Abstract: The present disclosure pertains to a window module for an aircraft or spacecraft, including a window frame which comprises, at least in portions, a current-generating element for generating an electric current.

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: The following steps are performed in the method of constructing an aircraft: taking a subassembly comprising two wings that are rigidly fastened together, and fitting it to a fuselage wall; and fastening the subassembly to the wall by means of fastener elements that are distinct from the subassembly and that present main axes that are vertical.

Abstract: An insulation system, for use with transport vehicle structural frame members, having at least a first structural frame member and adjacent structural frame members in a transport vehicle. Each structural frame member has a first free end, a second end attached to a transport vehicle wall, and two sides disposed between the first and second ends. The system has at least one flexible insulation member wrapped over the first free end and over at least portions of the two sides, and at least first and second self-retaining foam insulation members positioned on each side of the wrapped first structural frame member and disposed in compression fit between each side of the wrapped first structural frame member and each of the adjacent structural frame members. The foam insulation members impart one or more compression forces on the flexible insulation member to secure it in place without use of any fastener device.

Abstract: Methods and apparatus to control a gap between movable aircraft wing components are disclosed. An example apparatus includes a body having a trailing edge and a leading edge. The leading edge is to be coupled to an aircraft wing. The trailing edge is to engage a flap of the aircraft wing. The body includes a structure located between the trailing edge and the leading edge. The structure is to engage the flap to maintain a distance between the body and the flap.

Abstract: A trailing-edge flap system for a wing of an aircraft comprises a trailing-edge flap, a guide rail attached to the trailing-edge flap, a carriage slidably engaging the guide rail and rotatably attachable to a fixed position on the wing structure, and a drive means coupled the wing structure to a first joint on the guide rail. The drive means is configured to move the trailing-edge flap relative to the wing structure by moving the guide rail along the carriage by moving the first joint relative to the wing structure, such that the trailing-edge flap translates and rotates. The trailing-edge flap is at least movable into a cruise position, a high-lift position and an air brake position.

Abstract: A variable camber Krueger flap deployment linkage mechanism is presented. A first linkage assembly couples a flap assembly and an airfoil, and comprising a first drive arm, a first drive link, and a support arm. A second linkage assembly couples the flap assembly and the first drive arm, and comprises a drive transfer arm, a middle connection segment, and a bullnose link.

Abstract: Systems and methods disclosed herein may be useful for use in landing identification. In this regard, a method is provided comprising receiving pulse information over a first time period, wherein the pulse information is indicative of an angular distance traveled by a first wheel, comparing the pulse information to a threshold value, and determining a likelihood of a landing event based upon the comparison. In various embodiments, a system is provided comprising a monstable multivibrator in electrical communication with a metal-oxide-semiconductor field-effect transistor (MOSFET), a resistor-capacitor network in electrical communication with the MOSFET, and a comparator that receives a voltage from the resistor-capacitor network and a reference voltage.

Abstract: Systems and methods disclosed herein may be useful for use in landing identification. In this regard, a method is provided comprising receiving pulse information over a first time period, wherein the pulse information is indicative of an angular distance traveled by a first wheel, comparing the pulse information to a threshold value, and determining a likelihood of a landing event based upon the comparison. In various embodiments, a system is provided comprising a monstable multivibrator in electrical communication with a metal-oxide-semiconductor field-effect transistor (MOSFET), a resistor-capacitor network in electrical communication with the MOSFET, and a comparator that receives a voltage from the resistor-capacitor network and a reference voltage.

Abstract: A landing gear assembly 10 having first and second parts 12b, 14b movably mounted with respect to one another. The landing gear assembly includes a critical space 32. A spring assembly 26 is arranged to bias the first and second parts to move relative to one another. A spring support 30 is provided to inhibit a broken portion of the spring assembly entering or contacting the critical space following a spring failure.

Abstract: The present disclosure describes an axle sleeve. The axle sleeve may be insertable over a portion of an axle, such as a mid-journal surface between an inner journal and an outer journal of the axle, to protect the mid-journal surface of the axle from damage. The axle sleeve may have a main body with an expansion mechanism, such as an axial cutout arrangement or a helical cutout arrangement. The expansion mechanism may allow the axle sleeve to expand diametrically to pass over a journal and to contract to seat on a mid-journal surface. An axial cutout arrangement may include cutout(s) extending from an end of the axle sleeve parallel to the central axis of the axle sleeve. A helical cutout arrangement may include cutout(s) extending from an end of the axle sleeve along a spiral path.

Abstract: An aircraft electric taxi drive system may provide electric taxiing of an aircraft by integrating control of an electric drive and an engine during the taxi phase of a flight plan. In some embodiments, the engine may provide supplemental drive to the aircraft's wheels during electric taxiing. The engine may be maintained on while the electric drive provides the main driving force to the wheels. A controller may determine the criteria to operate the engine as the electric drive taxis the aircraft to achieve a target ground speed. In some embodiments, a pilot interface may integrate control of the electric drive and the engine into a single throttle control providing the pilot an intuitive and singular point to throttle the aircraft without having to decide which taxi source is providing the taxi driving force.

Abstract: An auxiliary drive wheel taxi system for driving an aircraft autonomously without reliance on engine operation during ground travel is designed for installation in an aircraft location other than on nose or main landing gear components. The auxiliary drive wheel taxi system may be mounted in an integral housing located internally or externally on an aircraft's body at a selected location relative to main or nose landing gears and includes one or more auxiliary drive wheels mounted on an extensible strut adapted to extend from and retract into the housing. An electric, hydraulic, or pneumatic non-engine drive means controllable to provide torque required to rotate the drive wheel and drive the aircraft at desired taxi speeds may be mounted in a selected location to drive the auxiliary drive wheel. The manually or automatically controllable auxiliary taxi system is operable only to drive the aircraft during taxi.

Abstract: A gearbox for driving a sprocket includes a gear train and an output shaft assembly positioned between the gear train and a power output end of the gearbox. The output shaft assembly includes, a first shaft segment extending to the power output a second shaft segment coupled to the gear train and a torsion spring interposed between the first shaft segment and the second shaft segment. Upon non-conjugate meshing of the sprocket, the torsion spring expands and contracts so that the angular velocity of the second shaft segment differs from the angular velocity of the first shaft segment.

Abstract: A boundary layer ingesting (BLI) blade having a span is provided and includes a root section connectable to a hub, a tip section disposable at a distance from the hub and having a pitch and a body extending in a spanwise dimension from the root section to the tip section. The root section has a local pitch from the root section to about a 70% span location, which is less than the pitch at the tip section, to thereby reduce local angles of attack in a boundary layer region defined in and around the root section.

Abstract: The present invention is a winged VTOL aircraft of novel configuration that utilizes a single-axis rotor mounted at an oblique angle within a forward-facing, bifurcating duct, that is controlled by a plurality of servo driven vanes, producing a mechanically simple, redundantly controlled vehicle that can carry cargo, people, or otherwise, directly from point to point. The configuration uses sets of vanes to produce both moments and forces referenced around the vehicle's center of gravity, thereby, allowing the vehicle to translate in a level position, or stay stationary relative to the ground while at a slight pitch or roll attitude. This feature is very important for autonomous vehicles to accurately pick up and drop off payloads on unlevel terrain or in windy conditions. Other rotor vehicles require pitch or roll attitude to translate or compensate for wind.

Abstract: An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft.

Abstract: An aircraft for use in fixed wing flight mode and rotor flight mode is provided. The aircraft can include a fuselage, wings, and a plurality of engines. The fuselage can comprise a wing attachment region further comprising a rotating support. A rotating section can comprise a rotating support and the wings, with a plurality of engines attached to the rotating section. In a rotor flight mode, the rotating section can rotate around a longitudinal axis of the fuselage providing lift for the aircraft similar to the rotor of a helicopter. In a fixed wing flight mode, the rotating section does not rotate around a longitudinal axis of the fuselage, providing lift for the aircraft similar to a conventional airplane. The same engines that provide torque to power the rotor in rotor flight mode also power the aircraft in fixed wing flight mode.

Abstract: A system for providing the general public with simplified access to aerial surveillance. The system software initially functions as a viewer, but also provides a path to increase a participant's control. The software architecture is structured to accommodate multiple users simultaneously and minimizes operational down-time by organizing participants into a standby queuing system. The system also provides a step-by-step operator-pilot progression, with built in training and certification modules, to train and qualify a participant for higher levels of control. This progression starts by allowing a participant to remotely track the flight path of a surveillance aircraft, then view its camera feed, operate the camera, and eventually pilot the aircraft. The system in applicable whether the aircraft is manned or unmanned, and incorporates an interrupt mechanism to mitigate undesirable mission parameters.

Abstract: Unmanned aerial vehicles and methods for providing the same are disclosed. The unmanned aerial vehicles may have various configurations related to a support frame. The unmanned aerial vehicles may have various configurations with a continuous track for ground propulsion. The unmanned aerial vehicles may have various configurations related to payload clamps.

Abstract: A method for retrieving personnel is provided. The method includes receiving a radio signal indicating a real-time position of personnel to be retrieved, deploying an unmanned aerial vehicle to the real-time position, receiving an indication that the personnel to be retrieved is on-board the unmanned aerial vehicle, and operating the unmanned aerial vehicle to move the personnel to a different location.

Abstract: A service unmanned aerial vehicle (UAV) includes a flight system, a status component, a navigation system, and a recovery component. The flight system is for flying the service UAV. The status component is configured to determine that a first UAV is disabled. The navigation system is configured to fly the service UAV to a landing location of the first UAV in response to the status component determining that the first UAV is disabled. The recovery component is configured to recover one or more of a payload of the first UAV and a portion of the first UAV.

Abstract: A method for adaptive mission execution by an unmanned aerial vehicle includes receiving a set of pre-calculated mission parameters corresponding to an initial UAV mission; collecting UAV operation data during flight of the unmanned aerial vehicle; calculating a set of modified mission parameters from the set of pre-calculated mission parameters and the UAV operation data, the set of modified mission parameters corresponding to a modified UAV mission; and executing the modified UAV mission on the unmanned aerial vehicle.

Abstract: Stabilized airborne drop delivery using an Unmanned Aerial Vehicle (UAV) is described. In one embodiment, the UAV includes a flight controller configured to control a flight path of the UAV, a winch mechanism secured to an underside of the UAV, a platform tethered to and extendable from the winch mechanism, and a ballast system configured to stabilize the platform. The winch mechanism may be relied upon to drop an item for delivery without landing the UAV. Because the use of the winch mechanism may give rise to certain design and operating considerations, various active and passive flight and/or ballast control systems are described. These systems are configured to maintain an orientation of the UAV, the platform, and/or the item during one or more stages of airborne drop delivery.

Abstract: A mounting system is provided including a center platform having a plurality of mounting lugs for mounting the center platform transversely extending at least partially through an aircraft cabin with a first end and second end of the center platform adjacent a respective first and second side opening of the aircraft cabin. A first support pylon may be removably coupleable to the first end of the center platform to extend outwardly from a first side of the aircraft. A second support pylon may be removably coupleable to the second end of the center platform to extend outwardly form a second side of the aircraft. A modular floor component may be removably coupleable relative to a longitudinal side of the center platform to provide a substantially planar load surface including a top portion of the modular floor component and a top surface of the center platform.

Abstract: An interior component for an interior room of an aircraft is provided. The interior component includes a body having a first surface and a second surface and a multitude of functional modules which form a passenger service unit. The second surface is arranged opposite to the first surface and comprises a recess. The multitude of functional modules are arranged one after another in the recess in the longitudinal direction of the interior component, such that a first front surface of the functional module arranged frontally in the longitudinal direction closes flush with a first front surface of the body.

Abstract: A method and apparatus are presented. An apparatus comprises a wall and a urinal. The wall is physically associated with a fuselage for an aircraft. The urinal is positioned along the wall, the wall and urinal positioned within a specialty lavatory area module.

Abstract: A passenger seat for a means of transportation is provided, which comprises a seat frame with a top side, which top side is configured for supporting a seat pan with a seat cushion for providing a seating area for a passenger, and a bottom side opposing the top side. The passenger seat further comprises a stowage cavity arranged between the top side and the bottom side of the seat frame. The seat frame further comprises a first beam and a second beam, both beams being arranged parallel to each other and parallel to a transversal axis of the passenger seat. The top side of the seat frame provides an access to the stowage cavity such that a stowage compartment, which is configured to accommodate an item of luggage, is insertable into the stowage cavity through the access.

Abstract: A storage unit (100) has a storage box (110) and a base frame (130) which is removably mounted to the storage box. A hinge (160) is provided to a hinge mounting section (140) of the base frame (130) and supports a lid (150) so that the lid can be opened and closed. The hinge (160) is composed of two inner arms (170) and outer arms (180). A rotation shaft of the hinge is guarded by the inner arms (170) and outer arms (180), so that objects and fingers are prevented from being caught.

Abstract: The present invention provides a water inflow prevention device for aircraft, working when landing in water, the device including: a blocking body for blocking a flow channel from an outside of the aircraft when landing in water, the flow channel allowing the inside and outside of the aircraft to communicate with each other, and a valve element of a pressure adjusting valve being positioned in the flow channel; and a connection part that is deformed when landing in water, wherein the blocking body is supported by a member constituting an end of the flow channel on a side outside the aircraft through the connection part, and the connection part is deformed in a direction so as to block the flow channel by the blocking body, with use of force of water acting on the blocking body when landing in water.

Abstract: An impact protection apparatus is provided, comprising a gas container configured to hold a compressed gas and an inflatable member configured to be inflated by the gas and function as an airbag of a movable object, such as an aerial vehicle. A valve controls flow of gas from the container to the inflatable member in response to a signal from a valve controller. The valve and valve controller are powered by an independent power source than one or more other systems of the movable object. A safety mechanism may also be provided that, unless deactivated, prevents inflation of the inflatable member.

Abstract: An aerodynamic fairing whose floor has absolutely no contact with respect to the lateral panels over the entire length of the fairing along the longitudinal axis. A free space e is provided between the floor and the lower edge of each panel. There is a longitudinal mechanical gap between the floor and each of the lateral panels. The absence of any rigid mechanical connection between the floor and the lateral panels allows the transfer of the thermomechanical stresses from the floor to the lateral panels and therefore preventing the deformation of the fairing.

Abstract: A system and method are provided for controlling the power setting of an aircraft engine when the current height-above-terrain (HAT) value Hc is less then a predetermined minimum H(min). The system includes a ground proximity unit (GPU) for measuring Hc, one or more sensors coupled to the engine for detecting an out-of-range operating condition of the engine, an engine control unit (ECU) coupled to the GPU and the one or more sensors and the engine, for controlling operation of the engine in response to Hc, H(min) and the engine operating values. When the one or more sensors detects an out-of-range operating condition normally curable by reducing the engine power setting, the ECU is prevented from automatically reducing the power setting of the engine if Hc<H(min). No pilot action is required.

Abstract: Control systems and methods for a propulsion system are disclosed in which the propulsion control system is integrated to intelligently control propulsion and minimize transient effects from the power demands of other subsystems.

Abstract: An aircraft hybrid fuel system includes a main tank and a set of flexible bladders, the main tank and the set of flexible bladders defining a fuel containment space. The system further includes a set of pathways coupling the set of flexible bladders to the main tank. The set of pathways is constructed and arranged to vent gas out of the set of flexible bladders into the main tank while fuel from a fuel source is provided into the fuel containment space defined by the main tank and the set of flexible bladders. Along these lines, each flexible bladder can be provisioned with a fuel port to provide fuel, and a separate vent port to vent gas to the main tank.

Abstract: Systems and methods for isolating attitude failures are provided. In one embodiment, an attitude integrity and display system comprises a display system comprising a primary system displaying a first attitude solution and a standby system displaying a second attitude solution; an attitude integrity system generating an attitude integrity (AI) solution calculated from measurements from an attitude solution data source, the AI solution comprising an aircraft roll and pitch, the data source providing data independent from any data generated by inertial sensor flight instruments and not displayed on either the primary or the standby systems; and an attitude monitor that compares the first solution against the second solution. When the first solution deviates from the second solution by more than a threshold, the monitor identifies on the display system which of either the first or the second solution is failed based on which has a greater deviation from the AI solution.

Abstract: A method and device for automatically determining a speed profile with speed levels for an aircraft. The device includes a calculation unit which is configured for determining a speed profile (P1) which is such that, from upstream to downstream, the speed (V) is maintained at a speed constraint (V1) imposed at a waypoint (B1), up to said waypoint (B1), then a deceleration (T2) is performed from this waypoint (B1) up to an optimum speed (Vopt), said optimum speed (Vopt) being maintained up to another deceleration (T4) ending directly at a downstream speed limit (V2) reached at a given altitude level (A2).

Abstract: A method for determining a state of a component in a high lift system of an aircraft is proposed, the high lift system comprising a central power control unit for providing rotational power by means of a transmission shaft; and drive stations coupled with the power control unit and movable high lift surfaces.

Abstract: A method and apparatus for reducing an intensity of an electrical discharge that occurs within a fluid transport system in an aerospace vehicle. In one illustrative embodiment, an apparatus includes a transport member. The transport member is configured for use in the fluid transport system. The transport member includes a material configured to reduce voltages and currents, induced in response to an electromagnetic event, along the transport member.

Abstract: A seat assembling method for assembling at least one seat into an airplane, the method having the steps of position a seat installing device at a predetermined assembly position in the airplane, convey the at least one seat into the interior of the airplane to the seat installing device by means of a seat conveying device, transfer the seat from the seat conveying device to the seat installing device, and install the seat by means of the seat installing device which is positioned at the assembly position.

Abstract: According to one embodiment, a method of assessing health of two or more components includes receiving, from an aircraft, a plurality of flight measurements, the aircraft comprising a first component and a second component. At least two flight regimes that the aircraft operated in at the same time are identified. The at least two flight regimes comprise a first flight regime and a second flight regime. One of the first flight regime and the second flight regime is assigned to the first component based on where the first flight regime and the second regime are located within a prioritized list of flight regimes associated with the first component. One of the first flight regime and the second flight regime is assigned to the second component based on where the first flight regime and the second regime are located within a prioritized list of flight regimes associated with the second component.

Abstract: Herein is disclosed a tool, system and method for refueling on-orbit spacecraft. The tool and system are configured to allow for resupply of spacecraft configured to be propelled by either a bipropellant (oxidizer and fuel) or a monopropellant (typically hydrazine). The refueling tool is particularly suited for resupply of satellites not originally prepared for refueling but the system may also be used for satellites specifically designed for refueling.

Abstract: A system and method according to which ice is automatically disposed in respective bags and the bags of ice are distributed and stacked within a temperature-controlled storage unit, such as an ice merchandiser.

Abstract: A filling system for filling powder into a target container to be sealed has a metering device for metering a partial quantity of the powder to be filled in. A compaction element for the powder is arranged below the metering device. The compaction element can be lowered from above into the target container. The compaction element is a shaking element with a shaking drive. During filling of the target container with the powder, the shaking element at least partially projects from above into the target container. The shaking element has a bottom edge provided with a shaking projection, wherein the shaking projection, beginning at the bottom edge, extends downwardly. During filling of the target container with the powder, only the shaking projection of the shaking element projects from above into the target container and the shaking element as a whole does not contact the target container.

Abstract: The present invention relates to a plastic preform (200) for a container (300) comprising at least one elongate reinforcing element (210), and obtained by injection-molding. The present invention further relates to a container (300) blow-molded from such a preform (200), and comprising at least one reinforcing element (320), and having a continuous and smooth outer surface (310b).

Abstract: The invention concerns an apparatus (10) for simultaneously blowing and filling a plastic container from a preform, the apparatus comprising: a mold (14) for enclosing a preform, so as to leave access to the mouth of the preform, stretching means (42) for stretching the preform within the mold, an injection head (16) for injecting a liquid through the mouth so as to cause expansion of the preform within the mold, thereby obtaining a blown and filled container (12) that comprises a dispensing opening (22), characterized in that the apparatus further comprises a capping head (18) for fixing a cap (40) on the dispensing opening of said blown and filled container, the capping head being permanently arranged between the injection head (16) and the mold (14).

Abstract: A semi-rigid collapsible container has a side-wall with an upper portion, a central portion, a lower portion and a base. The central portion includes a vacuum panel portion having a control portion and an initiator portion. The control portion is inclined more steeply in a vertical direction, i.e. has a more acute angle relative to the longitudinal axis of the container, than the initiator portion. On low vacuum force being present within the container panel following the cooling of a hot liquid in the container the initiator portion will flex inwardly to cause the control portion to invert and flex further inwardly into the container and the central portion to collapse. Raised ribs provide an additional support for the container in its collapsed state. In another embodiment the telescoping of the container back to its original position occurs when the vacuum force is released following removal of the container cap.

Abstract: A stretch wrapping machine structure contains: a rotary disc including a column on which a guide way is arranged; an abutting plate including a rotating stem and a pushing portion adjacent to the rotating stem; a hot pressing sheet including a cutter seat, a driven bar, and a press segment; a holder including a V-shaped cross section and formed in a plate shape, the holder also including an actuation member, an actuating post, an operating segment, and a third cylinder; a biasing rod including a driving peg and a push segment; a controlling unit secured on a predetermined position of one side of the column; an air blowing unit located at a predetermined position of the holder. Thereby, an object is held on the rotary disc and is packed by a plastic film quickly and easily.

Abstract: An adapter device for suctioning air out of plastic bags of a type typically used for containing fallen leaves and other yard waste for disposal comprises a screen that surrounds a space that is connectable in fluid flow relation with the suction end of the vacuum hose, a shield positioned around the screen that is capable of preventing a plastic bag from being sucked by vacuum to the screen. The mouth of the shield is sized for blocking leaves or other yard waste matted in the bag from being sucked to the screen while allowing air in the bag to flow to the screen.

Abstract: Equipment for feeding containers to a packaging machine comprising a magazine containing stacked containers. The equipment comprising a carousel device for collecting and inserting the containers into a conveyor. The magazine is positioned with its lower end slightly above that of the conveyor and suitably upstream thereof, in that a carousel device, rotating about a horizontal axis orthogonal to the direction of continuous advance of the upper run of the conveyor of the packaging machine, is located under the magazine and upstream of the conveyor, in that this carousel device comprises a plurality of suction cup units positioned in a way determined by interaction with cams, and in that the units are designed to grip the container and draw it from the base of the store by gripping the base wall by means of which these units subsequently deposit the container in a dynamic way on to the conveyor.