Unified canopies for aircraft

Patent metadata

Field	Value
Publication number	US-10974806-B2
Application number	US-201715725698-A
Country	US
Kind code	B2
Filing date	Oct 5, 2017
Priority date	Oct 5, 2017
Publication date	Apr 13, 2021
Grant date	Apr 13, 2021

Abstract

An aircraft includes the aircraft component. The aircraft component includes an outer skin portion, a plurality of major stiffeners, and a plurality of minor stiffeners. The outer skin portion has an interior side and an exterior side configured to define an exterior boundary of the aircraft. The major stiffeners are integral with the outer skin portion and extend out from the interior side. The major stiffeners are configured to resist global deflection of the aircraft component in response to a bird strike on the aircraft component. The minor stiffeners are disposed between the major stiffeners, are integral with the outer skin portion, and extend out from the interior side. The minor stiffeners are configured to resist perforation of the aircraft component in response to the bird strike on the aircraft component.

First claim

What is claimed is:

1. An aircraft component, comprising:
an outer skin portion having an interior side and an exterior side configured to define an exterior boundary of an aircraft;
a plurality of major stiffeners unified with the outer skin portion and extending out from the interior side, wherein the plurality of major stiffeners are configured to resist deflection of the aircraft component in response to a bird strike on the aircraft component;
a plurality of minor stiffeners disposed between the plurality of major stiffeners, unified with the outer skin portion, and extending out from the interior side, wherein the plurality of minor stiffeners are configured to resist perforation of the aircraft component in response to the bird strike on the aircraft component; and
a crown frame unified with the outer skin portion and disposed around a periphery of the aircraft component extending out from the interior side, and
wherein the plurality of major stiffeners extend across the interior side from a first portion of the crown frame to a second portion of the crown frame.

2. The aircraft component of claim 1 , wherein the plurality of major stiffeners and the plurality of minor stiffeners have lateral axes that are normal to the outer skin portion.

3. The aircraft component of claim 2 , wherein the plurality of major stiffeners intersect each other at nonzero angles.

4. The aircraft component of claim 2 , wherein the plurality of major stiffeners intersect each other to define a repeating major cavity that has a shape that is substantially a triangular prism.

5. The aircraft component of claim 2 , wherein the plurality of major stiffeners include a plurality of first direction stiffeners, a plurality of second direction stiffeners intersecting the plurality of first direction stiffeners at a 60 degree angle, and a plurality of third direction stiffeners intersecting the plurality of first direction stiffeners at a 120 degree angle.

6. The aircraft component of claim 1 , wherein the plurality of minor stiffeners are arranged in a repeating pattern and pass through at least one of the plurality of major stiffeners.

7. The aircraft component of claim 6 , wherein the repeating pattern is centered on an intersection of two of the plurality of major stiffeners.

8. The aircraft component of claim 7 , wherein the repeating pattern is a hexagonal shape.

9. The aircraft component of claim 1 , wherein the plurality of major stiffeners have a first depth normal to the outer skin portion, the plurality of minor stiffeners have a second depth normal to the outer skin portion, and the first depth is larger than the second depth.

10. The aircraft component of claim 1 , wherein each of the plurality of major stiffeners has a depth of about 0.65 inches and is separated from each other parallel major stiffener of the plurality of major stiffeners by about 6.2 inches.

11. The aircraft component of claim 10 , wherein the plurality of major stiffeners form a plurality of cavities, and wherein the plurality of minor stiffeners have a depth of about 0.3 inches and intersect at a center of each of the plurality of cavities.

12. The aircraft component of claim 1 , wherein the exterior side has a convex surface that defines a crown of the aircraft, and wherein the interior side has a concave interior surface.

13. An aircraft, comprising:
a nose;
a window frame fastened to the nose;
a canopy surround portion fastened to the window frame; and
a unified crown secured to the window frame and the canopy surround portion, the unified crown comprising:
an outer skin portion having an interior side and an exterior side configured to define an exterior boundary of the aircraft;
a plurality of major stiffeners integral with the outer skin portion and extending out from the interior side, wherein the plurality of major stiffeners are configured to resist deflection of the unified crown in response to a bird strike on the aircraft component, wherein the plurality of major stiffeners intersect each other;
a plurality of minor stiffeners disposed between the plurality of major stiffeners, integral with the outer skin portion, and extending out from the interior side, wherein the plurality of minor stiffeners are configured to resist perforation of the unified crown in response to the bird strike on the aircraft component; and
a crown frame integral with the outer skin portion and disposed around a periphery of the unified crown extending out from the interior side, and
wherein the plurality of major stiffeners extend across the interior side from a first portion of the crown frame to a second portion of the crown frame.

14. The aircraft of claim 13 , wherein the plurality of major stiffeners and the plurality of minor stiffeners are normal to the outer skin portion, the plurality of major stiffeners have a first depth normal to the outer skin portion, the plurality of minor stiffeners have a second depth normal to the outer skin portion, and the first depth is larger than the second depth.

15. The aircraft of claim 14 , wherein the plurality of major stiffeners include a plurality of first direction stiffeners, a plurality of second direction stiffeners intersecting the plurality of first direction stiffeners at a 60 degree angle, and a plurality of third direction stiffeners intersecting the plurality of first direction stiffeners at a 120 degree angle to define a repeating major cavity that has a shape that is substantially a triangular prism.

16. The aircraft of claim 14 , wherein the plurality of minor stiffeners are arranged in a repeating pattern and pass through at least one of the plurality of major stiffeners, and wherein the repeating pattern is centered on an intersection of two of the plurality of major stiffeners.

17. The aircraft of claim 16 , wherein the plurality of major stiffeners have a depth of about 0.65 inches, form a plurality of cavities, and are separated from other parallel major stiffeners of the plurality of major stiffeners by about 6.2 inches.

18. The aircraft of claim 17 , wherein the repeating pattern is a hexagonal shape, the plurality of minor stiffeners have a depth of about 0.3 inches, and the plurality of minor stiffeners intersect at a center of each of the plurality of cavities.

Assignees

• Gulfstream Aerospace Corp

Inventors

• Chapman Mark
• Williams Bryan
• Volk Dillon

Classifications

• B64C1/06

  Frames; Stringers; Longerons {; Fuselage sections} · CPC title

• B64C1/1476 Primary

  Canopies; Windscreens or similar transparent elements · CPC title

• B64C1/1492

  Structure and mounting of the transparent elements in the window or windscreen · CPC title

• B64D2045/0095

  Devices specially adapted to avoid bird strike · CPC title