Aircraft wing, aircraft wing composite material, and method of manufacture thereof
AssigneeJapan Aerospace Exploration Agency
InventorsTakashi Ishikawa, Yutaka Iwahori, Tomohiro Yokozeki, Shin-ichi Takeda
Life of this patent
Estimating the term…
Abstract
To provide an aircraft wing which has both high bending flexibility in the wing chord direction and high capacity to maintain the wing shape in the wing span direction, and to which morphing aircraft technology can be applied in the high-speed regime where aerodynamic forces are high. The wing is formed by arranging a plurality of CFRP rods having maximum anisotropic stiffness in the axial direction, so as to be parallel to the wing span direction, and filling the gaps between the CFRP rods with an elastic material.
Claims10
An aircraft wing, comprising:
- a wing inner plate formed in a corrugated shape made from a first reinforcing material having at least one direction of anisotropy, and formed so that the direction of maximum anisotropic stiffness is perpendicular to or substantially perpendicular to a corrugation direction;
- and
- a wing outer plate made from a second reinforcing material having at least one direction of anisotropy and formed so that the direction of maximum anisotropic stiffness coincides with that of said wing inner plate, wherein the corrugation of said wing inner plate is oriented so as to be parallel to or substantially parallel to a wing chord direction.
An aircraft wing composite material, comprising:
- an inner plate formed in a corrugated shape made from a first reinforcing material having at least one direction of anisotropy, and formed so that the direction of maximum anisotropic stiffness is perpendicular to or substantially perpendicular to a corrugation direction;
- and
- an outer plate made from a second reinforcing material having at least one direction of anisotropy and formed so that a direction of maximum anisotropic stiffness coincides with that of said inner plate.
Dependencies are inferred from the claim text.