Abstract: Disclosed are a lithium transition metal oxide and a lithium secondary battery, in which a ratio of average particle diameter D50 of the lithium transition metal oxide to average particle diameter D50 of a transition metal precursor for preparation of the lithium transition metal oxide satisfies the condition represented by Equation 3 below: 0 < Average ? ? particle ? ? diameter ? ? D ? ? 50 ? ? of ? ? lithium ? ? transition ? metal ? ? oxide Average ? ? particle ? ? diameter ? ? D ? ? 50 ? ? of ? ? transition ? ? metal ? precursor < 1.2 .

Abstract: An aircraft includes an airframe with first and second wings having a fuselage extending therebetween. A propulsion assembly is coupled to the fuselage and includes a counter-rotating coaxial rotor system that is tiltable relative to the fuselage to generate a thrust vector. First and second yaw vanes extend aftwardly from the fuselage. A flight control system is configured to direct the thrust vector of the coaxial rotor system and control movements of the yaw vanes. In a VTOL orientation of the aircraft, differential operation of the yaw vanes and/or differential operations of first and second rotor assemblies of the coaxial rotor system provide yaw authority for the aircraft. In a biplane orientation of the aircraft, collective operation of the yaw vanes provides yaw authority for the aircraft.

Abstract: In an embodiment, a rotorcraft includes: a flight control computer configured to: receive a first sensor signal from a first aircraft sensor of the rotorcraft; receive a second sensor signal from a second aircraft sensor of the rotorcraft, the second aircraft sensor being different from the first aircraft sensor; combine the first sensor signal and the second sensor signal with a complementary filter to determine an estimated vertical speed of the rotorcraft; adjust flight control devices of the rotorcraft according to the estimated vertical speed of the rotorcraft, thereby changing flight characteristics of the rotorcraft; and reset the complementary filter in response to detecting the rotorcraft is grounded.

Abstract: A touch panel and a method of manufacturing the touch panel are provided. The touch panel includes a substrate comprising a wiring area and a sensor area, a sensing pattern located on a surface of the substrate in the sensor area, and a wiring line located on the surface of the substrate in the wiring area and electrically connected to the sensing pattern. The sensing pattern includes a plurality of first fine metal lines arranged irregularly in a mesh, and a first photosensitive layer pattern residue located between at least two of the first fine metal lines.

Abstract: Various embodiments of smart thermostats are presented herein. A smart thermostat can include a thermostat housing defining a rounded front aperture and having a sidewall. The smart thermostat can include a capacitive touch strip that senses a plurality of gestures. The smart thermostat can include an electronic display. The electronic display may be caused to display icons arranged in a graphical arc. The smart thermostat may include a reflective cover positioned such that the electronic display is viewed through the reflective cover.

Abstract: Various embodiments of smart devices are determined herein. A smart device can include a housing and an electronic display. The smart device can further include a cover, housed by the housing, through which the electronic display is visible. The cover can include a glass layer, wherein the glass layer is the outermost layer of the cover that is adjacent an ambient environment of the smart home device. The cover can further include an optical coating layer, deposited directly onto a surface of the glass layer, that comprises a plurality of sublayers. The optical coating layer can include alternating non-metallic oxide layers having different refractive indexes. The sublayers can vary in thickness such that the optical coating layer reflects light from the ambient environment through the glass layer.

Abstract: The present disclosure relates to a multi-type filter, and in particular, to a multi-type filter comprising: a cavity filter provided in any one (hereinafter, referred to as a “reference cavity”) among a plurality of cavities formed in a housing to be open to one side; and dielectric resonator filters respectively provided in at least two cavities adjacent to the reference cavity (hereinafter, referred to as “adjacent cavities”), wherein, to control the notch characteristics between the cavity filter and the at least two dielectric resonator filters according to windows formed by cutting of portions of partition walls between the reference cavity and the adjacent cavities to be in communication with each other, the windows are provided at different positions, which is advantageous in that the cross-coupling design is very easy without the need to include a metal crossbar and the like for separate notch formation.

Abstract: A solid-state ion conductor includes a compound of Formula 1: Li3a+b?(c*N)NaClbXc??Formula 1 wherein, in Formula 1, X is an anion having an average oxidation state of n and is ?3>n??1, and is at least one of Br, I, F, O, S, or P; and 1?a?4, 1?b?3, 0?c?3, and 4.8?(a+b+c)?5.2.

Abstract: The present disclosure relates to a nanoscale thin film structure and implementing method thereof, more specifically nanoscale thin film structure of which target structure is designed with quantized thickness and a method to implement the nanoscale thin film structure by which the performance of the manufactured nanodevice can be implemented the same as the designed performance, thereby applicable to high sensitivity high performance electronic/optical sensor devices.

Abstract: Disclosed are a cathode active material for a lithium secondary battery including a core containing lithium composite metal oxide, and a coating layer disposed on the core, containing a mixture of lithium oxide, tungsten oxide, boron oxide and phosphorus oxide, and having an amorphous phase, and a lithium secondary battery including the same.

Abstract: The present invention relates to a system and a method for determining a stroke based on a voice analysis. According to the present invention, voice data of subjects are collected to extract and analyze voice onset times to determine stroke patients based on voices. The system for determining a stroke generates and collects voice data from test subjects reading a predetermined word that includes a plosive sound. The system for determining a stroke extracts and calculates voice onset times from the voice data to calculate probability parameters for the voice onset times of each of a normal group and a stroke patient group. The system for determining a stroke uses a set of probability parameters to determine an integration section, and calculates probabilities of being in the normal group and the stroke patient group. The system for determining a stroke applies the calculated probabilities to the Bayes theorem to determine whether the subjects are stroke patients.

Abstract: In an embodiment, a method includes: obtaining a first signal from a first sensor of a rotorcraft, the first signal indicating measured angular velocity around a first axis of the rotorcraft; filtering the first signal with a lag compensator to estimate angular position around the first axis of the rotorcraft; and adjusting flight control devices of the rotorcraft according to the estimated angular position and the measured angular velocity around the first axis of the rotorcraft, thereby changing flight characteristics of the rotorcraft around the first axis of the rotorcraft.

Abstract: An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft has an airframe including first and second wings with a fuselage extending therebetween. A propulsion assembly is coupled to the fuselage and includes a counter-rotating coaxial rotor system that is tiltable relative to the fuselage to generate a thrust vector. A flight control system is configured to direct the thrust vector. In the VTOL orientation, the first wing is forward of the fuselage, the second wing is aft of the fuselage and the coaxial rotor system is configured to provide thrust in line with a yaw axis of the aircraft. In the biplane orientation, the first wing is below the fuselage, the second wing is above the fuselage and the coaxial rotor system is configured to provide thrust in line with a roll axis of the aircraft.

Abstract: A propulsion assembly for an aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The propulsion assembly includes a housing coupled to the fuselage of the aircraft. A coaxial rotor system includes a first rotor assembly and a second rotor assembly that are rotatable about a common axis of rotation. The first rotor assembly counter-rotates relative to the second rotor assembly. A motor assembly is operably associated with the coaxial rotor system. The motor assembly provides torque and rotational energy to the first rotor assembly and the second rotor assembly. A gimbal assembly couples the coaxial rotor system to the housing such that the coaxial rotor system is tiltable relative to the fuselage to generate a thrust vector.

Abstract: A method for separating and refining 1-butene with a high purity and a high yield from a raffinate-2 stream. The method includes: feeding raffinate-2 to a first distillation column; obtaining heavy raffinate-3 from a lower part of the first distillation column; recovering an upper part fraction containing 1-butene from an upper part of the first distillation column; feeding the upper part fraction containing 1-butene to a second distillation column; recovering a first lower part fraction rich in 1-butene from a lower part of the second distillation column and light raffinate-3 from an upper part of the second distillation column. Heat of the upper part fraction recovered from the upper part of the first distillation column is fed to the lower part of the second distillation column through a first heat exchanger. Thus, 1-butene is obtained with high purity and high yield while maximizing an energy recovery amount by double-effect distillation.

Abstract: An aircraft includes an airframe with first and second wings having a fuselage extending therebetween. A propulsion assembly is coupled to the fuselage and includes a counter-rotating coaxial rotor system that is tiltable relative to the fuselage to generate a thrust vector. First and second yaw vanes extend aftwardly from the fuselage. A flight control system is configured to direct the thrust vector of the coaxial rotor system and control movements of the yaw vanes. In a VTOL orientation of the aircraft, differential operation of the yaw vanes and/or differential operations of first and second rotor assemblies of the coaxial rotor system provide yaw authority for the aircraft. In a biplane orientation of the aircraft, collective operation of the yaw vanes provides yaw authority for the aircraft.

Abstract: An aircraft includes an airframe with first and second wings having a fuselage extending therebetween. A propulsion assembly is coupled to the fuselage and includes a counter-rotating coaxial rotor system that is tiltable relative to the fuselage to generate a thrust vector. Tail assemblies are coupled to wingtips of the first and second wings each having an elevon that collectively form a distributed array of elevons. A flight control system is configured to direct the thrust vector of the coaxial rotor system and to control movements of the elevons such that the elevons collectively provide pitch authority and differentially provide roll authority for the aircraft in the biplane orientation. In addition, when the flight control system detects an elevon fault, the flight control system is configured to perform corrective action responsive thereto at a distributed elevon level or at a coordinated distributed elevon and propulsion assembly level.