Diamond shaped window for composite and/or metallic airframe
AssigneeThe Boeing Company
InventorMax U. Kismarton
Life of this patent
Estimating the term…
Abstract
An aircraft fuselage may include a barrel section having a side region. The fuselage may include a first cutout and a second cutout formed in the side region in side-by-side relation to one another. The fuselage may provide a direct load path extending along the barrel section. The load path may extend substantially continuously from a lower portion of the side region generally under the first cutout to an upper portion of the side region generally over the second cutout.
Claims26
An aircraft fuselage, comprising:
- a barrel section having a first cutout and a second cutout formed in the barrel section in side-by-side relation to one another;
- and
- a direct load path extending along the barrel section, the load path extending substantially continuously from a lower portion of the barrel section generally under the first cutout to an upper portion of the barrel section generally over the second cutout.
An aircraft fuselage, comprising:
- a side region;
- a first cutout and a second cutout formed in the side region in side-by-side relation to one another, at least one of the first and second cutouts having a side segment;
- the fuselage being subject to a bending moment generating a shear load in the side region and a cabin pressurization load generating a hoop tension load in the side region;
- the side segment being oriented substantially parallel to a path of a resultant of the shear load and the hoop tension load.
An aircraft fuselage, comprising:
- a barrel section having at least one side panel;
- a first cutout and a second cutout formed in the side panel in side-by-side relation to one another;
- and
- a direct load path extending along the barrel section, the load path extending substantially continuously from a lower portion of the side panel generally under the first cutout to an upper portion of the side panel generally over the second cutout.
A method of forming cutouts in a side region of an aircraft fuselage, comprising the steps of:
- forming a first cutout and a second cutout in side-by-side relation to one another in the side region;
- and
- configuring the first cutout and the second cutout such that a direct load path extends along the side region substantially continuously from a lower portion of the side region generally under the first cutout to an upper portion of the side region generally over the second cutout.
Dependencies are inferred from the claim text.