Abstract: According to the embodiment of the present disclosure, an organo tin compound is represented by the following Chemical Formula 1: In Chemical Formula 1, L1 and L2 are each independently selected from an alkoxy group having 1 to 10 carbon atoms and an alkylamino group having 1 to 10 carbon atoms, R1 is a substituted or unsubstituted aryl group having 6 to 8 carbon atoms, and R2 is selected from a substituted or unsubstituted linear alkyl group having 1 to 4 carbon atoms, a branched alkyl group having 3 to 4 carbon atoms, a cycloalkyl group having 3 to 6 carbon atoms, and an allyl group having 2 to 4 carbon atoms.

Abstract: A method of manufacturing a multilayer metal plate by electroplating includes a first forming operation of forming one of a first metal layer and a second metal layer on a substrate by electroplating, wherein the second metal layer is less recrystallized than the first metal layer, the second metal layer is comprised of nanometer-size grains, and the second metal layer has a higher level of tensile strength than the first metal layer; and a second forming operation of forming, by electroplating, a third metal layer not formed in the first forming operation on a surface of one of the first metal layer and the second metal layer formed in the first forming operation.

Abstract: A display apparatus having a mura compensation function includes a mura memory in which compensation data corresponding to coefficient values of a mura compensation equation is stored; and a mura compensation circuit configured to perform mura compensations on display data by using the mura compensation equation to which the compensation data has been applied, wherein the coefficient values are set so that the mura compensation equation has been fit to have a curve that satisfies known difference values of selected gray levels, a first estimation difference value of a first estimation gray level higher than the selected gray levels, and a second estimation difference value of a second estimation gray level lower than the selected gray levels, and wherein the compensation data comprises the coefficient values of the mura compensation equation in which all of the known difference values of the selected gray levels, the first estimation difference value, and the second estimation difference value have a differen

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: In accordance with an embodiment, a method of operating an aircraft includes operating the aircraft in a first mode including determining an attitude based on a pilot stick signal, where a translational speed or an attitude of the aircraft is proportional to an amplitude of the pilot stick signal in the first mode; transitioning from the first mode to a second mode when a velocity of the aircraft exceeds a first velocity threshold; and operating the aircraft in the second mode where the output of the rate controller is proportional to the amplitude of the pilot stick signal.

Abstract: Technology provided herein relates in part to methods, processes, machines and apparatuses for non-invasive assessment of genomic nucleic acid instability and genomic nucleic acid stability.

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: Provided herein are methods, processes and apparatuses for non-invasive assessment of genetic variations.

Abstract: In accordance with an embodiment, a method of operating an aircraft includes operating the aircraft in a first mode including determining an attitude based on a pilot stick signal, where a translational speed or an attitude of the aircraft is proportional to an amplitude of the pilot stick signal in the first mode; transitioning from the first mode to a second mode when a velocity of the aircraft exceeds a first velocity threshold; and operating the aircraft in the second mode where the output of the rate controller is proportional to the amplitude of the pilot stick signal.

Abstract: In accordance with an embodiment, a method of operating an aircraft includes operating the aircraft in a first mode including determining an attitude based on a pilot stick signal, where a translational speed or an attitude of the aircraft is proportional to an amplitude of the pilot stick signal in the first mode; transitioning from the first mode to a second mode when a velocity of the aircraft exceeds a first velocity threshold; and operating the aircraft in the second mode where the output of the rate controller is proportional to the amplitude of the pilot stick signal.

Abstract: Provided herein are methods, processes and apparatuses for non-invasive assessment of genetic variations.

Abstract: Technology provided herein relates in part to methods, processes and apparatuses for non-invasive assessment of genetic variations.

Abstract: Provided herein are methods, processes and apparatuses for non-invasive assessment of genetic variations that make use of decision analyses. The decision analyses sometimes include segmentation analyses and/or odds ratio analyses.

Abstract: A rotorcraft is described and includes an inertial measurement unit (“IMU”) sensor mounted to the rotorcraft, the IMU sensor oriented relative to the rotorcraft such that a roll attitude of the rotorcraft occurs about a Z-axis and has a range of ±90 degrees, a pitch attitude of the rotorcraft occurs about an X-axis and has a range of ±180 degrees, and a yaw attitude of the rotorcraft occurs about a Y-axis and has a range of ±180 degrees.

Abstract: Technology provided herein relates in part to methods, processes, machines and apparatuses for non-invasive assessment of genomic nucleic acid instability and genomic nucleic acid stability. The method comprises providing a set of genomic portions each coupled to a copy number alteration quantification for a test sample, wherein the genomic portions comprises portions of a reference genome to which sequence reads obtained for nucleic acid from a test sample obtained from the subject have been mapped, and the copy number alteration quantification coupled to each genomic portion has been determined from a quantification of sequence reads mapped to the genomic portion; and determining, by a computing device, presence or absence of genomic instability for the subject according to the copy number alteration quantifications coupled to the genomic portions.

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: 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.

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: Provided herein are methods, processes and apparatuses for non-invasive assessment of genetic variations that make use of decision analyses. The decision analyses sometimes include segmentation analyses and/or odds ratio analyses.

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.