Variable morphing wing using surface actuated origami folds

Patent metadata

Field	Value
Publication number	US-12296948-B2
Application number	US-202217721962-A
Country	US
Kind code	B2
Filing date	Apr 15, 2022
Priority date	Apr 15, 2021
Publication date	May 13, 2025
Grant date	May 13, 2025

Abstract

Morphable active corrugate structure and aeronautical wings are provided herein including one or more skins or envelopes, and a sheet having independently actuable hinge domains attached to the one or more skins or envelopes and independently actuable facet domains, each of the hinge domains and facet domains configured with through-thickness differential expansion coefficients, wherein differential strains in at least one of the hinge domains or the facet domains cause the sheet to expand or contract along a flexible axis of the sheet, wherein the sheet is attached to the upper and lower skins at respective upper and lower of the hinge domains.

First claim

What is claimed is:

1. A morphable active corrugate structure comprising:
upper and lower skins; and
a sheet having;
a plurality of independently actuable hinge domains, each attached to one of the upper and lower skins and having a hinge domain through-thickness differential expansion coefficient (α H ), and
a plurality of independently actuable facet domains, each adjacent to one of the hinge domains, not attached to the upper and lower skins, and having a facet domain through-thickness differential expansion coefficient (α F ), wherein, for adjacent facet and hinge domains, α F <α H and a thickness of the facet domain (h F ) is less than a thickness of the adjacent hinge domain (h H ) in an unactuated state,
wherein the application of a domain-specific actuation force (ΔF) to one or more of the hinge and/or facet domains generates differential strains in the one or more of the hinge and/or facet domains, causing the sheet to locally expand or contract along a flexible direction of the sheet to create a local curvature (K) according to the relationship K=αΔF/h to produce a morphable shape of the active corrugate structure; and
wherein the applied ΔF is adjustable to change the differential strains in the one or more of the hinge and/or facet domains to produce a different morphable shape of the active corrugate structure.

2. The morphable active corrugate structure of claim 1 , wherein the differential strains cause the sheet to at least one of deform or bend along a direction of the sheet perpendicular to the flexible direction.

3. The morphable active corrugate structure of claim 1 , wherein the skin is elastic.

4. The morphable active corrugate structure of claim 3 , wherein:
in a fully expanded state of the hinge domains and the facet domains, the sheet is flat and extends in parallel contact with the upper and lower skins; and
in a contracted state of at least one of the hinge domains and the facet domains, the sheet is at least one of folded or corrugated and the facet domains are at least partially separated from the upper and lower skins.

5. The morphable active corrugate structure of claim 1 , wherein in a fully expanded state of the hinge domains and the facet domains, the sheet is at least one of folded or corrugated and the facet domains are at least partially separated from the upper and lower skins.

6. The morphable active corrugate structure of claim 5 , wherein at least one of expansion or contraction of the sheet causes flexure of the upper and lower skins.

7. The morphable enveloped corrugate structure of claim 1 , wherein at least one of expansion or contraction of the sheet causes flexure of at least one of the upper skin or the lower skin along a stiff direction of the sheet, perpendicular to the flexible direction of the sheet.

8. The morphable active corrugate structure of claim 1 , wherein each of the independently actuable hinge domains and the independently actuable facet domains is actuable by application of ΔF by an actuation driver, the actuation driver including at least one of thermal actuation, electrical actuation, magnetic actuation, pneumatic actuation, phase actuation, or combinations thereof.

9. A morphable enveloped corrugate structure comprising:
a skin forming an envelope;
a sheet within the envelope having;
a plurality of independently actuable hinge domains each attached to the skin and having a hinge domain through-thickness differential expansion coefficient (α H ), and
a plurality of independently actuable facet domains, each adjacent to one of the hinge domains, not attached to the skin, and having a facet domain through-thickness differential expansion coefficient (α F ), wherein, for adjacent facet and hinge domains, α F <α H and a thickness of the facet domain (h F ) is less than a thickness of the adjacent hinge domain (h H ) in an unactuated state,
wherein the application of a domain-specific actuation force (ΔF) to one or more of the hinge and/or facet domains generates differential strains in the one or more of the hinge and/or facet domains, causing the sheet to locally expand or contract along a flexible direction of the sheet to create a local curvature (K) according to the relationship K=αΔF/h to produce a morphable shape of the enveloped corrugate structure; and
wherein the applied ΔF is adjustable to change the differential strains in the one or more of the hinge and/or facet domains to produce a different morphable shape of the enveloped corrugate structure.

10. The morphable enveloped corrugate structure of claim 9 , wherein at least one of expansion or contraction of the sheet causes flexure of the envelope along the flexible direction of the sheet.

11. The morphable enveloped corrugate structure of claim 9 , wherein at least one of expansion or contraction of the sheet causes flexure of the envelope along a stiff direction of the sheet, perpendicular to the flexible direction of the sheet.

12. The morphable enveloped corrugate structure of claim 9 , wherein the envelope is an airfoil shaped wing envelope.

13. The morphable enveloped corrugate structure of claim 9 , wherein each of the independently actuable hinge domains and the independently actuable facet domains is actuable by application of ΔF by an actuation driver, the actuation driver including at least one of thermal actuation, electrical actuation, magnetic actuation, pneumatic actuation, phase actuation, or combinations thereof.

14. An aeronautical wing comprising:
a wing envelope;
a sheet within the wing envelope having:
a plurality of independently actuable hinge domains each attached to the wing envelope and having a hinge domain through-thickness differential expansion coefficient (α H ), and
a plurality of independently actuable facet domains, each adjacent to one of the hinge domains, not attached to the wing envelope, and having a facet domain through-thickness differential expansion coefficient (α F ), wherein, for adjacent facet and hinge domains, α F <α H and a thickness of the facet domain (h F ) is less than a thickness of the adjacent hinge domain (h H ) in an unactuated state,
wherein the application of a domain-specific actuation force (ΔF) to one or more of the hinge and/or facet domains generates differential strains in the one or more of the hinge and/or facet domains, causing the sheet to locally expand or contract along a flexible direction of the sheet to create a local curvature (K) according to the relationship K=αΔF/h to produce a morphable shape of the aeronautical wing; and
wherein the applied ΔF is adjustable to change the differential strains in the one or more of the hinge and/or facet domains to produce a different morphable shape of the aeronautical wing.

15. The aeronautical wing of claim 14 , wherein each of the independently actuable hinge domains and the independently actuable facet domains is actuable by an actuation driver, the actuation driver including at least one of thermal actuation, electrical actuation, magnetic actuation, pneumatic actuation, phase actuation, or combinations thereof.

16. The aeronautical wing of claim 14 , wherein the flexible direction of the sheet is oriented parallel to a chordwise direction of the wing envelope.

17. The aeronautical wing of claim 14 , further comprising at least one additional sheet within the wing envelope, the at least one additional sheet positioned adjacent to or spaced apart from the sheet along a spanwise direction of the wing envelope.

18. The aeronautical wing of claim 14 , wherein at least one of expansion or contraction of

Assignees

• Univ Northeastern

Inventors

• Upmanyu Moneesh
• Vaidya Raman

Classifications

• B64C23/069

  using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips · CPC title

• B64C3/14

  Aerofoil profile · CPC title

• B64C2003/142

  with variable camber along the airfoil chord · CPC title

• B64C3/26

  Construction, shape, or attachment of separate skins, e.g. panels · CPC title

• B64C3/385

  Variable incidence wings · CPC title