Abstract: A system and method to converting mechanical rotational energy of an aircraft input shaft of a transmission to electrical energy. The system includes an alternator having an inductor carried by the aircraft transmission and a magnet carried by the aircraft input shaft. The input shaft rotates the magnet in relation to the inductor, which in turn converts the mechanical rotational energy to electrical energy.

Abstract: The invention relates to a closure system on a fuel tank (2) of thermoplastics with barrier properties for hydrocarbons. The closure system comprises at least one orifice (4), with a closure cap (5) which closes the orifice (4) in a sealing manner and which cooperates in a form-fitting manner with closure means provided at the circumference of the orifice (4) and encloses at least one first sealing means between it and a tank wall (3). The closure system (1) according to the invention is distinguished in that the tank wall is sealed in the region of the orifice (4) with at least one second sealing means, which covers and/or shields a part of the tank wall surfaces exposed to hydrocarbons.

Abstract: A bi-directional drive system for turf grooming and brushing operations includes first and second accessory attachment assemblies connected to a reel deck assembly. A first drive housing connected to the first accessory attachment assembly has a first positive engagement drive member rotatable with respect to the first drive housing. A second drive housing connected to the second accessory attachment assembly has a second positive engagement drive member rotatable with respect to the second drive housing. An attachment member is releasably connected to each of the first and second positive engagement drive members and axially rotated in either a first or an opposite second axial rotation direction. First and second fasteners individually received through one of the first or second positive engagement drive members releasably couple the attachment member to the first and second positive engagement drive members. Attachment member removal is provided by releasing only the first and second fasteners.

Abstract: An induction motor system for a reel assembly of a turf maintenance vehicle includes a frame and a turf maintenance implement assembly defining a reel assembly movably connected to the frame. The reel assembly includes multiple reel blades defining a reel blade assembly. The reel blade assembly is rotatably connected to a structure of the reel assembly. Multiple induction coils are connected to the structure of the reel assembly and energized to create a magnetic field through the reel blades of the reel blade assembly thereby inducing rotation of the reel blade assembly.

Abstract: The system of the present application includes an engine and pylon arrangement for a tilt rotor aircraft in which the engine is fixed in relation to a wing portion of the aircraft, while the pylon is rotatable. The pylon supports a rotor hub having a plurality of rotor blades. Rotation of the pylon allows the aircraft to selectively fly in a helicopter mode and an airplane mode, as well as any combination thereof.

Abstract: A system and method to change a spring rate of a damper in real time. The damper includes a housing having an inner surface that forms a cavity. An elastomeric material is disposed within the cavity and fixedly attached to the inner surface of the housing. A first chamber is formed by a first end of the elastomeric material and the inner surface of the housing. The method includes restricting movement of the elastomeric material by regulating the pressure within the first chamber, which in turn changes the spring rate of the damper.

Abstract: A bi-directional drive system for turf grooming and brushing operations includes a first gear rotatably connected to a reel deck assembly. A reel shaft gear is connected to a reel shaft and rotated in a first axial rotation direction. Second and third gears are rotatably connected to the reel deck assembly. A double sided cogged belt is engaged to the reel shaft gear. An attachment member defining a turf component is rotated in the first axial rotational direction by rotation of the reel shaft gear connected to the first gear by the double sided cogged belt without rotation of the second and third gears. The turf component as a turf groomer is rotated in a second axial rotational direction opposite to the first axial rotational direction by rotation of the reel shaft gear connected to the first, second and third gears by the double sided cogged belt.

Abstract: A vibration isolator includes an upper housing and a lower housing; an upper reservoir housing defining a upper fluid chamber; a lower reservoir housing defining a lower fluid chamber; a piston spindle resiliently coupled to the upper housing with an upper elastomer member, the piston spindle being resiliently coupled to the lower housing with a lower elastomer member; an elongated portion having a tuning passage; and a tuning fluid disposed there within. The vibration isolator cancels vibratory forces at an isolation frequency. The vibration isolator is utilized in a pylon system for mounting a transmission in an aircraft. The vibration isolator is located between a pylon structure and a roof structure. The isolator includes a spherical bearing assembly that is located near a waterline location of a rotational axis of a drive shaft.

Abstract: An alignment tool for a pitch link comprises first and second pitch link retainers, wherein the distance between the retainers is adjustable to accommodate the length of the pitch link; and a measurement system for measuring the displacement of a rod end from an adjustment member of the pitch link, comprising first and second measurement reference points fixedly associated with the first and second retainers, respectively. Another alignment tool for a pitch link comprises first and second retainers having an adjustable distance there between; and a stabilization mechanism for stabilizing the tool on a surface. A method for adjusting and aligning a pitch link, in part comprising the steps of securing the pitch link to the alignment tool; measuring and recording a baseline length displacement of the pitch link; loosening the pitch link jam nuts; and adjusting the pitch link on the alignment tool to match the previously recorded displacement.

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.

Abstract: A step assembly for a vehicle can include a housing and a support member hingedly coupled to the housing with a shaft. A first locking feature can be associated with the housing while a second locking feature can be associated with the support member. A spring can be operably associated with the support member and the housing such that the spring can bias the second locking feature toward the first locking feature. The support member is configured to rotate between a stowed position and a deployed position. Further, the support member is configured as a step support and a hand hold device.

Abstract: A method of attaching a composite member to a structure. The method including forming a laminate of fabric impregnated with resin; applying heat at a first temperature to the impregnated laminate; applying vacuum at a first pressure to the impregnated laminate to degas the resin and form a degassed, impregnated laminate; positioning the degassed, impregnated laminate on a structure; and curing the degassed, impregnated laminate on the substrate by applying heat at a second temperature and by applying vacuum at a second pressure.

Abstract: According to one embodiment, a system for measuring coupling misalignment of a rotorcraft drive shaft includes a reference device and a sensor. The sensor is configured to receive a signal from the reference device indicative of a distance between the reference device and the sensor. The reference device and the sensor are configured to be disposed on opposite sides of a flexible coupling coupled to the drive shaft and disposed between the engine and the pylon. The flexible coupling is configured to rotate with the drive shaft and comprises a flexure portion configured to flex in response to a difference in alignment between the engine and the pylon. A misalignment measurement system may be configured to generate a misalignment value in response to the signal.

Abstract: An aircraft has an armor releasably attached to the body of an aircraft, an actuator connecting the armor to the body of the aircraft, and a control that, upon operation, actuates the actuator to release the armor from the body.

Abstract: A stud punch tool includes a lower frame, an upper handle pivotally attached to the lower frame, and a punching assembly attached to the lower frame and to the upper handle. The lower frame includes a body portion, a pair of ears extending upwardly therefrom, and a head portion and a handle portion extending from the body portion. The upper handle is attached to the ears. The punching assembly is connected to the head portion and is connected to the upper handle proximate to the connection of the upper handle to the ears. The upper handle can be gripped by a user for movement relative to the lower frame to cause the punching assembly to punch a hole in an associated workpiece.

Abstract: The shear bonding method is configured to facilitate bonding of structures in an out-of-autoclave environment. The shear bonding method includes bonding a plurality of frame members to the interior of a tapered tailboom. The frames are located on a bayonet type tool. An adhesive pack is applied to each frame. The bayonet type tool is inserted into the tailboom until the adhesive packs come into contact with the interior walls of the tailboom. Conductive heating tiles are applied to the tailboom. The conductive heating tiles are controlled to achieve and maintain viscosity of the adhesive packs. During this period the bayonet tool is actuated so that the frames are translated in relation to the tailboom. The heating tiles are then controlled to achieve and maintain the adhesive at a requisite curing temperature.

Abstract: According to one embodiment, a system for assessing health of an aircraft includes a receiver, a flight spectrum analyzer, and a health assessment analyzer. The receiver receives, from an aircraft, a plurality of measurements associated with two or more flight parameters. The plurality of measurements includes measurements spanning at least one period of time. The flight spectrum analyzer determines, based on a comparison of the plurality of measurements to a plurality of flight spectrum definitions, an amount of time the aircraft spent in each flight spectrum of a plurality of flight spectrums during the at least one period of time. The health assessment analyzer assesses a change in health of the aircraft over the at least one period of time based on the determination of the amount of time the aircraft spent in each flight spectrum and a plurality of spectrum health profiles.

Abstract: According to one embodiment, a clutch may be coupled between a rotor system and a power train of a rotorcraft. The clutch may be operable to disengage the rotor system from the power train during operation of the power train. A clutch control system in communication with the clutch and include a rotorcraft condition sensor operable to sense an operating condition of the rotorcraft and a control unit operable to prevent the clutch from disengaging the rotor system from the power train if the operating condition of the rotorcraft fails to satisfy a predetermined criterion.

Abstract: According to one embodiment, an aircraft part environmental stress analysis system includes a part failure repository, a part history repository, and a failure analysis engine. The part failure repository is configured to store a plurality of failure records, each failure record identifying a failed aircraft part. The part history repository is configured to store a plurality of part records, each part record storing, for a failed aircraft part, at least one measurement of an aspect of a natural environment of which the failed aircraft part was subject to. The failure analysis engine is operable to compare the plurality of failure records to the plurality of part records and identify at least one potential environmental cause of failure for a plurality of failed aircraft parts based on the comparison.

Abstract: An assembly includes a quick-release head, a tail piece and a flexible metal rod. The tail piece includes a shaft and a male coupler formed of a head, body, and flute. At least a portion of the male coupler head has a reduced outer dimension relative to an outer dimension of the body. When the male coupler is mounted in a second quick-release head or drill, a clearance space is provided between the reduced outer dimension portion and the second quick-release head or drill. During use, the assembly may undergo bending which results in significant forces applied in particular to the male coupler head. By providing the clearance space, these forces are predominantly shifted to the male coupler body, thereby reducing the likelihood that the male coupler head will shear from the remainder of the male coupler.