Abstract: A rotor system for rotor aircraft comprises a rotor hub comprising a plurality of rotor blades, a rotatable rotor mast coupled to the rotor hub, a swashplate assembly comprising a non-rotating ring engaged with a rotatable ring, a plurality of pitch links mechanically coupling the rotatable ring to the plurality of rotor blades, and a swashplate actuator system. The rotatable ring is configured to rotate with the rotor mast, and the non-rotating ring is configured to engage and guide the rotatable ring. The pitch links are configured to control the pitch angle of each rotor blade. The swashplate actuator system consists of: a first actuator and a second actuator, where the first actuator and the second actuator are mechanically coupled to a stationary surface and the non-rotating ring.

Abstract: A method of preserving rotor speed during a one engine inoperative operation of an rotorcraft, the method can include: detecting a failure of a first engine; monitoring an engine parameter associated with a second engine; using a computer processor to compare the engine parameter to an engine limit; and commanding a decrease collective pitch command when the engine parameter is within a predefined range of the engine limit.

Abstract: In some embodiments, a control manager is disposed between the rotor system and the flight control inceptor. The control manager is configured to receive control commands wirelessly from a ground control station, translate the control commands into one or more axes associated with the flight control inceptor, and transmit the translated control commands to the rotor system in place of the instructions received from the pilot via the flight control inceptor.

Abstract: According to one example embodiment, a method of assessing use of an aircraft component installed on an aircraft includes assessing whether received one or more measurements are sufficient to support calculation of a usage-based change in remaining useful life and, if the one or more measurements are sufficient to support calculation of the usage-based change in remaining useful life, calculating the usage-based change in remaining useful life based on the received one or more measurements and changing the second remaining useful life of the aircraft component by the difference between the default change in remaining useful life and the usage-based change in remaining useful life.

Abstract: According to one example embodiment, a method of assessing reliability of an aircraft component includes identifying, aboard an aircraft, a first probability of failure of the aircraft component installed on the aircraft. One or more measurements representative of at least one load applied against the aircraft component are received. Determined, aboard the aircraft, is a second probability of failure of the aircraft component based on the first probability of failure and the received one or more measurements representative of the at least one load applied against the aircraft component, the second probability of failure representing a probability of failure of the aircraft component after application of the at least one load.

Abstract: According to one embodiment, a spring tension adjustment device for adjusting tension in a spring includes a rotation feature and a plurality of spring-attachment features. The rotation feature defines a first axis of rotation. Each spring-attachment feature is configured to receive one end of a spring, each spring-attachment feature being located at a different distance from the rotation feature.

Abstract: The invention relates to a method for producing plastics containers (15) from thermoplastics with inserts (13) which, by exploiting the heat of plasticization, are connected during shaping of the plastics container (15) by a material bond and/or interlocking connection to the container wall (140), wherein the method provides the use of at least one opening (26) on the insert (13), which opening forms a melt duct or melt inlet and/or melt passage for plasticized or plastic material of the container wall (140), wherein the method is distinguished in that the opening (26) is monitored as a reference opening (26) by optical and/or sensory means during the production of the connection, wherein the degree of penetration of the opening (26) with thermoplastic from the container wall (140) is used as a measure of the quality of the connection.

Abstract: The invention described herein provides a flight crew with an easier and more intuitive way to control and monitor flight-control surfaces. Specifically, the invention displays all flight-control surfaces on a touch-screen display device located in an aircraft cockpit. The invention includes graphical and numerical position indicators to continuously display actual position information for flight-control surfaces. Additionally, the invention allows a flight crew to make flight-control surface adjustments through the touch-screen device. The invention further includes an engine performance indicator and a mode controller configured to display autopilot modes and to receive autopilot mode selections. A method is presented for controlling an aircraft flight-control surface via a touch screen device. The method includes receiving an indication of a flight-control surface and enabling selection of a position change.

Abstract: A system and method to tilt coaxial counter-rotating rotor hub assemblies relative to a fuselage. The system includes a first rotor hub assembly and a second rotor hub assembly spaced apart from the first hub assembly and carried by the fuselage. The method includes pivotally attaching the first rotor hub assembly and the second rotor hub assembly to a pivot joint and thereafter tilting the first rotor hub assembly and the second rotor hub assembly about the pivot joint with a driver.

Abstract: A rotorcraft vibration isolation system includes a plurality of liquid inertia vibration elimination (LIVE) units mounted on a first rotorcraft surface, an accumulator mounted on a second rotorcraft surface at a location that is remote from locations of the plurality of LIVE units, and a fluid passage to connect the accumulator to the plurality of LIVE units in parallel. The fluid passage has sufficient length to traverse between the location of the accumulator and each location of each LIVE unit. During rotorcraft operation, the second rotorcraft surface experiences lesser periodic vibration than the first rotorcraft surface.

Abstract: A method of manufacturing a core stiffened structure includes orienting the plurality of core wafers in a non-uniform pattern onto a first face sheet, the non-uniform pattern producing non-uniform spacing between adjacent core wafers; assembling a second face sheet onto the plurality of wafers; and curing an adhesive to create a bond between the plurality of wafers, the first face sheet, and the second face sheet.

Abstract: The invention relates to a device (6) for pressure-dependent opening of a suction intake (10), comprising a suction jet pump (11), comprising a feed line (12), an outlet line (13) and the suction intake (10); a valve body (15), displaceably arranged inside the feed line (12) in the delivery direction (14) of the suction jet pump (11) and having an effective area (16) exposed to the feed pressure of the suction jet pump (11); and a spring element (17), arranged between the feed line (12) and the valve body (15), for applying a force in opposition to the feed pressure inside the feed line (12); wherein the effective area (16) of the valve body (15), and the spring element (17) are designed so that the valve body (15) closes the suction intake (10) so that it is fluid-tight below a predefined pressure inside the feed line (12) and opens said intake when the predefined pressure inside the feed line (12) is exceeded.

Abstract: This description relates to a strapped windshield assembly for a rotorcraft. In some implementations, the rotorcraft includes an airframe, a windshield, and a plurality of independent straps connected to the airframe and the windshield, the straps operative to move independently with respect to one another. The independent movement of the straps allow relative movement of portions of the windshield in response to a strike. In some implementations, the straps are spaced every 4-6 inches along an edge of the windshield. In some implementations, the straps are over an edge of the windshield. The straps can have a modulus of elasticity of 8-12 millions of pounds per square inch (MSI). The windshield can include polycarbonate material.

Abstract: According to one embodiment, a pilot assistance system includes a trim assembly and a trim assembly control system. The trim assembly is operable to communicate with a pilot control device and operable to apply a force against the pilot control device in resistance of a command received from a pilot via the pilot control device. The trim assembly control system is in communication with the trim assembly, configured to identify a first pilot control device position relative to a reference pilot control device position, and configured to instruct the trim assembly to apply a cueing force against the pilot control device if the pilot control device is positioned proximate to the first pilot control device position.

Abstract: A fiber reinforced composite structure includes multiple plies of pre-impregnated fiber reinforced material. Consecutive plies are layered such that the fibers of one ply are at 90 degrees relative to the fibers of a proximate ply, and such that the fibers of each ply are oriented at positive or negative 45 degrees with respect to a reference plane of the fiber reinforced composite structure. In a method for fabricating a fiber reinforced composite structure, pre-impregnated fiber reinforced composite plies are layered into a tool layup. Each ply is cut on the bias at either plus 45 degrees or minus 45 degrees. The bias angles of the layered plies alternate one relative to the next. The layered plies are cured after layering.

Abstract: An apparatus for testing for the susceptibility of an aircraft system to radio frequencies comprises a wireless module for generating radio signals that sweep each of the 2.4 GHz frequency band and the 5 GHz frequency band. A first amplifier is configured for amplifying signals in the 2.4 GHz band, and a second amplifier is configured for amplifying signals in the 5 GHz band. The apparatus comprises at least one dual band antenna for transmitting the signals in each of the 2.4 GHz and the 5 GHz bands.

Abstract: In some embodiments, a redundant control system includes first and second control systems, having first and second clutches, and a shared clutch system. The shared clutch system may include a shared shaft configured to receive mechanical energy from a shared power source, a first shared clutch corresponding to the first clutch and configured to receive mechanical energy from the shared shaft, and a second shared clutch corresponding to the second clutch and configured to receive mechanical energy from the shared shaft. A first linkage provides mechanical communication between an output of the first clutch, an output of the first shared clutch, and a first output device in mechanical communication with the rotor system. A second linkage provides mechanical communication between an output of the second clutch, an output of the second shared clutch, and a second output device in mechanical communication with the rotor system.

Abstract: The invention refers to a fuel vapor storage and recovery apparatus comprising a housing (2) defining at least first and second compartments, at least one compartment being filled with an adsorbent material, at least one tank port (5) connectable to a fuel tank vent line, at least one atmospheric vent port (7), an outer housing member (8) defining a first outer compartment (3), an inner housing member defining a second inner compartment (4), the first outer compartment (3) encompassing the second inner compartment (4), wherein the inner housing member (9) is fitted into the outer housing member (8) at one end of the housing (2), such that a wall (13) of the inner housing member (9) engages an inner wall of the outer housing member (8) and wherein the inner housing member (9) and the outer housing member (8) are sealed against each other by means of a closure cap (14).

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: A method of modifying a workpiece includes providing a workpiece, determining a load stress profile associated with a load condition, the load stress profile comprising a load stress greater than a material stress limit of the workpiece, determining a residual stress profile, the residual stress profile comprising a residual stress less than the material stress limit of the workpiece, and providing the workpiece with the residual stress profile, wherein a sum of the load stress and the residual stress is less than the material stress limit of the workpiece.