Energy-Absorbing Beam Member

• US 20150225063A1
• Filed: 02/03/2015
• Published: 08/13/2015
• Est. Priority Date: 02/12/2014
• Status: Active Grant

• Current Assignee: United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
• Original Assignee: The United States of America As Represented By The Secretary of Agriculture
• Inventors: Littell, Justin D.
• Granted Patent: US 9,616,988 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 1/062 specially adapted to absorb crash loads
• CPC Class Codes: B64C 1/18 Floors

Abstract

An energy-absorbing (EA) beam member and having a cell core structure is positioned in an aircraft fuselage proximate to the floor of the aircraft. The cell core structure has a length oriented along a width of the fuselage, a width oriented along a length of the fuselage, and a depth extending away from the floor. The cell core structure also includes cell walls that collectively define a repeating conusoidal pattern of alternating respective larger and smaller first and second radii along the length of the cell core structure. The cell walls slope away from a direction of flight of the aircraft at a calibrated lean angle. An EA beam member may include the cell core structure and first and second plates along the length of the cell core structure on opposite edges of the cell material.

Claims

1. An energy-absorbing (EA) beam member for use in an aircraft having a fuselage and a floor, the EA beam member comprising:

a cell core structure having cell walls, a length, a width, and a depth, wherein the cell walls collectively define a repeating conusoidal pattern of alternating respective smaller and larger first and second radii along the length of the cell core structure, and wherein the cell walls are angled away from a forward direction of flight of the aircraft at a calibrated lean angle;

a first plate affixed to a first edge of the cell core structure along the length of the cell core structure, wherein the first plate is substantially flat such that the first plate is attachable to the floor; and

a second plate affixed to a second edge of the cell core structure along the length of the cell core structure opposite the first edge.

2. The EA beam member according to claim 1, wherein the second plate is curved along a length of the second plate.

3. The EA beam member according to claim 1, wherein the calibrated lean angle is greater than about 2 degrees.

4. The EA beam member according to claim 1, wherein the smaller first radii are no more than about 90 percent of the larger second radii.

5. The EA beam member according to claim 1, wherein the cell core structure is constructed of woven materials.

6. The EA beam member according to claim 5, wherein the woven materials include carbon fiber and aramid fiber arranged in a plurality of different layers, and wherein respective longitudinal axes of the carbon and aramid fibers are orthogonal with respect to each other.

7. An energy-absorbing (EA) beam member for use in an aircraft having a fuselage with an annular fuselage skin and a floor, the EA beam member comprising:

a cell core structure having cell walls constructed of woven carbon and aramid fibers, a length, a width, and a depth, wherein the cell walls collectively define a repeating conusoidal pattern of alternating respective smaller and larger first and second radii along the length of the cell core structure, and wherein the cell walls are angled away from a forward direction of flight of the aircraft at a calibrated lean angle of at least about 2 degrees;

a first plate connected to a first edge of the cell core structure along the length of the cell core structure, wherein the first plate is substantially flat; and

a second plate connected to a second edge of the cell core structure along the length of the cell core structure opposite the first edge;

wherein the first radii are about 30 percent to about 90 percent of the second radii.

8. The EA beam member according to claim 7, wherein the woven carbon and aramid fibers are arranged in at least four different layers.

9. The EA beam member of claim 8, wherein in each of the four different layers the carbon fibers are oriented in a warp direction and the aramid fibers are oriented in a fill direction.

10. The EA beam member of claim 9, further comprising a pair of end plates configured for attachment to the fuselage.

11. The EA beam member of claim 10, wherein one of the end plates is flat along its length and the other one of the end plates is curved along its length.

12. An aircraft comprising:

a fuselage having a width and a length;

a floor; and

an energy-absorbing (EA) beam member positioned proximate to the floor and having a cell core structure, wherein the cell core structure has a length oriented along the width of the fuselage, a width oriented along the length of the fuselage, and a depth extending away from the floor, and also includes cell walls that collectively define a repeating conusoidal pattern of alternating respective smaller and larger first and second radii along the length of the cell core structure, and wherein the cell walls slope away from a forward direction of flight of the aircraft at a calibrated lean angle.

13. The aircraft according to claim 12, wherein the calibrated lean angle is greater than about 2 degrees.

14. The aircraft according to claim 12, wherein the smaller first radii are at least 10 percent of the size of the larger second radii.

15. The aircraft according to claim 12, wherein the EA beam member is connected to the floor to form a support structure for the floor.

16. The aircraft according to claim 12, wherein the cell core structure is constructed of woven materials.

17. The aircraft according to claim 16, wherein the woven materials include carbon fiber.

18. The aircraft according to claim 16, wherein the woven materials include aramid fiber.

19. The aircraft according to claim 16, wherein the woven materials include carbon fiber and aramid fiber arranged in a plurality of different layers, and wherein respective longitudinal axes of the carbon and aramid fibers are orthogonally arranged with respect to each other.

20. The aircraft according to claim 12, wherein the EA beam member includes a first plate and a second plate, the cell core structure includes first and second edges affixed to the respective first and second plates, the first plate is connected to the floor, and the second plate is connected to the fuselage.