Abstract: An aircraft system includes a wing member and a plurality of unmanned aircraft systems selectively connectable to the wing member. The wing member has a generally airfoil cross-section, a leading edge and a trailing edge. The unmanned aircraft systems have a connected flight mode while coupled to the wing member and an independent flight mode when detached from the wing member. In the connected flight mode, the unmanned aircraft systems are operable to provide propulsion to the wing member to enable flight. The unmanned aircraft systems are operable to be launched from the wing member to perform aerial missions in the independent flight mode and are operable to be recovered by the wing member and returned to the connected flight mode. Thereafter, in the connected flight mode, the unmanned aircraft systems are operable to be resupplied by the wing member.

Abstract: The invention relates to a method for producing hollow bodies from thermoplastic material comprising the shaping of at least one tubular preform or at least two two-dimensional, web-like preforms of plasticated thermoplastic material into a substantially closed hollow body, for example in the form of a fuel tank for motor vehicles.

Abstract: Fuel tank made of thermoplastic material comprising baffle components provided therein in the form of at least one baffle element (2) comprising at least one wall portion (4) which is clamped approximately centrally and/or at the end, so that said wall portion may perform relative movements in relation to the tank, caused by splashing movements of the fuel, at least one fastening foot being provided for the clamping, the base thereof being provided with at least one through-hole, through which the fastening foot is riveted and/or welded to the tank wall (2).

Abstract: An electrical interconnect including an electrically conductive male interlock having a substantially flat base portion and a longitudinally extending locking member, and an electrically conductive female interlock having a first retention groove in a support member, the first retention groove for receiving and retaining the locking member on the support member. At least a portion of the locking member is disposed on a surface of the female interlock and slidably received in the first retention groove to form a first locked position so as to enable electrical conduction.

Abstract: An oscillating pump system includes a pump operable to circulate a fluid. The pump has a first port stage including an inlet port and an outlet port and a second port stage including a first oscillating port and a second oscillating port. An oscillator disk is disposed between the first port stage and the second port stage. The oscillator disk is rotatable relative to the inlet port, the outlet port, the first oscillating port and the second oscillating port. During rotation, the oscillator disk alternatingly routes the fluid to the inlet port from the first and second oscillating ports and alternatingly routes the fluid from the outlet port to the first and second oscillating ports, thereby generating oscillating fluid flow.

Abstract: A rotorcraft capable of a hover mode and a forward cruise mode including a fuselage, a first electric propulsion system, a second electric propulsion system, and an electric power control unit to control power to the first and second electric propulsion systems in the hover and forward cruise modes. The first electric propulsion system is a tip jet cold flow system that imparts rotation on a pair of rotor blades disposed above a top surface of the fuselage, and a first electric motor configured to drive the tip jet cold flow system. The second electric propulsion system includes a propeller disposed in the rear of the fuselage and a second electric motor configured to drive the propeller.

Abstract: An emergency lighting system (ELS) for an aircraft has a capacitor, a light emitting diode (LED) selectively powered by the capacitor, and at least one of a photoluminescent sign and a photoluminescent panel configured to receive light emitted from the LED.

Abstract: Systems, methods and computer-storage media are provided for displaying a real-time image in a cockpit of an aircraft. Use of a synthetic vision application is provided with a gradient-type feature such that a level of synthetic enhancements applied to an image may be adjusted to a synthetic vision application value that is less than 100 percent. The synthetic vision enhancement may be overlaid with the original image, according to the synthetic vision application value, to generate a modified image. Additional information may overlay the original image with the synthetic vision application such as a three-dimensional weather representation. The synthetic vision application may be used in conjunction with a high-definition camera to generate the original image. The modified image may be updated in real-time such that an updated view is continuously modified with an updated synthetic vision enhancement to provide accurate real-time views.

Abstract: The present invention discloses a venting apparatus (10) for liquid containers, in particular for an aqueous urea solution, and comprises a housing (11) that is connectable to the liquid container (40) and that has a first opening (12) to the liquid container (40) and a second opening (13) to the surrounding environment of the liquid container. The venting apparatus further comprises an air-permeable and liquid-impermeable membrane, which is arranged between the first opening (12) and the second opening (13) in the housing (11). In addition, the venting apparatus comprises a slosh baffle, which at least partly covers the first opening (12). The venting apparatus (10) according to the invention is characterized in that the housing (11) and the slosh baffle (20) are formed in one piece.

Abstract: A bearing assembly can include a top retainer; a middle retainer having a first concave spherical surface; a bottom retainer having a second concave spherical surface; a spherical ball member; and an elastomeric member coupled to the first concave spherical surface, the second concave spherical surface, and an outer surface of the spherical ball member.

Abstract: In one example embodiment, an engine flow measurement device features an engine data repository, one or more sensor units, and a measurement unit. The measurement system is configured to identify, from performance data, a maneuver performed during operation of the aircraft and to measure, for the identified maneuver, a plurality of maneuver flow values achieved during performance of the maneuver. The plurality of maneuver flow values correspond to a plurality of maneuver engine power values. Each of the plurality of maneuver flow values represent a volume of air flow through the air filter at a particular moment during performance of the maneuver.

Abstract: The present invention discloses an operating fluid container (10) made of thermoplastic material for a motor vehicle and a method for equipping an operating fluid container with a stiffening element (20).

Abstract: A pedestal assembly for receiving a pylon assembly of a tiltrotor aircraft having a helicopter mode and an airplane mode, the tiltrotor aircraft having an airframe including a fuselage and a wing. The pedestal assembly includes an inboard pedestal supported by the airframe and positioned above the wing. The inboard pedestal includes an inboard bearing assembly disposed within an inboard pillow block housing. The pedestal assembly also includes an outboard pedestal supported by the airframe and positioned above the wing. The outboard pedestal includes an outboard bearing assembly disposed within an outboard pillow block housing. The inboard and outboard bearing assemblies are operable to receive the pylon assembly therein such that the pylon assembly is rotatably mounted between the inboard and outboard pedestals to selectively operate the tiltrotor aircraft between the helicopter mode and the airplane mode.

Abstract: A propulsion system for a tiltrotor aircraft includes an engine supported by the airframe and a fixed gearbox operably coupled to the engine. Inboard and outboard pedestals are supported by the airframe and positioned above the wing. A pylon assembly is rotatably coupled between the inboard and outboard pedestals. The pylon assembly includes a spindle gearbox having an input gear, a mast operably coupled to the input gear and a proprotor assembly operable to rotate with the mast. The spindle gearbox is rotatable about a conversion axis to selectively operate the tiltrotor aircraft between helicopter and airplane modes. A common shaft, rotatable about the conversion axis, is configured to transfer torque from an output gear of the fixed gearbox to an input gear of the spindle gearbox. Each of the inboard and outboard pedestals includes a spherical bearing providing a self-aligning coupling with the pylon assembly.

Abstract: A propulsion system for a tiltrotor aircraft includes an engine supported by the airframe and a fixed gearbox operably coupled to the engine. Inboard and outboard pedestals are supported by the airframe and positioned above the wing. A pylon assembly is rotatably coupled between the inboard and outboard pedestals. The pylon assembly includes a spindle gearbox having an input gear, a mast operably coupled to the input gear and a proprotor assembly operable to rotate with the mast. The spindle gearbox is rotatable about a conversion axis to selectively operate the tiltrotor aircraft between helicopter and airplane modes. A common shaft, rotatable about the conversion axis, is configured to transfer torque from an output gear of the fixed gearbox to the input gear of the spindle gearbox. Each of the inboard and outboard pedestals includes a journal bearing that provides a stiff coupling with the pylon assembly.

Abstract: A method of inspecting a component using a film overlay including providing the component, the component having a first surface, a core, and a second surface; positioning a film overlay having a reference indicia and a structural indicia on the first surface of the component; aligning the reference indicia on the film overlay with a reference feature on the component; positioning a testing probe on a top surface of the film overlay so the probe is aligned with the structural indicia; and transmitting a signal from the probe through the film overlay, the first surface, the core, and the second surface.

Abstract: In accordance with one embodiment of the present application, an actuation system is configured for actuation of an airfoil member with a flap mechanism. The actuation system can include an upper drive tape and a lower drive tape, each partially wrapped around a first bearing and second bearing. An inboard frame can be actuated by at least one linear actuator. Similarly, an outboard frame can be actuated by at least one linear actuator. The inboard frame is coupled to the upper drive tape, while the outboard frame is coupled to the lower drive tape. An actuation of the inboard frame and outboard frame in a reciprocal manner acts move a flap input lever reciprocally upward and downward. A flap mechanism is configured to convert the movement of the flap input lever into rotational movements of the airfoil member.

Abstract: A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators.

Abstract: A rotary system including a grip having an opening forming a first bridge for receiving a centrifugal force bearing that faces inwardly towards the rotor mast. A rotor blade couples to the grip and a pitch horn positioned outside the opening pitches the rotor blade during flight. A bearing assembly attaches the first bridge to the yoke and controls blade forces exerted against the hub assembly during flight.

Abstract: A method of manufacturing a door skin and a fuselage wall having a doorway and a member extending into the doorway for abutting the door includes placing a first sheet of uncured composite material on a mold plate to define the door and fuselage skin, disposing an insert over the first sheet overlapping a desired periphery of the door, placing a second sheet of uncured composite material on a peripheral portion of the insert and over the first sheet adjacent the peripheral portion of the insert to form the member, curing the sheets and bonding the sheets together adjacent the insert during the cure, removing the insert from between the sheets after cure, and separating the door skin from the wall skin after cure by moving a cutting tool through the first sheet and without penetrating the second sheet around the desired periphery of the door. An assembly for manufacturing the door skin and a fuselage wall is also discussed.