Abstract: Aspects of the present invention relate to thermal management systems for head-worn computers.

Abstract: The present invention provides a semiconductor device enabling efficient compression without increasing the circuit size and a processing method using the semiconductor device. According to an embodiment, an image processor includes: a coding circuit to perform image processing on a target image divided into a plurality of tiles, the image processing being performed on each of the tiles; a determination circuit to determine whether a tile boundary is included in the area of an image block serving as a unit of compression of the target image; and a compression circuit to compress the image block image-processed by the coding circuit, according to a determination result of the determination circuit.

Abstract: A data storage system includes a non-volatile memory array controlled by a controller that records a number of a plurality of like operations targeting a first block among a plurality of blocks in the non-volatile memory array. In response to the number of the plurality of like operations satisfying a threshold, the controller initiates a mitigation read request by recording an identifier of a second block in a high priority request in a mitigation data structure. The controller initiates other mitigation read requests by recording identifiers of other blocks of the non-volatile memory in low priority requests in the mitigation data structure. The controller preferentially services the high priority request from the mitigation data structure over the low priority requests, where servicing the high priority request includes performing a mitigation read to the second block.

Abstract: Methods and apparatus for controlling aircraft flight control surfaces are disclosed. An example apparatus includes a flight control surface controller to move a control surface of an aircraft to a target position via at least one of a first actuator or a second actuator associated with the control surface based on a command input received by the flight control surface controller. The flight control surface controller to: obtain a flight characteristic of the aircraft; compare the flight characteristic to a flight characteristic threshold; in response to a first comparison result, cause the first actuator to move the control surface to the target position based on the command input without moving the second actuator; and in response to a second comparison result, cause the first actuator and the second actuator to move the control surface to the target position based on the command input.

Abstract: A data storage system includes a non-volatile memory array controlled by a controller that records a number of a plurality of like operations targeting a first block among a plurality of blocks in the non-volatile memory array. In response to the number of the plurality of like operations satisfying a threshold, the controller initiates a mitigation read request by recording an identifier of a second block in a high priority request in a mitigation data structure. The controller initiates other mitigation read requests by recording identifiers of other blocks of the non-volatile memory in low priority requests in the mitigation data structure. The controller preferentially services the high priority request from the mitigation data structure over the low priority requests, where servicing the high priority request includes performing a mitigation read to the second block.

Abstract: Methods, apparatus, and articles of manufacture for a distributed aircraft actuation system are disclosed. An example apparatus includes a collection engine to obtain first monitoring information corresponding to a first set of control surfaces of an aircraft, the first set including a first control surface on a first side of the aircraft and a second control surface on a second side of the aircraft, the second side opposite the first, and obtain second monitoring information corresponding to a second set of control surfaces of the aircraft, the second set including a third control surface on the first side and a fourth control surface on the second side.

Abstract: A method and system for parsing a tree-adjoining grammar (TAG). A grammar parser reads in a sequence of tokens and determines if the sequence is valid in the grammar. It uses a matrix-vector representation of the TAG and performs parsing one token at a time. The innovation is the use of matrices and vectors to efficiently store the grammar and perform the parsing using these matrices and vectors.

Abstract: Systems, methods, and apparatus for reducing the probability of the occurrence of an aircraft's tailstrike are disclosed. In one or more embodiments, a disclosed method for reducing a probability of an occurrence of a tailstrike for an aircraft comprises determining whether a tailstrike has a first probability of occurring by using tailstrike related data. The method further comprises producing a tactile warning to a pilot of the aircraft, when at least one processor determines that a tailstrike has the first probability of occurring. In at least one embodiment, the determining of whether a tailstrike has a first probability of occurring comprises determining whether an aircraft pitch attitude is greater than a first probability threshold by using the tailstrike related data; and determining that a tailstrike has the first probability of occurring, when the aircraft pitch attitude is greater than the first probability threshold.

Abstract: To provide a semiconductor device which suppresses a delay in processing. The semiconductor device is equipped with a plurality of read units which read data stored across a plurality of banks in a memory having the banks, and an access method managing section which, when one of the read units reads the data, determines a read start bank number being a bank number to start reading according to operation situations of the read units excepting the one read unit, and instructs the determined read start bank number to the one read unit.

Abstract: Systems for compensating for force fighting in multi-actuator systems are provided. A drive controller unit comprises a first feedforward controller in communication with a first actuator and configured to receive a drive command signal. A first feedback regulator is configured to output a first feedback input into the first feedforward controller, and to receive as input a first actuator position and a first actuator force. The drive controller unit further comprises a second feedforward controller in communication with a second actuator and configured to receive the drive command signal. A second feedback regulator is configured to output a second feedback input into the second feedforward controller, and to receive as input a second actuator position and a second actuator force. The drive controller unit utilizes both feedforward controllers and both feedback regulators to minimize force fighting while driving a common aileron.

Abstract: A sewing ring for prosthetic heart valves that is connected and configured to pivot outward. A biocompatible fabric covering surrounds at least a portion of the sewing ring, and the ring may be exclusively connected to a stent with the fabric. The sewing ring may be generally planar and of uniform thickness, or may be of varying thickness. The fabric may be used to encompass both the stent and the sewing ring, and may be a single piece. A seam may be provided in the fabric as a discrete pivoting line. The sewing ring may be convertible between bi-stable positions. The ring may extend outward in a frusto-conical shape so as to enable inversion between a position facing the inflow end of the valve and a position facing the outflow end of the valve. The sewing ring may have a compliant insert having a celled construction defined by outer walls and inner ribs. A method of implantation, and a method of assembly of the heart valve is also provided.

Abstract: Methods, apparatus, and articles of manufacture for a distributed aircraft actuation system are disclosed. An example apparatus includes a collection engine to obtain first monitoring information corresponding to a first set of control surfaces of an aircraft, the first set including a first control surface on a first side of the aircraft and a second control surface on a second side of the aircraft, the second side opposite the first, and obtain second monitoring information corresponding to a second set of control surfaces of the aircraft, the second set including a third control surface on the first side and a fourth control surface on the second side.

Abstract: Methods and apparatus for controlling aircraft flight control surfaces are disclosed. An example apparatus includes a flight control surface controller to move a control surface of an aircraft to a target position via at least one of a first actuator or a second actuator associated with the control surface based on a command input received by the flight control surface controller. The flight control surface controller to: obtain a flight characteristic of the aircraft; compare the flight characteristic to a flight characteristic threshold; in response to a first comparison result, cause the first actuator to move the control surface to the target position based on the command input without moving the second actuator; and in response to a second comparison result, cause the first actuator and the second actuator to move the control surface to the target position based on the command input.

Abstract: Methods and apparatus for reacting rotary actuator and control surface loads into a wing structure using reaction links. The apparatus incorporates a structural interface feature that can facilitate a change of the component(s) in the load loop, such as the path connecting a control surface to a fixed aircraft structure via a rotary actuator. In particular, the structural interface between the rotary actuator and the rear spar of a wing can be tuned for stiffness to achieve an optimized load path that reacts actuator and control surface loads back into the wing structure. An actuator integration objective can be met for any rotary actuator using an integration method which tolerates wing and/or hinge line deflection.

Abstract: Aspects of the present invention relate to mechanical hinge system for a head-worn computer.

Abstract: Methods and apparatus for reacting rotary actuator and control surface loads into a wing structure using reaction links. The apparatus incorporates a structural interface feature that can facilitate a change of the component(s) in the load loop, such as the path connecting a control surface to a fixed aircraft structure via a rotary actuator. In particular, the structural interface between the rotary actuator and the rear spar of a wing can be tuned for stiffness to achieve an optimized load path that reacts actuator and control surface loads back into the wing structure. An actuator integration objective can be met for any rotary actuator using an integration method which tolerates wing and/or hinge line deflection.

Abstract: A method and apparatus for positioning a control surface. A desired position for the control surface associated with an aerodynamic aircraft structure is identified. The control surface is moved to the desired position using an electronically controlled rotary actuator system located inside of the aerodynamic aircraft structure, wherein a shape of the aerodynamic aircraft structure with the electronically controlled rotary actuator system has a desired aerodynamic performance.

Abstract: Provided is a method of epitaxial deposition, which involves dry-etching a semiconductor substrate with a fluorine containing species and exposing the dry-etched substrate to hydrogen atoms, prior to epitaxially depositing a semiconductor layer to the surface of the substrate.

Abstract: An aircraft control system includes pilot and co-pilot flight control systems that each include a first shaft mechanically coupled to and displaced apart from a second shaft, the shafts defining and being rotatable about independent longitudinal axes. A connecting link enables rotation of one of the first shafts to rotate a corresponding one of the second shafts. A position transducer is mechanically coupled to each shaft and configured to communicate an electrical signal corresponding to the rotation of the respective shaft. A flight control unit electrically communicates with the position transducers and is configured to (a) receive the electrical signal from each position transducer, (b) detect a failure of the flight control system by detecting differences in the position transducers' electrical signals, and (c) communicate the electrical signal from the position transducer to a flight control surface actuation system to compensate for the detected failure.

Abstract: A prosthetic heart valve for implant in a human. The valve includes a wireform with undulating inflow cusps and outflow commissure posts to which flexible leaflets attach and coapt in a flow area. Each leaflet may drape over the top of the wireform in the cusp area, but have tabs that each extend underneath the wireform at the commissure posts to be secured along with a tab of an adjacent leaflet. The prosthetic heart valve may also be a dual-wire wireform, with the leaflets sandwiched therebetween. One wireform may be larger than the other, with the leaflets extending over the smaller wireform. The smaller wireform may have commissures that bend radially outward from the larger wireform to provide structure to which the leaflet tabs attach.