US 8,128,028 B2Granted

Internally stiffened composite panels and methods for their manufacture

AssigneeThe Boeing Company

InventorEmmanuel J. Grillos

Life of this patent

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Abstract

Internally stiffened composite panels and associated manufacturing methods. An internally stiffened composite panel can include a first face sheet, a second face sheet offset from the first face sheet, and at least one core portion sandwiched between the first and second face sheets. The composite panel can further include a stiffener disposed between the first and second face sheets adjacent to the core portion. The stiffener can have a first attachment portion attached to the first face sheet, a second attachment portion attached to the second face sheet, and an intermediate portion extending between the first and second attachment portions. One or both of the first and second attachment portions can be configured to engage a fastener, such as a blind fastener, for attaching a part to the composite panel.

Claims13

Dependent claims

An aircraft comprising:

a fuselage;
and
a wing fixedly attached to the fuselage, wherein at least one of the fuselage and the wing includes a composite panel, the composite panel including:
a first face sheet;
a second face sheet offset from the first face sheet;
a first core portion extending between the first and second face sheets and attached to the first and second face sheets;
a second core portion spaced apart from the first core portion, the second core portion extending between the first and second face sheets and attached to the first and second face sheets;
a stiffener disposed between the first and second face sheets at least proximate to the first and second core portions, the stiffener having at least one attachment portion attached to the first face sheets, wherein the first core portion fits against the stiffener and overlays the at least one attachment portion to sandwich the at least one attachment portion between the first core portion and the first face sheet, and wherein the first core portion is bonded to the at least one attachment portion;
and
an elongate passageway defined by the stiffener and extending between the first and second face sheets, wherein the passageway is open.

7 more elements

An aircraft comprising:

a fuselage;
and
a wing fixedly attached to the fuselage, wherein at least one of the fuselage and the wing includes a composite panel, the composite panel including:
a first face sheet offset from a second face sheet;
a stiffener having first and second flange portions attached to the first face sheet, a cap portion attached to the second face sheet, and an intermediate portion extending between the cap portion and the first and second flange portions, wherein the first flange portion is spaced apart from the second flange portion, and wherein the first and second flange portions extend outwardly from opposite sides of the intermediate portion;
a first core portion positioned between the first and second face sheets on a first side of the stiffener, wherein the first core portion fits against the first flange portion and the intermediate portion and is bonded to the first flange portion and the intermediate portion;
and
a second core portion positioned between the first and second face sheets on a second side of the stiffener opposite to the first side of the stiffener, wherein the second core portion fits against the second flange portion and the intermediate portion and is bonded to the second flange portion and the intermediate portion, and wherein the stiffener defines a passageway extending between the first and second core portions;
wherein the passageway is open, and wherein the first and second face sheets sandwich the stiffener, the first core portion, and the second core portion therebetween.

6 more elements

Dependencies are inferred from the claim text.

Facts

Application: 11/626,766Filed 24 Jan 2007 · division
Priority: 20 Sep 2002
Published: US 2010/0252681 A17 Oct 2010
Granted: 6 Mar 2012
Term ends: Not estimatedThe source records don’t support an estimate.

Classification6 codes

E04C 2/365
Spaced apart by transversely-placed strip material, e.g. honeycomb panels: by honeycomb structures
B64C 1/12
Frames; Stringers; Longerons ; Fuselage sections: construction or attachment of skin panels
Y10T 29/49622
Structural member making: vehicular structural member making
E04C
Structural elements

Family

Application10/251,268Parent of this division · filed 20 Sep 2002
US 2010/0252681 A1Pre-grant publication · published 7 Oct 2010
US 7,197,852 B2Parent of this division
US 2004/0055248 A1Published application
US 8,128,028 B2This patent

From the US filing history. Foreign family members aren’t listed.