Abstract: A composite core includes a plurality of tubes, each the plurality of tubes comprising a plurality of fibers disposed in a polymeric matrix. Adjacent tubes of the plurality of tubes are adhesively bonded to one another along sides of the adjacent tubes. A method of making a composite core includes the steps of providing a plurality of tubes, each of the plurality of tubes including a plurality of fibers disposed in a polymeric matrix, and adhesively bonding adjacent tubes of the plurality of tubes along sides of the adjacent tubes. A method of making a composite core such that a removable band is included in the core, the removable band being configured to be removable through a procedure subsequent to the cure of the composite core, thereby producing gaps in the core.

Abstract: A method for applying adhesive to sides of a flange, such as in rotorcraft connection joints, includes attaching an intermediate member to an edge of a flange and flowing adhesive in gaps between sides of the flange and inner edges of a double lap joint element by inserting the flange with the intermediate member into the double lap joint element.

Abstract: A regime recognition system for an aircraft has a regime engine configured to identify a sub-regime performance of the aircraft only after having identified a top tier or top level regime performance that can include the sub-regime performance.

Abstract: A rotorcraft includes a proprotor coupled to the wing and a pusher propeller. Power is transferred from the proprotor to the pusher propeller with the use of a torque splitter. The torque splitter contains several gears, including a ring gear which rotates on an axis. The power outputted by the torque splitter is increased or decreased by selectively slowing down the rotation of the ring gear by the use of a clamp.

Abstract: A rotary system and method to control feathering movement of a rotor blade. The system having a yoke arm configured to rotate a rotor blade. A first bearing and a second bearing are utilized to secure the rotor blade to the yoke arm and are configured to restrict longitudinal and transverse movement, while allowing feathering movement of the rotor blade relative to yoke arm.

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: According to one embodiment, a rotorcraft yoke comprises a plurality of arms. The plurality of arms, in combination, comprise a plurality of fibrous plies extending continuously throughout all of the plurality of arms.

Abstract: A propeller blade assembly including a propeller blade having a leading edge, and a trailing edge extending between a tip and a hub, and an electrically conductive band extending longitudinally on either or both of the leading edge and trailing edge. The electrically conductive band secured to the leading edge of the propeller serves as an entry point on the aircraft and conductive channel into the airframe thereby avoiding the potentially damaging effect of the lightening on the carbon fiber composite propeller.

Abstract: Systems and methods are provided for task-based health data monitoring relating to aircraft components of aircraft within an aircraft fleet. One method includes identifying health data of an aircraft component for potential monitoring based upon a condition indicator provided by a health and usage monitoring system, establishing a Review Item for the health data of the aircraft component having an initial data review state of New Data, thereby creating a Review Task, generating images of the Review Item for display and receiving an indication to change the data review state of the Review Item from New Data to Watch Data, receiving new health data relating to the aircraft component from the health and usage monitoring system and automatically resetting the data review state of the Review Item from Watch Data to New Data responsive to the receipt of the new health data, thereby creating a new Review Task.

Abstract: The invention relates to a ventilating device (2) for liquid containers (1), in particular for liquid containers (1) for an aqueous urea solution, including a housing (3) which can be mounted at an opening of the liquid container (1) and has a first opening (4) to the liquid container (1) and a second opening (5) to the surroundings of the liquid container (1), a diaphragm (6) which is arranged within the housing (3), is permeable to air, is impermeable to liquid and is configured in such a way that a deformation of the diaphragm (6) takes place by a pressure change in the liquid container (1), as a result of which the volume within the housing (3) within the diaphragm (6) changes, with the result that the displaced volume leaves the housing (3) via the second opening (5) to the surroundings of the liquid container (1). Furthermore, the invention relates to a liquid container (1) having a ventilating device (2) according to the invention.

Abstract: The device is configured for moving a fluid within a gearbox. In one illustrative embodiment, the device includes a base portion coupled to a rotatable member within the gearbox. An inlet portion of the device is configured to draw the fluid from a reservoir portion of the gearbox. The device is configured to utilize a centrifugal force for moving the fluid from the inlet portion toward the base portion along an interior surface of a conical portion. In another illustrative embodiment, the device includes a conical portion having an external threaded portion configured to capture a fluid during a rotation of the device. In such an embodiment, the threaded portion is configured to utilize a centrifugal force for moving the fluid captured by the threaded portion along an exterior surface of the conical portion.

Abstract: The invention provides an air and fluid cleaning system for propelling a cleaning fluid and air onto a vehicle vision device such as a vehicle camera system. The cleaning system comprises at least one fluid nozzle aimed at the camera; at least one cleaning fluid pump fluidly connected to both a fluid supply conduit and a cleaning fluid source; at least one air nozzle aimed at the vehicle camera; and at least one telescopic air jet fluidly connected to the air nozzle, hydraulically connected to the fluid supply conduit, and operated by the fluid pressure provided by the cleaning fluid pump; such that during a first operation time interval only cleaning fluid is propelled onto the vehicle camera and during a second operation time interval only an air jet burst is propelled onto the vehicle camera. The invention further includes a method for cleaning a vehicle camera exposed to ambient.

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: 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: A conditional switched rate filter system having a two stage digital filter to remove noise from the input signal. The first stage of the filter effectively removes the random noise from the input signal higher in frequency (cut-off frequency) than outside the characteristic response of the closed loop system. The second stage of the filter is used to filter out noise that is at same frequency response as the closed loop system.

Abstract: A rotorcraft includes a body, a rotor blade, and a power train coupled to the body and operable to rotate the rotor blade. The power train includes an engine, a gearbox in mechanical communication with the engine, and a driveshaft in mechanical communication with the gearbox. The rotorcraft also includes a sensor operable to detect a rotorcraft parameter, and a lubrication flow calculation unit operable to receive the rotorcraft parameter, generate the flow rate based on the rotorcraft parameter, and transmit the flow rate to a lubrication system configured to deliver lubricant to the gearbox at the transmitted flow rate.

Abstract: In some embodiments, a rotorcraft flight control actuator includes a driving member configured to receive mechanical energy from a power source, a driven member, a magnetorheological (MR) fluid disposed between the driving member and the driven member and configured to transmit a variable amount of mechanical energy from the driving member to the driven member, an output member configured to be coupled between the driven member and a flight control device of a rotor system, and a magnetic circuit configured to deliver a magnetic field towards the MR fluid, the magnetic circuit configured to vary the strength of the magnetic field in response to inputs.

Abstract: A control system having a series of control loops for determining the upper and lower cyclic limit increments due to the contribution of collective pitch in rotorcraft based at least on nacelle angle and airspeed.

Abstract: Systems, methods and computer-storage media are provided for use of navigational aids. Three-dimensional graphical representations of flight plans, flight paths, waypoints, etc., may be displayed to improve situational awareness. Additionally, dynamic monitoring of airports, waypoints, traffic, etc., may be performed so that real-time updates are available to users. The real-time updates will not only include updated location information and any relevant navigational markers (e.g., updated waypoints, new traffic, etc.) but will also include detailed information related to the navigational markers such as a distance from the marker, an airspeed of the marker (if applicable), and the like.

Abstract: In some aspects, a master cylinder assembly for vertical lift aircraft is configured to move pressurized fluid through a conduit in response to applied movement of an input lever. A low pressure relief valve can be connected to a first conduit to limit pressure to a low level. An isolation valve can be connected to the first conduit and configured to isolate the low pressure relief valve from the conduit when engaged. A high pressure relief valve can be connected to a second fluid conduit to limit pressure to a high level. In some aspects, a rotor brake actuator is fluidly connected to the first conduit and the second conduit and configured to engage a rotor brake in response to hydraulic fluid pressure.