Energy attenuation stabilizers and methods

Patent metadata

Field	Value
Publication number	US-11459085-B2
Application number	US-201916399936-A
Country	US
Kind code	B2
Filing date	Apr 30, 2019
Priority date	Apr 30, 2019
Publication date	Oct 4, 2022
Grant date	Oct 4, 2022

Abstract

According to one implementation of the present disclosure, a stabilizer of an aircraft includes an energy attenuating portion. The energy attenuating portion includes first and second edge sections separated by an adaptable section. The adaptable section may be rigid in a first range of directions and compressible in a second range of directions.

First claim

What is claimed is:

1. A stabilizer of an aircraft comprising:
an energy attenuating portion comprising:
first and second edge sections separated by a lattice structure, the lattice structure including, a substrate that defines a plurality of cells, each configured to attenuate energy upon deformation, and comprising
one or more nodes having a first thickness to transfer aerodynamic loads, and
one or more free walls having a second thickness that is different from the first thickness to attenuate an impact load;

wherein the substrate has a first stiffness value in a first direction and a second stiffness value in a second direction, the first direction is substantially perpendicular to the second section, and the first stiffness value is different than the second stiffness value.

2. The stabilizer of claim 1 , further comprising:
a fiber-laid skin comprising at least first and second skin portions,
wherein the first skin portion includes a first composite material, and the second skin includes a second composite material, and wherein the first composite material is different from the second composite material.

3. The stabilizer of claim 2 , wherein the first skin portion comprises one or more materials having a third stiffness value, and wherein the second skin portion comprises one or more materials having a fourth stiffness value.

4. The stabilizer of claim 2 , wherein the fiber-laid skin encloses the energy attenuating portion.

5. The stabilizer of claim 2 , wherein the fiber-laid skin has a third stiffness value in the first direction and has a fourth stiffness value in the second direction.

6. The stabilizer of claim 1 , wherein the plurality of cells comprise one or more cell sizes and one or more cell densities.

7. The stabilizer of claim 1 , wherein each of the plurality of cells comprises the first thickness to counter aerodynamic vectors and the second thickness to counter an impact vector, wherein the first thickness is greater than the second thickness.

8. The stabilizer of claim 1 , wherein the plurality of cells is configured to receive different magnitudes of energy attenuation or a single magnitude of energy attenuation.

9. The stabilizer of claim 1 , wherein the first stiffness value corresponds to deformation resistance in response to a first force having a first magnitude, and wherein the second stiffness value corresponds to deformation resistance in response to a second force having a second magnitude.

10. The stabilizer of claim 1 , wherein in response to an impact event, the first and second edge sections are configured to at least partially detach from the lattice structure.

11. A stabilizer of an aircraft comprising:
an energy attenuating portion comprising:
a fiber-laid skin; and
a lattice structure enclosed within the fiber-laid skin, including a substrate that defines a plurality of cells, each configured to attenuate energy upon deformation, and comprising
one or more nodes having a first thickness to transfer aerodynamic loads, and
one or more free walls having a second thickness that is different from the first thickness to attenuate an impact load;

wherein the substrate has a first stiffness value in a first direction and a second stiffness value in a second direction, the first direction is substantially perpendicular to the second section, and the first stiffness value is different than the second stiffness value.

12. The stabilizer of claim 11 , wherein the fiber-laid skin comprises first and second fiber-laid skin portions, and wherein the first fiber-laid skin portion comprises one or more materials having a third stiffness value, and the second fiber-laid skin portion comprises one or more materials having a fourth stiffness value.

Assignees

• Bell Helicopter Textron Inc
• Textron Innovations Inc

Inventors

• Sinusas Eric
• Noiseux-Boucher Guillaume
• Boisvert Olivier
• Doyon Nicolas
• Duval Sebastien

Classifications

• B64C2025/005

  Tail skids for fuselage tail strike protection on tricycle landing gear aircraft · CPC title

• B64C5/02 Primary

  Tailplanes · CPC title

• B64C25/001

  Devices not provided for in the groups B64C25/02 - B64C25/68 · CPC title

• B64C5/06 Primary

  Fins (B64C5/08 takes precedence) · CPC title

• B64C27/04

  Helicopters · CPC title