Abstract: An engine cooling system for a rotorcraft includes an engine having an engine cooling circuit, a hydraulic pump powered by the engine to pump hydraulic fluid, and a hydraulic circuit in fluid communication with the hydraulic pump and the engine cooling circuit, the hydraulic circuit including at least one hydraulic-powered component. The hydraulic pump is adapted to pump the hydraulic fluid through both the hydraulic circuit and the engine cooling circuit, thereby cooling the engine.

Abstract: A testing apparatus, inspection system, and method for through-transmission ultrasonic testing. The testing apparatus includes a yoke having a support member with a pair of hinge joints, each hinge joint located on an end of the support member; a pair of arms extending from the support member having a hinge end and a pivotable transducer end, each arm being coupled to the hinge joint at the hinge end and extending to the pivotable transducer end; a pair of transducer support members disposed on each of the pivotal transducer ends; and a tension member connected to the pair of arms for aligning the pair of transducer support members during testing.

Abstract: The invention relates to a method for producing a container (2) from a thermoplastic, having at least one surround (4), provided in the container wall (1), for a container opening. The surround (4) comprises a structure behind which parts of the container wall (1) extend and/or which is penetrated by said parts. The method is carried out using a multi-part blow mold that has at least two mold parts, each having at least one cavity, wherein the surround is placed as an insert in the cavity (10) of the blow mold (7). The method comprises pressing the preform that has been forced into the cavity (10) into the structure of the surround (4) by means of a tool which is brought to bear on the preform (12) on the side of the preform facing away from the cavity (10).

Abstract: A method, system, and device for diagnosing an anomaly of a monitored component in a drive train, the method including: obtaining original data based on samples of a tachometer signal; processing the original data to obtain rotational information; processing the original data to produce a sine spectrum; determining complex magnitudes of the sine spectrum; removing dominate torsional mode residuals from the complex magnitudes of the sine spectrum to produce a frequency spectrum; and determining a condition indicator from the frequency spectrum.

Abstract: There is a method, system, and device for diagnosing an anomaly of a monitored component in a drive train, the method including obtaining original data based on samples of a vibration signal and a tachometer signal; generating a time synchronous average vibration signal; processing the time synchronous average vibration signal to produce a frequency-domain spectrum; determining the complex magnitudes of the frequency-domain spectrum; selecting a sub-synchronous band of the complex magnitudes of the frequency-domain spectrum to generate a sub-synchronous spectrum; and determining the mean of the sub-synchronous spectrum to generate a condition indicator.

Abstract: A soft-in-plane proprotor system for a tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub, a plurality of proprotor blades and a plurality of blade support assemblies coupling the proprotor blades with the hub. Each blade support assembly includes a flapping bearing coupled to the hub and a yoke having first and second longitudinal sections with outboard grip members and an inboard arcuate section connecting the first and second longitudinal sections and coupled to the flapping bearing. A lead-lag damper is coupled between the hub and an inboard station of the respective proprotor blade. A twist shank is coupled between the outboard grip members of the yoke and an outboard station of the respective the proprotor blade. The twist shank defines a virtual lead-lag hinge outboard of the yoke and coincident with the respective pitch change axis.

Abstract: A soft-in-plane proprotor system for a tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub, a plurality of proprotor blades and a plurality of loop yokes, each coupling one of the proprotor blades with the hub and each including first and second longitudinal sections extending between inboard and outboard arcuate sections and a bearing assembly disposed between the inboard and outboard arcuate sections of each loop yoke. Each bearing assembly includes a flapping bearing disposed generally within the inboard arcuate section of the respective loop yoke and coupled to the hub, a lead-lag damper coupled to the hub, a centrifugal force bearing disposed generally within the outboard arcuate section of the respective loop yoke and a blade anchor coupled between the lead-lag damper and the centrifugal force bearing. The blade anchor is also coupled to the respective proprotor blade.

Abstract: A gear shaft allows a ceramic bearing to be used in environments where gear steel is desirable for driving a gear. The gear shaft includes a gear region and a bearing region. A bearing can be disposed about the bearing region of the gear shaft. A gear can be disposed about the gear region of the gear shaft. The bearing includes a ceramic material. The gear region of the gear shaft includes gear steel, whereas the bearing region of the gear shaft includes a bearing-region material that has a coefficient of thermal expansion (CTE) that is close to the CTE of the ceramic material.

Abstract: A bearing liner allows a bearing to be mounted to a bearing housing even where the coefficients of thermal expansion of the bearing and the housing are different. The bearing liner includes a body portion and a mounting portion. The body portion has a cylindrical substrate that extends about a longitudinal axis of the bearing. The mounting portion includes mounting tabs that extend from the body portion of the liner. The mounting tabs allow the liner to be fixed to the housing and to the bearing. The mounting tabs are configured to flex relative to the body portion of the liner so as to allow for thermal expansion and contraction of the housing relative to the bearing while still securing the bearing to the housing.

Abstract: A drivetrain subassembly includes a clutch portion and a gear shaft portion connected by an integrated inner race/gear shaft member. The clutch portion includes a sprag clutch configured to transfer torque from an engine to a rotor system while allowing the rotor system to continue to rotate in the event of an engine failure. The inner race of the clutch portion is integrally formed with the gear shaft of the gear shaft portion of the subassembly. The gear shaft is configured to rotate about the longitudinal axis of the sprag clutch for transmitting torque from the sprag clutch to a downstream drivetrain component.

Abstract: A yoke for providing a centrifugal force retention load path between a proprotor blade and a hub of a soft-in-plane proprotor system operable for use on a tiltrotor aircraft. The yoke includes a continuous loop having a longitudinal axis and first and second longitudinal sections extending between inboard and outboard arcuate sections. A flapping bearing receiving region is disposed at least partially within the inboard arcuate section to an interior of the continuous loop. A centrifugal force bearing receiving region is disposed at least partially within the outboard arcuate section to the interior of the continuous loop. The continuous loop is formed from a composite material having a plurality of double bias material plies and a plurality of unidirectional material plies such that the number of unidirectional material plies is greater than the number of double bias material plies.

Abstract: A proprotor system for tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub and a plurality of proprotor blades coupled to the hub such that each proprotor blade is operable to independently flap relative to the hub about a flapping axis and independently change pitch about a pitch change axis. The proprotor blades have a first in-plane frequency less than 1.0/rev.

Abstract: A cross tube for a helicopter skid landing gear, including a monolithic metallic tube having a central portion extending transversely between two end portions with longitudinal central axes of the central portion and of the end portions being located in a plane, where the central portion has inner and outer heights, the end portions each have inner and outer heights, and the inner and outer heights of one of the central portion and the end portion are respectively greater than the inner and outer heights of the other of the central portion and the end portion. A skid tube with two portions with cross-sections having one or both of different orientations with respect to one another and different dimensions with respect to one another, and a method of forming a structural tube for a helicopter skid landing gear are also provided.

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: The present disclosure provides vehicle that includes an auxiliary storage compartment. In various embodiments, the auxiliary storage compartment includes a front wall, a pair of opposing sidewalls and a back wall that is disposed laterally between the sidewalls. The auxiliary storage compartment additionally includes a floor disposed between the front wall and the back wall. In various embodiments, at least one of the sidewalls comprising an access door movable between an Open position, wherein access to the auxiliary storage compartment is provided via the open access door, and a Closed position, wherein the closed access door defines the respective sidewall.

Abstract: The present application provides a drive link for a constant-velocity joint of an aircraft rotor, the link connecting a drive hub attached to a driveshaft to a rotor yoke. The link comprises a leading bearing connected to the drive hub, a trailing bearing connected to the yoke, a central portion between the bearings, and a tension loop connecting the bearings. The tension loop is formed from a composite material and is formed as a continuous band. The tension loop transfers drive forces from the leading bearing to the trailing bearing for driving the yoke in rotation with the driveshaft.

Abstract: A system and method of increasing the control authority of redundant stability and control augmentation system (SCAS) actuators by utilizing feedback between systems such that one system may compensate for the position of a failed actuator of the other system. Each system uses an appropriate combination of reliable and unreliable inputs such that unreliable inputs cannot inappropriately utilize the increased authority. Each system may reconfigure itself when the other system actuator fails at certain positions so that the pilot or other upstream input maintains sufficient control authority of the aircraft.

Abstract: A hinge has a door interface comprising a serrated surface and an oversized hole, a bolt at least partially extending into the oversized hole, and a washer disposed on the bolt and captured between the door interface and a head of the bolt, the washer comprising a serrated surface facing toward the serrated surface of the door interface. The oversized hole has a diameter selected to allow significant radial movement of the bolt within the oversized hole.

Abstract: The invention relates to a method for manufacturing a fuel tank on the basis of thermoplastic material, the method comprising the following method steps: producing semifinished products in sheet form from a fiber composite material with a matrix of thermoplastic material, laminating the semifinished products with a laminate that comprises at least one barrier layer for hydrocarbons, heat-treating the laminated semifinished products until the thermoplastic material plasticizes, thermoforming the plasticized semifinished products in a thermoforming mold to form shells and joining the shells to form an essentially closed tank.

Abstract: A system determines wireless network performance. A wireless instrument is configured to send, receive and measure received wireless signals in a monitored area. A master controller connected with the wireless instrument forms a distributed wireless network testing solution. The master controller is configured to send and receive wireless signals with the wireless instrument, measure received wireless signals and perform an analysis of the wireless signals to determine a radio frequency environment performance of the distributed wireless network based on the wireless signals.