Abstract: Systems and methods for sender profile and/or recipient profile disambiguation and/or confirmation are disclosed. In instances where a sender profile is not indicated by a user sending a communication from a communal device, heuristic data may be utilized to infer the sender profile. Similar heuristic data may also be used when selection of the sender profile is associated with a low confidence level. Heuristic data may also be used to infer the recipient profile when the user does not indicate the recipient profile or when selection of the recipient profile is associated with a low confidence. Various confirmations may result from the sender and recipient profile disambiguation.

Abstract: Threshold voltage shift values, or TVS values, are calibrated for a non-volatile memory unit including strings of memory cells organized into memory pages, the memory pages being organized into blocks. The calibration involves a read operation to read a given page of the memory pages, based on given one or more TVS values for the given page. In response to a read failure of the read operation, the calibration determines one or more corrected TVS values based on one or more reference TVS values of one or more reference pages of the memory pages. The calibration subsequently performs a read operation to read the given page based on the one or more corrected TVS values. This calibration exploits TVS values of reference pages to determine corrected TVS values of the failing page, instead of finding appropriate TVS values by repeatedly re-reading the failing page.

Abstract: A high-frequency chest wall oscillation (HFCWO) system includes a garment configured to be worn around a chest of a user. At least one fluid pod is housed by the garment and is configured to receive a fluid. The at least one fluid pod includes a housing configured to be pulsated by the fluid.

Abstract: Color quantification of chemical test pads and titration of analytes can be performed under different lighting conditions. In one embodiment, the lighting condition is estimated under which a digital image is captured and utilized to select a set of reference colors from which the quantified color is compared to determine the titration. In another embodiment, a plurality of comparisons are made with different lighting conditions with the result having the highest confidence level being selected to determine the titration.

Abstract: One embodiment includes a rotary aircraft, including: a main drive rotor; an aircraft body mechanically coupled to the main drive rotor; and first and second flight assist wings passively rotatably coupled to the aircraft body.

Abstract: Color quantification of chemical test pads and titration of analytes can be performed under different lighting conditions. In one embodiment, the lighting condition is estimated under which a digital image is captured and utilized to select a set of reference colors from which the quantified color is compared to determine the titration. In another embodiment, a plurality of comparisons are made with different lighting conditions with the result having the highest confidence level being selected to determine the titration.

Abstract: An aircraft includes a fuselage airframe and a wing airframe that is subject to flight loads. The fuselage airframe includes fore/aft floor beams having a plurality of floor intercostals laterally extending therebetween and fore/aft roof beams with a plurality of roof intercostals laterally extending therebetween. Each of a plurality of cabin frames extends generally vertically between respective floor and roof beams. The wing airframe includes forward and aft wing spars with a plurality of wing ribs extending therebetween. At least one fuel tank, that is configured to contain a pressurized fuel such as pressurized hydrogen fuel, integrally forms at least a portion of one of the beams, the intercostals, the frames, the spars and/or the ribs such that the fuel tank is subject to the flight loads.

Abstract: A diagnostic test kit is provided. In one aspect, the diagnostic test kit includes a diagnostic test including a test region for indicating a test result. The diagnostic test kit also includes a scan surface including one or more control markings. The one or more control markings are representative of one or more predetermined test results for the diagnostic test. The diagnostic test can include a lateral flow immunoassay test, and the one or more control markings can include one or more lines. The one or more lines can vary in at least one of thickness, color, hue, and reflectivity.

Abstract: A rotorcraft has a horizontal stabilizer movable about an axis of rotation and a horizontal stabilizer control system configured to control the horizontal stabilizer to at least one of move the rotorcraft into a minimum drag position, maintain the aircraft in a minimum drag position, efficiently achieve a maneuver, enter efficient autorotation, and maintain efficient autorotation.

Abstract: A high frequency chest wall oscillation therapy system includes an air pulse generator. The air pulse generator includes control circuitry and a fluid chamber carrying a fluid. A motor is configured to generate compression and expansion of the fluid in the fluid chamber to generate pressurized fluid. A pressure sensor detects a pressure of the pressurized fluid in the fluid chamber. A garment includes at least one fluid bladder defining a pressurizable chamber adapted to receive the pressurized fluid from the fluid chamber to provide a force of high frequency pressure oscillation to a patient's chest wall.

Abstract: A disconnector trigger bar safety for a semi-automatic pistol is provided and includes a trigger bar having a firing pin end having a sear surface and a cam surface. The trigger bar has an inside surface disposed adjacent to the cam surface. A disconnector is moveable from an inward position to an outward position and has a cam surface to receive the cam surface of a trigger bar. An inset portion is provided on the trigger bar at the firing pin end that has a bottom surface. A protuberance on the side of the disconnector is provided to mate with the inset portion of the trigger bar. The protuberance has a top surface matable to the bottom surface of the inset portion. Rearward movement of the trigger bar causes the cam surface of the trigger bar to slide against the cam surface of the disconnector to move the firing pin end of the trigger bar downwardly. The disconnector moves to provide clearance for the trigger bar to move upward.

Abstract: A rotorcraft having pusher propeller generated power during autorotations. The rotorcraft has an engine powered mode and an autorotation mode. The rotorcraft includes an engine and a drivetrain configured to receive torque and rotational energy from the engine in the engine powered mode. A main rotor system is coupled to the drivetrain and is rotatable to generate lift and forward thrust for the rotorcraft in the engine powered mode. A pusher propeller is coupled to the drivetrain and is rotatable to generate forward thrust for the rotorcraft in the engine powered mode. In the autorotation mode, the pusher propeller is aerodynamically driven responsive to airflow therethrough and the drivetrain is configured to receive torque and rotational energy from the pusher propeller, thereby providing power to the main rotor system.

Abstract: A rotor system for a rotorcraft includes a rotor hub having a plurality of blade grips coupled thereto. Each blade grip has a rotor blade coupled thereto. A fairing is disposed at least partially around the rotor hub. Each of a plurality of lead-lag dampers is coupled to at least a respective one of the blade grips. Each lead-lag damper has a damper heat exchanger and a fluid pump operably associated therewith. A fairing heat exchanger is in fluid communication with the damper heat exchangers and the fluid pumps. Each lead-lag damper is configured to drive the respective fluid pump responsive to damping operations to pump a cooling fluid from the respective damper heat exchanger to the fairing heat exchanger.

Abstract: A method of simulating an aircraft one-engine inoperative (“OEI”) event includes operating a supplemental power unit (“SPU”) at a first SPU power level less than an SPU contingency power rating, operating a primary engine at a first primary-engine power level, reducing the primary-engine power level to less than the first primary-engine power level, and maintaining a sum of the primary-engine power level and the SPU power level at a power level substantially equal to the SPU contingency power rating.

Abstract: An aircraft includes a fuselage airframe and a wing airframe that is subject to flight loads. The fuselage airframe includes fore/aft floor beams having a plurality of floor intercostals laterally extending therebetween and fore/aft roof beams with a plurality of roof intercostals laterally extending therebetween. Each of a plurality of cabin frames extends generally vertically between respective floor and roof beams. The wing airframe includes forward and aft wing spars with a plurality of wing ribs extending therebetween. At least one fuel tank, that is configured to contain a pressurized fuel such as pressurized hydrogen fuel, integrally forms at least a portion of one of the beams, the intercostals, the frames, the spars and/or the ribs such that the fuel tank is subject to the flight loads.

Abstract: An exemplary electric distributed propulsion system includes two or more rotors that are individually controlled by the rotational speed of associated motors, an input control connected to the associated motors to provide rotational speed control to the two or more rotors to produce a desired net thrust, and a logic connected to the input control and the associated motors, the logic for controlling speed and direction of the two or more rotors to achieve the desired net thrust and to avoid a motor speed condition.

Abstract: A rotor system for a rotorcraft includes a rotor hub having a plurality of blade grips coupled thereto. Each blade grip has a rotor blade coupled thereto. A fairing is disposed at least partially around the rotor hub. Each of a plurality of lead-lag dampers is coupled to at least a respective one of the blade grips. Each lead-lag damper has a damper heat exchanger and a fluid pump operably associated therewith. A fairing heat exchanger is in fluid communication with the damper heat exchangers and the fluid pumps. Each lead-lag damper is configured to drive the respective fluid pump responsive to damping operations to pump a cooling fluid from the respective damper heat exchanger to the fairing heat exchanger.

Abstract: A rotor system includes a drive hub, a set of rotor blades extending radially from the drive hub, and a set of tension-torsion straps connecting the rotor blades to the drive hub. The drive hub has a rotor mast opening extending along a mast axis. The rotor system is configured to rotate about the mast axis. The drive hub further has a set of mounting slots for mounting the tension-torsion straps. The mounting slots are arranged along a circle around the drive hub, each mounting slot extending through the drive hub along a respective mounting axis. The mounting axis of each of the mounting slots is biased relative to the mast axis. The tension-torsion straps are mounted to the drive hub at their corresponding mounting slots.

Abstract: An exemplary anti-torque system for a helicopter includes two or more electric fans rotatably mounted on a tail boom, the two or more electric fans rotatable about a longitudinal axis of the tail boom.

Abstract: A method for analyzing a diagnostic test may include receiving an image depicting a diagnostic test, wherein the diagnostic test comprises a test region indicating a test result, validating quality of the image, locating a test region image portion of the image depicting the test region of the diagnostic test; and predicting the test result based on the test region image portion. Furthermore, a method for facilitating analysis of a diagnostic test may include receiving one or more images depicting one or more control markings on a scan surface, wherein the one or more control markings are representative of one or more predetermined test results for the diagnostic test, and verifying detection of the one or more control markings in the one or more images using at least one computer vision technique.