arbitrary orientation in space, said photographic target being outside the current field of view of the acquisition device while the UAV flies along a predefined flying path, this method comprising: computing a target UAV position and an orientation in space required to acquire a desired image from a set of parameters, navigating to said target UAV position, modifying an attitude of the UAV in order to modify the acquisition direction to point toward the photographic target, acquiring images, and starting a recovery phase by controlling the UAV back to cruise attitude and navigate back along the predefined flying path.

Abstract: A remotely controlled UAV is disclosed. The UAV includes a parachute, with a cylindrical power and control module suspended vertically below the parachute. In one embodiment, a propulsion source is mounted on top of the power and control module with control lines connected to the module below the propulsion source, and in another embodiment the power and control module is suspended from a point above a propulsion source. The UAV may be flown under a parachute and guided by remote control, or the control module (fuselage) may be released from the parachute and extendable fixed wings deployed to enable the UAV to be flown as a fixed wing vehicle.

Abstract: An aircraft comprising a wing box and a fuselage provided with a connecting device configured to be connected to the wing box and to transmit thereto stresses undergone by the fuselage during maneuvers of the aircraft are provided. The connecting device is formed by a keel beam and a keel beam panel connected to the beam via a connecting portion of the beam, that is moreover provided with a main portion extending in a first, generally longitudinal direction and a transfer portion extending in a second direction different from the first direction and configured to be connected to the box. The main, transfer and connecting portions are configured to direct a major part of the stresses received by the beam in the second direction and transmit said major part of the stresses to the box by compression.

Abstract: A method and apparatus for managing a recreational water area. A recreational water area management system comprises a water area manager. The water area manager is configured to receive information about a recreational water area from a group of autonomous vehicles, analyze the information to identify an event, and coordinate the group of autonomous vehicles to perform a mission in the recreational water area based on the event.

Abstract: A fuselage of a fiber-reinforced composite material for an aircraft with a skin and with a multiplicity of circumferential stiffeners and only a small number of longitudinal stiffeners, the skin having a multiplicity of local reinforcements.

Abstract: An aircraft comprising a front beam having stiffeners and a front lower fuselage section having stiffeners, each stiffener comprising a core and at least one bearing surface. Each stiffener of the front beam is connected to a stiffener of the lower fuselage section by at least one batten which abuts against the bearing surfaces of the stiffeners. A sealed wall is arranged in a transverse plane which corresponds approximately to the connection plane between the front beam and the front lower fuselage section. The sealed wall includes cut-outs in order to allow the stiffeners and the battens to pass.

Abstract: Systems and methods are provided for a wiring harness for an aerial vehicle. A wing of the aerial vehicle comprises a pocket for insertion of the wiring harness. The wiring harness provides wiring and associated connections capable to attach to and power various components.

Abstract: Self-aligning fitting assemblies and systems and methods including the same are disclosed herein. The self-aligning fitting assemblies include a barrel-side fitting that includes a plurality of barrel-side attachment holes and a floor-side fitting that includes a plurality of floor-side attachment holes. The self-aligning fitting assemblies also include an alignment pin recess and a fitting alignment recess. The methods include translating a floor grid relative to a fuselage barrel, operatively aligning a plurality of alignment pin recesses with a corresponding plurality of fitting alignment recesses, and locating a plurality of alignment pins within the plurality of alignment pin recesses such that each of the plurality of alignment pins extends through a respective one of the plurality of fitting alignment recesses. The methods also include lowering the floor grid relative to the fuselage barrel and installing a plurality of fasteners.

Abstract: A method and apparatus for operating a nose cone. In one illustrative example, an apparatus comprises a plurality of segments and a movement system associated with the plurality of segments. The plurality of segments forms the nose cone. Each of the plurality of segments comprises a segment outer surface that forms a portion of an outer surface of the nose cone. The movement system is used to move at least one of the plurality of segments to move the nose cone between a retracted state and an expanded state.

Abstract: A main wing (1) on which a tensile load is exerted in a longitudinal direction includes a holed structural member that is a composite material made of fiber reinforced plastic which extends in the longitudinal direction and in which access holes (5) are formed and that serves as a center portion (3b); and a front portion (3a) and a rear portion (3c) that are composite materials made of fiber reinforced plastic which extend in the longitudinal direction of the main wing and which are connected to side portions of the center portion. The tensile rigidity of the center portion in the longitudinal direction is set to be lower than the tensile rigidity of the front portion and the rear portion in the longitudinal direction.

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.

Abstract: A modular floor track adapter system including a plurality of adapter plates laterally sized to span existing aircraft floor beams, each of the plurality of adapter plates shaped to interlock with an adjacent adapter plate in a side-by-side arrangement and including a series of holes for attaching seat track crown sections and panel attachment tabs for securing an aircraft floor panel thereto.

Abstract: Rear fuselage of an aircraft comprising a tail cone end and a rest of the real fuselage whereby the tail cone end is attached to the rest of the rear fuselage by means of an attachment system comprising two upper lugs, two lower lugs and a detachable balancer fitting. The balancer fitting is an adjustable fitting, being locked in a Z and Y directions of a Cartesian axis and being movable along an X direction of the Cartesian axis providing guidance for the tail cone end and the rest of the rear fuselage.

Abstract: Fuselages according to the present disclosure include a structural frame and a skin operatively coupled to the structural frame. In some embodiments, the skin includes a plurality of core sections that extend circumferentially around the fuselage and that are spaced-apart longitudinally along the fuselage. In some embodiments, the inner side of the skin generally undulates longitudinally along the fuselage. Methods of constructing fuselages also are disclosed.

Abstract: Structural panel assemblies include first and second composite panels positioned in edgewise alignment, with at least one tab extending from a mating edge of the first panel and including an exterior surface in facing registration with a corresponding portion of an interior surface of the second composite panel. The corresponding portion includes a recessed area to interfit with the tab or is otherwise configured to receive the tab. The exterior surface of the tab is spaced from the corresponding portion, to receive a bonding material therebetween for bonding the composite panels.

Abstract: The present disclosure relates to a wall component for an aircraft for forming an outer wall comprising at least one first wall element, at least one second wall element and at least one connecting device for connecting the first wall element to the second wall element. On wall regions that are to be directed towards each other, the first and the second wall element comprise connecting regions. Furthermore, a joint element is provided, which comprises a joint region with a joint region surface that is to be arranged towards the outside of the aircraft, wherein the joint region is designed to be received with a matching fit into a recess formed by the connecting regions of the wall elements, and wherein the joint region surface, when the joint element is inserted, is flush with the outer surfaces of the wall elements.