Abstract: A wing includes an upper wing skin, a lower wing skin, and a wing rib positioned between the upper wing skin and the lower wing skin. The wing rib includes: a corrugated composite web comprising a wave pattern and a first fitting coupling said corrugated composite web with one of said upper wing skin and said lower wing skin.

Abstract: A structural assembly including a first structural member defining a first partial bore and including a first protrusion and a second protrusion, a second structural member defining a second partial bore and including a first protrusion and a second protrusion, wherein the second partial bore is aligned with the first partial bore to define a through-bore, a shaft extending through the through-bore, wherein the shaft includes a first end portion and a second end portion, a first engagement member proximate the first end portion, wherein the first engagement member engages both the first protrusion of the first structural member and the first protrusion of the second structural member, and a second engagement member proximate the second end portion, wherein the second engagement member engages both the second protrusion of the first structural member and the second protrusion of the second structural member.

Abstract: One embodiment is a method including defining a maximum deflection for a first axis of a control surface axis of an aircraft; defining a maximum deflection for a second axis of the control surface; and creating a graphical representation of the maximum deflection for the first and second control surface axes. The method further includes determining an angle of rotation of a structure on which the control surface is carried, wherein the angle of rotation is relative to a body of the aircraft; rotating the graphical representation in accordance with the determined angle of rotation; calculating a distance between a point representing a selected combination of roll moment and yaw moment and each edge of the graphical representation; and calculating a control surface deflection based on the calculated distances.

Abstract: A system and method for preventing a maximum asymmetric condition between pylon tilt angles due to a degraded pylon in a fly-by-wire tiltrotor aircraft during transitions between airplane mode and helicopter mode includes a conversion system for imparting movement on a right and left pylon. A flight control computer is operatively connected to a set of transducers for measuring pylon angles. The flight control computer is further connected to a set of actuators which are attached to each pylon. The flight control computer receives flight dynamics input from the set of transducers and/or the pilot and sends pylon command to the set of actuators. The conversion system measures the difference between the pylon angles during the transition and provides a pylon command adjustment if the difference exceeds a preset threshold.

Abstract: An air vehicle control system is described that includes a computer-implemented controller. The controller is configured to control an air vehicle, where the air vehicle is logically divided into four sections of electrical and mechanical devices that are operatively connected to the controller via a control data bus and an actuation bus. The four sections include a forward sector, a left engine sector, a right engine sector, and an aft sector. The controller controls all four sections of electrical and mechanical devices of the air vehicle.

Abstract: An aircraft wing subassembly including: a wing skin defining a first outer surface, and, a structural reinforcement member, the structural reinforcement member defining a second outer surface, wherein the structural reinforcement member is arranged within the wing such that the first outer surface and the second outer surface form part of an outer wing surface.

Abstract: A method of assembling a wing tip device to a wing of a powered aircraft including: providing a wing tip, providing a wing tip device, pivotably attaching the wing tip device to the wing at a first position, pivoting the wing tip device about the first position, and attaching the wing tip device to the wing at a second position spaced from the first position.

Abstract: An electromechanical actuator includes an actuator that is translatable along an axis relative to a case and that is made up of a deployed part and a non-deployed part, which are following one another along the axis and which are respectively deployed and not deployed outside the case. The axial span of the deployed part varies proportionally opposite that of the non-deployed part as a function of the translated position of the actuator. The actuator also includes an electric motor for translating the actuator, which is supported by the case and is connected to the non-deployed part of the actuator by a transmission. The case defines an inner volume inside which the non-deployed part of the actuator, the motor and the transmission are arranged. The inner volume is, during operation of the actuator, pressurized while being filled with a gaseous atmosphere.

Abstract: An unmanned aerial vehicle comprising a rotor having one or more propeller blades and a propeller guard surrounding the rotor. The propeller guard comprises a main guard surrounding the one or more propeller blades and a movable guard vertically displaced from the main guard. The movable guard is movable from a default position to an engaged position by temporarily deforming the movable guard such that the movable guard contacts and obstructs rotation of the one or more propeller blades.

Abstract: A fluid delivery device includes a body and a reed. The body has a primary inflow passage, a secondary inflow passage, and an outflow passage. The reed is disposed at least partially within the body. The reed is configured to move to a first position when a fluid flows from the primary inflow passage and move to a second position when the fluid flows from the secondary inflow passage.

Abstract: A bond fixture includes a first fixture having a heater and a plurality of clamps. Each of the plurality of clamps includes a first member and a second member rotatable between a first position and a second position. A second fixture includes a root end lift translatable vertically between a retracted position and an extended position and a root end clamp translatable along a horizontal axis. The root end clamp is configured to cooperate with the root end.

Abstract: A dynamic propulsion system may be implemented to recover some or all of the wasted energy during a flight. The dynamic propulsion system may include one or more propellers that are configured to act as a propulsion system when altitude is rising and act as a windmill to generate energy to charge a battery during descent. The one or more propellers may include blades that are configured to adjust their angle of attack or pitch on command to switch from propulsion mode to regenerative mode and vice versa.

Abstract: A strake may extend along a portion of an approaching side of a tail boom of a helicopter. A number of vortex generators (VGs) may extend along a portion of a retreating side of the tail boom. For tail booms with circular cross sections, the strake and the VGs are positioned between approximately 5 and 15 degrees below a horizontal plane of the tail boom when viewed end on, on respective sides of the tail boom. For tail booms with non-circular cross sections, the strake and the VGs is positioned between approximately 5 and 15 degrees above a location where a change in curvature is greatest (e.g., where flow separation would otherwise occur) on a bottom half of the tail boom when viewed end on, on respective sides of the tail boom. A fairing may be located on the retreating side on the upper half of the tail boom, to create an asymmetric profile.

Abstract: An aeronautical apparatus is disclosed that has two pairs of wings. Each wing has a thrust-angle motor. A propeller and propeller motor are coupled to each thrust-angle motor. Propeller pitch is controlled by a propeller-pitch motor. The thrust-angle motor allows the propeller axis of rotation to be parallel to the fuselage's longitudinal axis; vertical (perpendicular to longitudinal axis, as in well-known fixed-position, four-propeller drones); and any position between as well as a given range exceeding these bounds which is used for control. An electronic control unit is electronically coupled to the thrust-angle motors, propeller motors, and propeller-pitch motors, which can be independently controlled, to provide the desired thrust and trajectory. Such an apparatus can provide efficient operation in vertical take-off/landing (hovering) and forward (translational) flight modes.

Abstract: Airframes configured for stable in-flight transition between forward flight and vertical takeoff and landing are described herein. In one embodiment, an aircraft can include a fuselage, opposed wings extending from opposed sides of the fuselage, and a plurality of engines. At least one engine can be mounted to each of the opposed wings and at least a portion of each opposed wing including at least one of the plurality of engines can rotate relative to the fuselage around a rotation axis that is non-perpendicular and transverse to a longitudinal axis of the fuselage. Rotating portions of the wings including at least one of the plurality of engines in the described manner can provide a stable and smooth transition between vertical and forward flight.

Abstract: A tail sitter aircraft includes a fuselage having a forward portion, an aft portion and a longitudinally extending fuselage axis. At least two wings are supported by the forward portion of the fuselage. A distributed propulsion system includes at least one propulsion assembly operably associated with each fixed wing and is operable to provide forward thrust during forward flight and vertical thrust during vertical takeoff, hover and vertical landing. A tailboom assembly extends from the aft portion of the fuselage and includes a plurality of rotatably mounted tail arms having control surfaces and landing members. In a forward flight configuration, the tail arms are radially retracted to reduce tail surface geometry and provide yaw and pitch control with the control surfaces. In a landing configuration, the tail arms are radially extended relative to the fuselage axis to form a stable ground contact base with the landing members.

Abstract: Various embodiments of a foldable unmanned aerial vehicle having a multi-layer laminate structure and extendible arms are disclosed.

Abstract: A fact checking system utilizes social networking information and analyzes and determines the factual accuracy of information and/or characterizes the information by comparing the information with source information. The social networking fact checking system automatically monitors information, processes the information, fact checks the information and/or provides a status of the information, including automatically modifying a web page to include the fact check results. The fact checking system is able to be implemented utilizing a drone device.

Abstract: The disclosure relates to an arrangement comprising a flyable unmanned transporting device and a movable catch arm, which is provided at a ground station, for holding the transporting device at the ground station, wherein at least one recess is provided on the transporting device, and the catch arm, at its end facing away from the ground station, has at least one expansion element which can be introduced into the at least one recess and, in the introduced state, can be expanded in order to produce a form fit between the at least one recess and the at least one expansion element.

Abstract: In an illustrative embodiment, a frame assembly for enclosing an electronic device mounted to a rear surface of a seatback of an aircraft seat includes a rear frame for mounting within a recess of the rear surface of the seatback, a front frame detachably connected to the rear frame such that the electronic device, when mounted in the frame assembly, is enclosed between the front frame and rear frame, the front frame including an opening defining a boundary of a visible screen region of the electronic device, and an adapter disposed between the rear frame and the rear surface of the electronic device, the adapter including an aperture configured to receive the rear surface of the electronic device and raised peripheral edges surrounding the aperture to adapt the dimensions of the electronic device to the dimensions of the rear frame.

Abstract: Alternate manners of utilizing areas of, principally, cargo areas of commercial passenger aircraft are described. These manners of utilizing preferably occur during cruise or other non-TTL portions of flight and provide passengers with additional opportunities to move, shop, meet, relax, bathe, exercise, cook, eat, work, or otherwise engage in activities conventionally unavailable or difficult to perform while on-board commercial aircraft. They likewise may provide opportunities to generate additional revenue from passengers without necessarily adding seats. Equipment and structures permitting these uses of the cargo areas as lower deck cabins also are detailed.

Abstract: A cabin module for a commercial aircraft includes a set of bulkheads defining a quadrant with an inboard wall and converging side walls. The module is sub-divided by a removable partition which splits the module into two passenger compartments. The quadrant shape of the module enables it to overlap an adjacent seat area, thereby using space between seat areas that is otherwise underutilised. In a particular form the modules define a single central aisle which transitions from a pair of parallel aisles aft via a Y-shaped transition region.

Abstract: A seat for an aircraft comprises a compartment and a seal system. The seal system comprises a first tab connected to a first portion of the compartment, a second tab connected to a second portion of the compartment, and a piece of adhesive material connecting the first tab to the second tab.

Abstract: An aircraft seat armrest includes an armrest portion and two extension elements coupled to the armrest portion on opposite sides thereof. A first of the two extension elements is rotatable from a first, closed, position where it is disposed below the armrest portion to a second, open, position wherein the first extension element is adjacent to the armrest portion. The arm rest also includes a first locking mechanism disposed on the first extension element that maintains the first extension element in the open position after it has been moved from the closed position to the open position.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein, a dehumidification system arranged in fluid communication with the ram air circuit, and a compressing device arranged in fluid communication with the ram air circuit and the dehumidification system. The compression device includes a compressor and a first turbine coupled to one another via a shaft. During operation of the first turbine, work is extracted from a first medium within the first turbine to power the compressor. At an outlet of the first turbine, a temperature of the first medium is above freezing and at least a portion of the moisture within the first medium is condensed.

Abstract: An environmental control system of an aircraft with a power turbine includes a heat exchanger and a plenum attached to and in fluid communication with the heat exchanger. The plenum includes a housing with a first inlet fluidly connected to the power turbine, a second inlet fluidly connected to a source of ram air, and an outlet fluidly connected to the heat exchanger.

Abstract: An environmental control system assembly for an aircraft includes a heat exchanger assembly and a plenum. The heat exchanger assembly includes a first heat exchanger in fluid communication with a source of bleed air, a second heat exchanger disposed adjacent to the first, a third heat exchanger disposed adjacent to the second, and an end sheet. The first heat exchanger includes a first endwall, a first inlet header, a first outlet header, and a first endcap located on the first outlet header. The third heat exchanger includes a third endwall, a third inlet header connected to the third endwall, a third outlet header, and a third endcap located on the third inlet header. The end sheet includes the first, second, and third endwalls. The plenum fluidly connects the first outlet header of the first heat exchanger to the third inlet header of the third heat exchanger.

Abstract: A method for detecting icing conditions for an aircraft including a measurement of the parameters of embedded systems, with the exception of probes dedicated to the detection of ice, a transformation of the measurements of the symptomatic parameters to obtain P-tuples of values of explanatory variables which explain icing conditions, a classification of the measurements by classifiers on the basis of the P-tuples of values thus obtained, the classifiers having been previously trained in a supervised manner, each classifier providing a prediction of membership in a class of icing conditions, the predictions of the various classifiers being consolidated to provide a consolidated prediction of icing conditions.

Abstract: A distributed parachute system is disclosed. In various embodiments, a parachute is at least partially deployed along one or more dimensions. A deployment mechanism configured to deploy the parachute is provided.

Abstract: A method of electrically powering an electrical load in an aircraft, the method including electrically powering the electrical load with a main source that generates electricity; measuring an instantaneous parameter characterizing the main source; determining a level of use of the main source from the measured instantaneous parameter; adjusting the voltage of the main source as a function of the level of use; measuring an output voltage from the main source; comparing the measured voltage or the level of use with a predetermined threshold value; and whenever the measured voltage is less than the predetermined threshold value, electrically powering the electrical load from an auxiliary source that stores electricity so as to supply additional electric power to the electrical load.

Abstract: A power system for an aircraft includes a plurality of power consumers each operable to consume power in a range from zero to maximum power demand and collectively capable of consuming a combined maximum power demand, a power source operable to output power to the power consumers and a power allocation system operable to allocate power from the power source to the power consumers based on an operational parameter of the aircraft. The power allocated by the power allocation system is less than the combined maximum power demand of the power consumers, thereby allowing the power source to have a maximum power output less than the combined maximum power demand of the power consumers.

Abstract: A projection system of the present disclosure includes: a flying object having an exterior body, a flying device that causes the exterior body to fly, and an image capturing device that captures an image; a projection device that projects a capture-dependent image on the exterior body, the captured-dependent image depending on the image; and a controller that causes the projection device to project the capture-dependent image.

Abstract: A method for positioning a boarding bridge at an airplane includes taking a picture of the parked airplane. A row of two adjacent side window rings is detected in the picture, wherein the side window ring is an extraction of a side window. A door polygon adjacent to the row of side window rings is searched for and a relative position of the door is calculated. The position is compared to a position of a distal end of the passenger boarding bridge or a camera taking the picture and the passenger boarding bridge is moved automatically based on the calculated relative position.

Abstract: The present invention is a device, system and method for removing stuck brake key screws. Specifically, the invention is capable of ensuring a more effective means and method for removing stuck brake key screws from an aircraft's landing gear wheel hub half. More specifically, the invention provides for optimal or virtually optimal engagement of the device with the head of a screw to be removed, and which, it is the inventor's belief, allows for the virtually optimal transmission of screw removal torque to a screw, which should minimize the likelihood of stripping the head of the stuck screw and, if stripped, the need to expend the time and effort to drill out the screw.

Abstract: A payload joint (10) for detachably attaching to each other two adjacent construction elements (2) in a spacecraft and/or launch vehicle, the payload joint (10) comprises two opposing clamps (11a, 11b) and two opposing flanges of the construction elements collaborating with angled surfaces of the clamps (11a, 11b). The payload joint comprises a bolt that connects the clamps (11a, 11b) and drives them towards each other when tightening the payload joint (10). The payload joint (10) further comprises a bolt cutter (101) arranged for cutting the bolt upon activation.

Abstract: Networked initiation systems for hold-down and release mechanisms (HDRMs) are described. The systems include a control unit, a plurality of firing control units operably connected to and in communication with the control unit, wherein each firing control unit has at least one HDRM operably connected thereto, and wherein each firing control unit is individually addressable by the control unit over an interface bus to enable selective operation of the HDRMs operably connected to the firing control units.

Abstract: The present disclosure relates to an aerosol container made of plastic, the container having a neck, the opening of which is closeable in a pressure-tight manner by a valve unit that can be actuated by a pushbutton, the container being Tillable with a liquid or gaseous propellant and a liquid to be sprayed. The aerosol container can be an injection cast preform with an elongated tubular preform body. The preform body is closed by a dome-shaped convex preform base, beyond which an integrally formed stand region projects in an axial direction. The preform body adjoins the opening of the neck at the opposite axial longitudinal ends of the preform body.

Abstract: A method for producing a packaging material comprises providing a core material layer of fibre-based material having an inner side and an outer side, embossing the core material layer for forming embossed features having an initial height, the embossed features protruding from the outer side of the core material layer to later form a tactile pattern on a side of the package to be formed by the packaging material, and laminating at least one layer to the inner side of the embossed core material layer such that the height of the embossed features is temporarily reduced to a minimum height.

Abstract: The machine (1) in question comprises a dispensing module (6) and a unit (9) for applying lids (3). According to the invention, the machine (I) comprises: a rotary plate (5) having cavities (12); a unit (7) for delivering shells (2) of capsules to a cavity (12), comprising a storage magazine (15) for storing the shells (2) stacked together, and a sub-assembly (20-24) for delivering shells (2) one by one to the plate (5), by gravity; a unit (8) for filling a shell (2) with product, comprising a funnel (16) facing which an empty shell (2) placed in a cavity (12) of the plate (5) is positioned by rotating said plate (5).

Abstract: A packaging machine hopper is provided for holding a stack of packaging articles with each article in a generally horizontal orientation. The hopper comprises a support for holding at least part of the stack at an angle to vertical.

Abstract: In an installation for the treatment of containers comprising at least one filling station and a packing station for processing film or packaging material blanks and having work components acting upon the packaging material and forming packages, at least one measuring device for dimensional deviations of filled containers and a control unit for automatically adjusting at least one installation station depending on a dimensional deviation detected, work components in the packing station (P) acting upon the packaging material when the filled containers are packed are automatically adjustable by way of the control unit. In a method for packing filled containers, work components of the packing station acting upon packaging material are adjusted automatically depending on dimensional deviations measured in order to form packages of different dimensions with at least substantially the same packing density.

Abstract: An apparatus for processing containers includes at least one processing assembly for containers and elements for feeding, with a continuous flow, the containers to a labeling unit having at least one labeling station intended to label the containers that arrive from a respective flow of containers. The apparatus includes elements for identifying non-conforming containers configured to be ejected from the respective flow of containers, expulsion elements configured to remove, from the respective flow intended for a respective labeling station, the containers that immediately follow the positions of the non-conforming containers along the advancement direction of the flow in order to obtain, in the respective flow, an uninterrupted sequence of missing containers in a number equal to at least one preset number.

Abstract: A blow bottle includes an outer layer and an inner layer, wherein the inner layer has blackness higher than that of the outer layer, and wherein the outer layer has an L* value of 20 or more and 90 or less in an International Commission on Illumination (CIE) L*a*b* color system.

Abstract: A container for dispensing a liquid water-insoluble edible fat includes a main body portion containing a body volume and a fill sub-volume, less than the body volume, within a first region of the main body portion. The container includes a pouring portion configured to direct a flow of the liquid water-insoluble edible fat out of the container when the container is tilted off of a vertical axis, and a neck portion connecting the main body portion to the pouring portion. The neck portion has a neck width less than a width of the main body portion in a first direction, the main body volume is configured to further include a catch sub-volume within a second region of the main body portion extending beyond the neck width in the first direction, the second region is different than the first region, and the catch sub-volume is substantially equal to the fill sub-volume.

Abstract: A synthetic resin container, the container including: a parting line; and a plurality of reduced pressure absorbing panels each formed as a groove extending in the vertical direction while twisting in the circumferential direction, the reduced pressure absorbing panels being disposed in the trunk, in which: when the parting line passes through an upper part of a first reduced pressure absorbing panel and through a lower part of a second reduced pressure absorbing panel, the first reduced pressure absorbing panel is shallower in depth at the upper part thereof than at a central part thereof in the vertical direction, and the second reduced pressure absorbing panel is shallower in depth at the lower part thereof than at a central part thereof in the vertical direction.

Abstract: A container (10) comprising one or more walls (12, 14, 16) and a base (18) defining an enclosure for storing and displaying one or more items (90). A locking tab (22) is defined in each side wall (16) and corresponding locking slots (26) are defined in the base (18). The locking tabs (22) each define an undercut (22c). The container (10) can be mounted on top of a further container (10) to form a modular display device by inserting the locking tabs (22) of the further container into the locking slots (26) and sliding the container forwardly to engage the base (18) in the undercuts. The modular display device (34, FIG. 3) may also include a stand for supporting one or more containers at an angle on a horizontal surface and a header.

Abstract: A container and blanks and a blank assembly for forming the container are provided herein. The container includes a tray, the tray including a pair of tray side walls, a pair of tray end walls, and a first glue panel coupled to one of the tray end walls. The container also includes a cover releasably coupled to the tray to transition the container from a shipping to a display configuration, the cover including a pair of cover side walls aligned with the pair of tray side walls, a pair of cover end walls aligned with the pair of tray end walls, and a second glue panel coupled to one of the cover end walls. At least a portion of the tray overlaps with at least a portion of the cover, and the first and second glue panels are vertically aligned with and uncoupled from one another.

Abstract: A latchable package comprises: a support (200) for supporting one or more items; a structure (300) for selectively blocking access to the one or more items; and a latchable insert (400). The latchable insert comprises a substantially planar tab member that is coupled to the support such that the insert and support are movable together in an opening direction from a first position in which the structure blocks access to the one or more items to a second position in which the one or more items are accessibly clear of the structure. The structure and the latchable insert comprise co-operating latch features (380) configured to engage when the insert and support are arranged in the first position.

Abstract: A bottle carrying and opening system includes a container and a bottle opener. The container includes a bottom wall and a perimeter wall extending upwardly from the bottom wall. The container further includes an interior space configured to hold bottles inside it. The bottle opener is coupled to the perimeter wall of the container and is configured to remove a cap of a bottle. The bottle opener includes a base panel and a functional sports article, wherein the functional sports article is shaped to represent a hockey puck, baseball, football, or basketball. The bottle carrying and opening system is useful for carrying bottles for opening bottles using the built-in bottle opener, which is always conveniently on hand, cannot be misplaced, and has an appealing look inspired by a current sports season.

Abstract: A dispensing basket includes a pair of opposed side walls and a back wall that extends between the opposed side walls. A pair of front walls extend from the side walls in a direction towards each other and angled away from the back wall. The pair of front walls form a funnel with an opening between the pair of front walls. A floor extends between lower ends of the side walls, the back wall, and the front walls.