Abstract: A rotor blade locking assembly for locking a rotor blade in a deployed position. The rotor blade locking assembly comprises a locking mechanism configured to be coupled to a blade grip. The locking mechanism comprises a latch and an actuator configured to cause the latch to move between an unlocked position and a locked position. The assembly comprises a locking plate configured to be coupled to the rotor blade. The locking plate comprises a bearing surface configured to bear against a contact surface of the latch, when the latch is in the locked position.

Abstract: An aircraft nacelle is disclosed and includes a first fan cowl and a second fan cowl. An opening is defined in an exterior surface of the first fan cowl. The aircraft nacelle also includes a blade, a latch mechanism, an arm, and a linkage assembly operably connecting the arm to the blade. The blade is moveable along between a stowed position and a deployed position. The latch mechanism is moveable between a latched position an unlatched position where a portion of the latch mechanism obstructs a path of movement of the blade. The arm is unable to move from an extended position where a portion of the arm extends through the opening in the exterior surface of the aircraft nacelle into a retracted position within an interior volume of the aircraft nacelle when the blade is in the deployed position and the latch mechanism is in the unlatched position.

Abstract: A tri-hybrid yoke including a center ring connected to a CF fitting connected to flexure arms. An inboard centrifugal force bearing assembly connects to the CF fitting and a grip. An outboard shear bearing assembly connects to the flexure arm and the grip. In use, the center ring and the CF fittings carry the centrifugal force at a position inboard of the flexure arm.

Abstract: The aircraft includes a rotor. The rotor includes a plurality of rotor blades. The aircraft further includes a non-rotating aircraft component. A proximity sensor is disposed with at least one of the non-rotating aircraft component and the rotor blades. A flight control computer is electrically coupled to the proximity sensor.

Abstract: The aircraft includes a rotor. The rotor includes a plurality of rotor blades. The aircraft further includes a non-rotating aircraft component. A proximity sensor is disposed with at least one of the non-rotating aircraft component and the rotor blades. A flight control computer is electrically coupled to the proximity sensor.

Abstract: A multi-zone food holding bin has a continuous food supporting surface with multiple food holding zones. Each food holding zone is independently controllable so that different food temperatures may be maintained in adjacent food holding zones.

Abstract: A bearing assembly for coupling a proprotor blade to a yoke in a proprotor system. The bearing assembly is positionable within an inboard pocket of a blade arm of the yoke. The proprotor system is operable for use on a tiltrotor aircraft having helicopter and airplane flight modes. The bearing assembly includes a centrifugal force bearing and a shear bearing having an inboard beam coupled therebetween. The centrifugal force bearing has a mating surface, a lateral movement constraint feature and at least one radially extending anti-rotation feature. The inboard beam has a mating surface in a contact relationship with the mating surface of the centrifugal force bearing, a lateral movement constraint feature operably associated with the lateral movement constraint feature of the centrifugal force bearing and at least one radially extending anti-rotation feature that corresponds with the at least one radially extending anti-rotation feature of the centrifugal force bearing.

Abstract: A gimbal joint may employ a plurality of wear sleeves, each disposed between a pin or pin receptive bore of a first structure and a corresponding bore or pin of a second structure and between another pin or bore of the first structure and a corresponding bore or pin of a third structure. Each of these structures may be adapted to rotate in a single plane, with one structure adapted to also tilt about a first axis, and one other structure adapted to tilt about a second axis. Each integral flanged wear sleeve may comprise a right circular hollow cylindrical body portion, which may be interiorly sized to be retained on one of the pins and externally sized to be retained in one of the pin receptive bores, and a flange portion may radiate from one end of the cylindrical body portion.

Abstract: Methods, systems, and apparatus, including computer programs encoded on a computer storage medium, for a multi-peer telepresence communications system. In one aspect, a method includes formulating a geometry of an environment based on sensor data collected from the environment by at least one sensor; capturing, with a camera, a plurality of video frames of the environment and associating each of the captured video frames with spatial transform data of the camera within the geometry of the environment; providing the video frames and associated camera position data to a remote peer; compositing, by the remote peer, the video frames and associated camera position data to generate a local composite; and displaying, on the remote peer, a three-dimensional augmented reality of the environment based on the local composite.

Abstract: A conveyor belt includes a conveyor belt slat having a coupling mechanism extending from a bottom of a base of the conveyor belt slat.

Abstract: A multi-zone food holding bin has a continuous food supporting surface with multiple food holding zones. Each food holding zone is independently controllable so that different food temperatures may be maintained in adjacent food holding zones.

Abstract: A conveyor belt includes a conveyor belt slat having a coupling mechanism extending from a bottom of a base of the conveyor belt slat.

Abstract: Implementations of semiconductor packages may include: a digital signal processor having a first side and a second side and an image sensor array, having a first side and a second side. The first side of the image sensor array may be coupled to the second side of the digital signal processor through a plurality of hybrid bond interconnect (HBI) bond pads and an edge seal. One or more openings may extend from the second side of the image sensor array into the second side of the digital signal processor to an etch stop layer in the second side of the digital signal processor. The one or more openings may form a second edge seal between the plurality of HBI bond pads and the edge of the digital signal processor.

Abstract: A conveyor belt includes a conveyor belt slat having a coupling mechanism extending from a bottom of a base of the conveyor belt slat.

Abstract: A control valve has a trim assembly to condition the flow of fluid through the control valve and, in some applications, to provide guidance for a valve plug. The trim assembly has a lattice structure formed of a plurality of triply periodic surfaces that form a plurality of passages that extend between an inner surface of the circumferential wall and an outer surface of the circumferential wall.

Abstract: A proprotor system for a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a yoke having a plurality of blade arms with inboard pockets. A centrifugal force and shear bearing assembly is disposed in each of the inboard pockets of the yoke. Each of a plurality of proprotor blades is coupled to the yoke by one of the bearing assemblies such that each proprotor blade has a pitch change degree of freedom about a pitch change axis and a tilting degree of freedom about a focal point. Each bearing assembly includes a centrifugal force bearing coupled to the yoke, a shear bearing coupled to the yoke and an inboard beam coupled between the centrifugal force bearing and the shear bearing. Each inboard beam is coupled to a respective proprotor blade.

Abstract: A folding rotor blade assembly for an aircraft a yoke, an inboard beam coupled to the yoke, an inboard centrifugal force bearing coupled to the inboard beam, a grip coupled to the inboard beam, an outboard bearing housing coupled to the grip, and a rotor blade pivotally coupled to the grip by a blade fold bolt that is positioned outboard of the outboard bearing housing.

Abstract: A load control system may include control devices for controlling power provided to an electrical load. The control devices may include a control-source device and a control-target device. The control-target device may control the power provided to the electrical load based on digital messages received from the control-source device. The control devices may include a load control discovery device capable of sending discovery messages configured to discover control devices within a location. The discovered control devices may be organized by signal strength and may be provided to a network device to enable association of the discovered control devices within a location. The discovery messages may be transmitted within an established discovery range. The discovery range may be adjusted to discover different control devices. Different control devices may be identified as the load control discovery device for discovering different control devices.

Abstract: A multi-piece inboard beam assembly for use in a rotor blade assembly of a rotorcraft. The inboard beam assembly includes an inboard beam connected to an inboard beam fitting with an anti-rotational connection. The inboard beam is connected to a yoke via bearings and the inboard beam fitting is connected to a grip in a double shear condition. In use, the grip, the inboard beam fitting with the double shear connection, the inboard beam, a centrifugal force bearing held by the inboard beam, and the yoke carry the centrifugal force created upon rotation of the rotor blade assembly.