초록 ▼

An aircraft fuselage includes a tubular shell having a centerline axis, opposite ends, and a cross-section having a radius R(φ), where φ is the angular coordinate of a cylindrical coordinate system, a curvature Curv(φ), where Curv(φ) is the inverse of a local radius of curvature

An aircraft fuselage includes a tubular shell having a centerline axis, opposite ends, and a cross-section having a radius R(φ), where φ is the angular coordinate of a cylindrical coordinate system, a curvature Curv(φ), where Curv(φ) 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 φ, 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.

대표청구항 ▼

What is claimed is: 1. An internally pressurizable aircraft fuselage structure, comprising: an elongated tubular shell having a centerline axis x, opposite closed nose and tail ends, and a non-circular cross-section having a radius R(φ) at substantially every point along the x axis between the

What is claimed is: 1. An internally pressurizable aircraft fuselage structure, comprising: an elongated tubular shell having a centerline axis x, opposite closed nose and tail ends, and a non-circular cross-section having a radius R(φ) at substantially every point along the x axis between the two ends, where φ is a roll elevation angle varying from 0 degrees to +360 degrees about the x axis; wherein the radius R(φ) of each cross-section of the shell varies radially by no more than ±7% from a radius r(φ) of an elliptical cross-section having a major axis with a dimension of 2·rmaxand a minor axis with a dimension of 2·rmin, the shell has at least one structural attribute that has been tailored as a function of the elevation angle φ 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 at least one structural attribute has not been so tailored; the shell includes structural components including at least one external circumferential skin attached to internal longitudinal stringers and axially spaced circumferential frames, each circumferential frame having a varying depth as defined by an outer edge of the frame lying substantially along a first elliptical path and an inner edge lying substantially along a second elliptical path, and, the ratio of the major axis to the minor axis is greater for the second elliptical path than for the first elliptical path. 2. The fuselage structure of claim 1, wherein: a maximum width of the shell is greater than a maximum height thereof and, the maximum width and height of the shell are respectively substantially aligned with the major and minor axes of the elliptical cross-section. 3. The fuselage structure of claim 1, wherein r(φ) is given by the relation: 4. The fuselage structure of claim 1, wherein a curvature Curv(φ), defined as the inverse of the local radius of curvature of a surface of the shell, is associated with R(φ), and a corresponding curvature k(φ) associated with r(φ) is given by: 5. The fuselage structure of claim 1, wherein the shell functions as a pressure vessel, and wherein the design load comprises internal pressurization loads. 6. The fuselage structure of claim 1, wherein at least one dimension of at least one of the structural components is tailored as a function of at least one of R(φ) and Curv(φ). 7. The fuselage structure of claim 6, wherein the at least one dimension comprises a radial dimension, an axial dimension or a circumferential dimension. 8. The fuselage structure of claim 6, wherein the at least one dimension comprises a thickness of the at least one external circumferential skin. 9. The fuselage structure of claim 1, wherein a local frame depth of the circumferential frames in a crown region of the fuselage is increased relative to an average frame depth. 10. The fuselage structure of claim 1, wherein a local frame depth of the circumferential frames in a keel region of the fuselage is increased relative to an average frame depth. 11. The fuselage structure of claim 1, wherein a local frame depth of each of the circumferential frames in left and a right side regions of the structure in a passenger cabin portion of the structure is decreased relative to an average frame depth.