Abstract: A method includes generating thrust at one or more engines of an aircraft. The method includes generating first electricity at a first power unit concurrently with generating second electricity at a second power unit. The first power unit and the second power unit are independent of the one or more engines of the aircraft. The first electricity has a first set of electrical characteristics and the second electricity has a second set of electrical characteristics, where the first set of electrical characteristics is different than the second set of electrical characteristics.

Abstract: A method includes generating thrust at one or more engines of an aircraft. The method includes generating first electricity at a first power unit concurrently with generating second electricity at a second power unit. The first power unit and the second power unit are independent of the one or more engines of the aircraft. The first electricity has a first set of electrical characteristics and the second electricity has a second set of electrical characteristics, where the first set of electrical characteristics is different than the second set of electrical characteristics.

Abstract: Systems and methods of independent power generation are disclosed. A particular system includes an aircraft having at least one engine and a plurality of independent power units. Each power unit of the plurality of independent power units generates electricity independently of the at least one engine. The plurality of independent power units include at least a first independent power unit that generates first electricity having a first set of electrical characteristics and a second independent power unit that generates second electricity having a second set of electrical characteristics concurrently with the first power unit generating the first electricity. The first set of electrical characteristics is different than the second set of electrical characteristics.

Abstract: A method for minimizing the weight of an internally pressurized aircraft fuselage of a type that includes an elongated tubular shell having a near-elliptical cross-section with a radius R(?)- and a curvature Curv(?), where ? is a roll elevation angle of the shell, includes tailoring at least one structural attribute of the shell as a function of at least one of the elevation angle ?, R(?) and Curv(?) so as to reduce the weight of the fuselage relative to an identical fuselage shell in which the same at least one structural attribute has not been so tailored.

Abstract: A method for minimizing the weight of an internally pressurized aircraft fuselage of a type that includes an elongated tubular shell having a near-elliptical cross-section with a radius R(?)- and a curvature Curv(?), where ? is a roll elevation angle of the shell, includes tailoring at least one structural attribute of the shell as a function of at least one of the elevation angle ?, R(?) and Curv(?) so as to reduce the weight of the fuselage relative to an identical fuselage shell in which the same at least one structural attribute has not been so tailored.

Abstract: An aircraft fuselage includes a tubular shell having a centerline axis, opposite ends, and a cross-section having a radius R(?), where ? is the angular coordinate of a cylindrical coordinate system, a curvature Curv(?), where Curv(?) is the inverse of a local radius of curvature of a surface of the shell, and a circumferential shape that varies radially by no more than ±7% from that of an elliptical cross-section at substantially every station along the centerline axis between the nose and tail ends thereof. The weight of the shell is minimized by “tailoring,” i.e., optimizing, at least one structural attribute, expressed as a function of ?, associated with every element of the shell, such that the weight of the shell required to react a design load incident thereon is less than that required to react the same design load, but wherein the same structural attribute has not been so tailored.

Abstract: An aircraft fuselage includes a tubular shell having a centerline axis, opposite ends, and a cross-section having a radius R(?), where ? is the angular coordinate of a cylindrical coordinate system, a curvature Curv(?), where Curv(?) is the inverse of a local radius of curvature of a surface of the shell, and a circumferential shape that varies radially by no more than ±7% from that of an elliptical cross-section at substantially every station along the centerline axis between the nose and tail ends thereof. The weight of the shell is minimized by “tailoring,” i.e., optimizing, at least one structural attribute, expressed as a function of ?, associated with every element of the shell, such that the weight of the shell required to react a design load incident thereon is less than that required to react the same design load, but wherein the same structural attribute has not been so tailored.