Energy absorption stabilizers and methods

Patent metadata

Field	Value
Publication number	US-11518502-B2
Application number	US-201916399932-A
Country	US
Kind code	B2
Filing date	Apr 30, 2019
Priority date	Apr 30, 2019
Publication date	Dec 6, 2022
Grant date	Dec 6, 2022

Abstract

According to one implementation of the present disclosure, a stabilizer of an aircraft includes an energy absorbing assembly. The energy absorbing assembly includes first and second portions and a retractable section. The retractable section may be at least partially affixed to the first portion and is configured to enable displacement of the second portion of the stabilizer with respect to the first portion.

First claim

What is claimed is:

1. A stabilizer of an aircraft comprising:
an energy absorbing assembly comprising:
a first portion of the stabilizer; and
a retractable section at least partially affixed to the first portion,
an energy absorbing mechanism within the retractable section that is configured to enable displacement of the retractable section parallel with a longitudinal span of the stabilizer of a second portion of the stabilizer with respect to the first portion.

2. The stabilizer of claim 1 , wherein the displacement of the second portion of the stabilizer is one of linear, axial, or angular displacement.

3. The stabilizer of claim 1 , further comprising:
an outer skin enclosing the first and second portions, wherein the outer skin is made of a rigid material.

4. The stabilizer of claim 3 , further comprising:
an air gap between the first and second portions of the stabilizer, wherein the air gap is enclosed by the outer skin.

5. The stabilizer of claim 4 , wherein in response to an impact event of a distal end of the stabilizer, the second portion is configured to at least partially resistively displace the air gap.

6. The stabilizer of claim 1 , wherein in response to an impact event of a distal end of the stabilizer, the second portion is constructed for either elastic or plastic deformation.

7. A stabilizer of an aircraft comprising:
an energy absorbing assembly comprising:
a first portion of the stabilizer; and
a retractable section at least partially affixed to the first portion, wherein the retractable section is configured to enable displacement of the retractable section parallel with a longitudinal span of the stabilizer of a second portion of the stabilizer with respect to the first portion; and

one or more plates each comprising an aperture, wherein the one or more plates are at least partially adjoined to the first portion of the stabilizer.

8. The stabilizer of claim 7 , wherein the retractable section further comprises:
a fastener configured to secure a first end of one plate of the one or more plates to the first portion of the stabilizer.

9. The stabilizer of claim 8 , wherein a diameter of the fastener is greater than a width of the aperture.

10. The stabilizer of claim 7 , wherein in response to an impact event of a distal end of the stabilizer, the retractable section is configured to align displacement of the second portion along the aperture and proximate the first portion.

11. The stabilizer of claim 7 , wherein the one or more plates comprise at least first and second plates positioned on opposing sides of the stabilizer.

12. The stabilizer of claim 7 , wherein the one or more plates comprise a U-shaped plate, wherein the retractable section further comprises at least two fasteners, and wherein the at least two fasteners are configured to secure first ends of the U-shaped plate to the first portion of the stabilizer.

13. The stabilizer of claim 7 , wherein the retractable section is configured for one or more energy absorption metrics, wherein the energy absorption metrics correspond to different magnitudes of sliding friction.

14. The stabilizer of claim 1 , wherein the retractable section comprises one or more mechanical dampers.

15. The stabilizer of claim 1 , wherein the retractable section comprises one or more energy absorption devices.

16. The stabilizer of claim 1 , wherein the energy absorbing assembly comprises an aerodynamic shape.

17. A method of energy absorption by a stabilizer, comprising:
setting, in a first positioning, first and second portions of the stabilizer, wherein, in the first positioning, the first and second portions are encased in an outer skin, separated by an air gap, and adjoined by a retractable section; and
in response to an impact event of a distal end of the stabilizer, engaging an energy absorbing mechanism within a retractable section of the stabilizer to resistively displace the retractable section parallel with a longitudinal span of the stabilizer the second portion to converge the first portion over the air gap.

18. The method of claim 17 , further comprising:
evaluating, in a second positioning, energy absorption metrics in the retractable section of the stabilizer, wherein, in the second positioning, the second portion is proximate to the first portion of the stabilizer, the air gap is at least partially eliminated, and the outer skin is detached from the stabilizer.

19. A method of energy absorption by a stabilizer, comprising:
forming a first portion of the stabilizer; and
forming a retractable section at least partially affixed to the first portion, and
forming an energy absorbing mechanism within the retractable section;
wherein the energy absorbing mechanism is configured to enable displacement of the retractable section parallel with a longitudinal span of the stabilizer of a second portion of the stabilizer with respect to the first portion.

20. The method of claim 19 , wherein forming the retractable section comprises forming at least one of one or more plates or one or more coil spring mechanisms.

Assignees

• Bell Helicopter Textron Inc
• Textron Innovations Inc

Inventors

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

Classifications

• B64C2025/325

  specially adapted for helicopters · CPC title

• B64C5/12

  for retraction against or within fuselage or nacelle · CPC title

• B64C25/58 Primary

  Arrangements or adaptations of shock-absorbers or springs (shimmy-dampers B64C25/50) · CPC title

• B64C27/04

  Helicopters · CPC title

• B64C25/32 Primary

  characterised by elements which contact the ground or similar surface  (arrester hooks B64C25/68) · CPC title