Abstract: A rotor hub assembly includes a yoke and a high capacity laminated (HCL) bearing, comprising layers of elastomeric material and layers of metal. The HCL bearing is affixed to the yoke to prevent separation of the HCL bearing from the yoke.

Abstract: A system comprises an image sensor comprising an array of infrared sensors operable to capture an image of a scene, an integration timing circuit variably controlling an integration time of the infrared sensors, a readout integrated circuit (ROIC) operable to generate signals from the infrared sensors corresponding to the captured image of the scene, and an automatic gain control operable to applied a gain to the generated signals. The system further comprises a dynamic range compensation controller operable to receive image parameters corresponding to the generated signals, compare the received image parameters to target image parameters, and generate an integration timing signal for controlling the integration timing circuit.

Abstract: A system is provided for processing documents. In particular, the system is incorporates a feeder for feeding documents to a device for further processing of the documents. For instance, the system finds particular application in the field of document imaging in which a variety of documents of varying sizes and orientation are to be fed to an imaging system, such as a document scanner. The system may provide an input mechanism for easily identifying a characteristic of one of the documents and the system may include features for handling packets of documents.

Abstract: A method and apparatus for processing documents are provided. The apparatus includes a feeder for receiving a packet of a plurality of documents and separating the documents to serially feed the documents to a scanner. A retard adjacent the feeder is operable in first and second positions. In the first position the retard forms a nip with the feeder so that the retard is operable to impede the progress of one or more documents in the packet while the feeder feeds one of the documents in the packet. In the second position, the retard is spaced apart from the feeder to form a gap between the feeder and the retard. The system further includes a sensor for detecting a characteristic of the documents in a packet indicative of whether the number of documents in the packet exceeds a predetermined threshold. A drive mechanism automatically drives the retard pad between the first and second positions in response to the detected characteristic.

Abstract: A system is provided for processing documents. In particular, the system is incorporates a feeder for feeding documents to a device for further processing of the documents. For instance, the system finds particular application in the field of document imaging in which a variety of documents of varying sizes and orientation are to be fed to an imaging system, such as a document scanner. The system may provide an input mechanism for easily identifying a characteristic of one of the documents and the system may include features for handling packets of documents.

Abstract: A wing airframe for a wing of a tiltrotor aircraft includes a wing airframe core assembly and a wing skin assembly disposed on the wing airframe core assembly. The wing skin assembly includes an outer skin and a damping sublayer, the damping sublayer interposed between the outer skin and the wing airframe core assembly. The tiltrotor aircraft includes a pylon assembly subject to aeroelastic movement during forward flight. The wing is subject to deflection in response to the aeroelastic movement of the pylon assembly. The damping sublayer reduces the deflection of the wing, thereby stabilizing the wing during forward flight.

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 tension-torsion strap, for example for a rotor aircraft, including a continuous length of carbon fiber tow arranged in multiple loops to form an elongated member extending between opposing ends and a flexible cover encasing the carbon fiber tow.

Abstract: Methods and systems for implementing artificial intelligence enabled preparation end-pointing are disclosed. An example method at least includes obtaining an image of a surface of a sample, the sample including a plurality of features, analyzing the image to determine whether an end point has been reached, the end point based on a feature of interest out of the plurality of features observable in the image, and based on the end point not being reached, removing a layer of material from the surface of the sample.

Abstract: An embodiment of the indention includes a passive, fiber optic, thermal insulator. The thermal insulator includes an inner sleeve defining a central access port. The thermal insulator includes an outer sleeve concentric to the inner sleeve. The inner sleeve and the outer sleeve are joined sufficient to define an annular void. The thermal insulator includes a first insulator located in the annular void. Optionally, the apparatus includes at least one optical fiber secured in the central access port.

Abstract: In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, an adapter ring, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the swashplate and the adapter ring, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the swashplate and the adapter ring, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.

Abstract: An attachment system is provided for attaching furring strips to joists, each such joist having a bottom surface, an upper surface and a sidewall. The attachment system for each furring strip including a fastener having a shaft and a head, the fastener secured to the sidewall of the joist in a position vertically displaced from the bottom surface. At least one length of wire is provided with a mid-portion and two free ends, the mid-portion being looped around the fastener. The free ends are wrapped around the furring strip and fastened to each other to securely hold the furring strip to the floor joist.

Abstract: A vibration attenuator for an aircraft has first and second coaxial spinners configured for rotation about a mast axis and relative to a rotor. Upper and lower weights of each spinner are spaced radially from the axis and positioned 180 degrees from each other about the axis. The weights of each spinner are spaced from each other a distance parallel to the mast axis, each weight rotating about the mast axis in a different plane. The spinners rotate together relative to the rotor at a selected angular rate and are selectively rotatable relative to each other between a minimum-moment configuration, in which the upper weight of each spinner is angularly aligned with the lower weight of the other spinner, and a maximum-moment configuration, in which the upper weights are angularly aligned and the lower weights are angularly aligned, producing a whirling moment about the mast axis as the spinners rotate.

Abstract: In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, a phase adapter fulcrum, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the plurality of actuators and the swashplate, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the plurality of actuators and the plurality of lower pitch links, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.

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 and independently change pitch. In the airplane mode, the proprotor blades have a first in-plane frequency greater than 2.0/rev.

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 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: An attachment system is provided for attaching furring strips to joists, each such joist having a bottom surface, an upper surface and a sidewall. The attachment system for each furring strip including a fastener having a shaft and a head, the fastener secured to the sidewall of the joist in a position vertically displaced from the bottom surface. At least one length of wire is provided with a mid-portion and two free ends, the mid-portion being looped around the fastener. The free ends are wrapped around the furring strip and fastened to each other to securely hold the furring strip to the floor joist.

Abstract: In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, an adapter ring, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the swashplate and the adapter ring, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the swashplate and the adapter ring, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.

Abstract: In one embodiment, a rotor hub comprises a hub plate, a yoke for attaching a plurality of rotor blades, a plurality of yoke support bearings, and a plurality of cushioned damper bearings for attaching a plurality of dampers.