Integrated stringer panel and method of making thereof
An integrated stringer panel for an aircraft, including a base panel comprising a sheet-like continuous part; and a stringer panel comprising a sheet-like continuous part, wherein the base panel is bonded to the stringer panel, wherein the stringer panel is corrugated to define two or more stringer channels, and one or more raised areas between the two or more stringer channels, and wherein the one or more raised areas include one or more openings to allow access to the base panel through the stringer panel.
1 . An integrated stringer panel for an aircraft, comprising:
a base panel comprising a sheet-like continuous part; and
a stringer panel comprising a sheet-like continuous part,
wherein the base panel is bonded to the stringer panel,
wherein the stringer panel is corrugated to define:
two or more stringer channels, and
one or more raised areas between the two or more stringer channels,
wherein the stringer panel is thicker at portions corresponding to the two or more stringer channels, and
wherein the one or more raised areas comprise one or more openings to allow access to the base panel through the stringer panel.
2 . The integrated stringer panel for an aircraft of claim 1 , wherein the stringer panel is integrally formed to define the two or more stringer channels, the one or more raised areas, and the one or more openings.
3 . The integrated stringer panel for an aircraft of claim 1 , wherein the stringer panel is bonded to the base panel only along a portion of a first surface corresponding to the two or more stringer channels and the one or more raised areas are not bonded to or in contact with the base panel.
4 . The integrated stringer panel for an aircraft of claim 1 , wherein the base panel comprises at least one of a metal or metal alloy and a composite material, and wherein the stringer panel comprises at least one of a metal or metal alloy and a composite material.
5 . The integrated stringer panel for an aircraft of claim 1 , wherein the two or more stringer channels extend along substantially an entire length L of the stringer panel.
6 . The integrated stringer panel for an aircraft of claim 1 , wherein the two or more stringer channels are not enclosed.
7 . The integrated stringer panel for an aircraft of claim 1 , wherein the one or more raised areas have a height along a y-axis from about 0.5 inches to about 10.0 inches.
8 . The integrated stringer panel for an aircraft of claim 1 , wherein each of the one or more raised areas comprises at least one of the one or more openings.
9 . The integrated stringer panel for an aircraft of claim 1 , wherein the one or more openings are defined on a top surface of the one or more raised areas, and wherein the one or more openings comprise from about 20% to about 90% of a total surface area of the stringer panel.
10 . The integrated stringer panel for an aircraft of claim 1 , wherein each of the one or more raised areas defines a cavity between the base panel and the stringer panel, and wherein the one or more cavities are not enclosed and the one or more openings allow access to the base panel through the one or more cavities.
11 . The integrated stringer panel for an aircraft of claim 1 , further comprising an adhesive layer to bond the stringer panel to the base panel disposed between the stringer panel and the base panel.
12 . The integrated stringer panel for an aircraft of claim 1 , further comprising one or more leg brackets bonding the stringer panel to the base panel, wherein the one or more leg brackets are integrally formed in the stringer panel and disposed within the one or more openings.
13 . The integrated stringer panel for an aircraft of claim 1 , wherein the base panel comprises an exterior surface defining a fuselage skin and an interior surface opposite the exterior surface of the base panel.
14 . The integrated stringer panel for an aircraft of claim 13 , wherein the interior surface of the base panel is bonded to the stringer panel.
15 . The integrated stringer panel for an aircraft of claim 14 , wherein the one or more raised areas are not bonded to the interior surface of the base panel.
16 . An integrated stringer panel for an aircraft, comprising:
a base panel comprising a sheet-like continuous part;
a stringer panel comprising a sheet-like continuous part; and
one or more leg brackets bonding the stringer panel to the base panel,
wherein the stringer panel is corrugated to define:
two or more stringer channels, and
one or more raised areas between the two or more stringer channels, and
wherein the one or more raised areas comprise one or more openings defined on a top surface of the one or more raised areas to allow access to the base panel through the stringer panel.
17 . The integrated stringer panel for an aircraft of claim 16 , wherein the one or more leg brackets are disposed within the one or more openings to bond the stringer panel to the base panel.
18 . The integrated stringer panel for an aircraft of claim 16 , wherein the stringer panel is integrally formed to define the two or more stringer channels, the one or more raised areas, the one or more openings, and the one or more leg brackets.
19 . The integrated stringer panel for an aircraft of claim 16 , wherein the stringer panel is bonded to the base panel only along at least a portion of a first surface of the base panel corresponding to the two or more stringer channels and at least a portion of a bottom surface of the leg brackets.
20 . The integrated stringer panel for an aircraft of claim 16 , wherein the base panel comprises an exterior surface defining a fuselage skin and an interior surface opposite the exterior surface of the base panel, and wherein the interior surface of the base panel is bonded to the stringer panel.