Yaw alleviation mechanism for aircraft collision

Patent metadata

Field	Value
Publication number	US-11760464-B2
Application number	US-202117326911-A
Country	US
Kind code	B2
Filing date	May 21, 2021
Priority date	May 21, 2021
Publication date	Sep 19, 2023
Grant date	Sep 19, 2023

Abstract

A yaw alleviation device for an aircraft containing rotatable wing roots attached to wings. The device includes a spring configured to operatively connect to a wing; and a buckling member to operatively connect to the wing. The spring is configured to extend from an original unstrained position upon the buckling member undergoing buckling from an original unbuckled position to cause rotation of one or both wings in rotationally opposite directions. The buckling member may be positioned parallel and at an offset distance to the spring.

First claim

What is claimed is:

1. A yaw alleviation device for an aircraft containing rotatable wing roots attached to wings, the device comprising:
a spring configured to operatively connect to a wing; and
a buckling member to operatively connect to the wing,
wherein the spring is configured to extend from an original unstrained position upon the buckling member undergoing buckling from an original unbuckled position to cause rotation of one or both wings in rotationally opposite directions.

2. The device of claim 1 , wherein the buckling member is positioned parallel and at an offset distance to the spring.

3. The device of claim 1 , wherein the spring operatively connects to the wing root on each side of the aircraft.

4. The device of claim 1 , wherein the buckling member operatively connects to the wing root on each side of the aircraft.

5. The device of claim 1 , wherein the rotation of one or both wings in rotationally opposite directions is to alleviate some of a yaw moment imparted on one of the wings.

6. The device of claim 5 , wherein the yaw moment imparted on one of the wings is a result of an air collision creating a force on one of the wings.

7. The device of claim 5 , wherein upon removal of yaw moment, the spring contracts back to the original unstrained position and the buckling member unbuckles back to the original unbuckled position causing both of the wings to rotate back to an original wing position.

8. The device of claim 5 , wherein the rotation of both of the wings occurs upon the yaw moment exceeding a buckling moment derived by a buckling force sufficiently large to cause the buckling member to buckle.

9. The device of claim 1 , wherein the buckling member comprises a material that is configured to buckle without fracturing.

10. The device of claim 1 , wherein the buckling member comprises any of a metal and a shape memory polymer material.

11. A system comprising:
an aircraft sub-system comprising:
an aircraft chassis;
a first wing root pivotally attached to the aircraft chassis;
a second wing root pivotally attached to the aircraft chassis and gear meshed to the first wing root;
a first wing fixedly attached to the first wing root; and
a second wing fixedly attached to the second wing root;

a yaw alleviation device operatively connected to the aircraft sub-system, wherein the yaw alleviation device comprises:
a spring operatively connected to the first wing and the second wing; and
a buckling member operatively connected to the first wing and the second wing, wherein the buckling member is positioned parallel and at an offset distance to the spring,

wherein the spring is configured to extend from an original unstrained position upon the buckling member undergoing buckling from an original unbuckled position to cause a yaw rotation of the first wing root and the second wing root in rotationally opposite directions to counter a yaw moment imparted on one of the wings.

12. The system of claim 11 , wherein the yaw alleviation device is to generate a resistive moment that resists a rotational moment associated with a buckling force of the buckling member times the offset distance.

13. The system of claim 12 , wherein upon the yaw moment being smaller than the resistive moment, the buckling member does not buckle and the spring does not extend.

14. The system of claim 12 , wherein upon the yaw moment being larger than the resistive moment, the buckling member buckles and the spring extends.

15. The system of claim 14 , wherein upon the buckling member buckling and the spring extending causing rotation of the first wing root with the first wing and the second wing root with the second wing, the yaw moment becomes no greater than the resistive moment.

16. The system of claim 14 , wherein upon removal of the yaw moment, the spring retracts causing the first wing root with the first wing and the second wing root with the second wing to pivot to an original position relative to the aircraft chassis.

17. A method of performing yaw alleviation of an aircraft, the method comprising:
providing a yaw alleviation device operatively attached to wings on the aircraft, wherein the yaw alleviation device comprises:
a spring operatively connected to a first wing and a second wing of the aircraft; and
a buckling member operatively connected to the first wing and the second wing;

receiving a yaw moment from an impact force generated upon one of the wings of the aircraft; and
actuating the yaw alleviation device by:
extending the spring from an original unstrained position to an extended position; and
buckling the buckling member from an original unbuckled position to a buckled position,

wherein extension of the spring and buckling of the buckling member causes a rotation of the first wing root and the second wing root in rotationally opposite directions from an original position to counter the yaw moment.

18. The method of claim 17 , comprising, upon removal of the yaw moment, retracting the spring to the original unstrained position and unbuckling the buckling member to the original unbuckled position causing the first wing root and the second wing root to pivot to the original position.

19. The method of claim 18 , comprising pivoting the first wing root and the second wing root to the original position at a force proportional to a stiffness constant and extension distance of the spring.

20. The method of claim 17 , comprising mechanically actuating the buckling member to buckle.

Assignees

• U S Army Devcom Army Res Laboratory
• Us Army

Inventors

• Henry Todd C
• Hrynuk John T
• Kroninger Christopher M
• Dorothy Michael R
• Haynes Robert A

Classifications

• B64C3/40 Primary

  Varying angle of sweep · CPC title

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• B64D25/00

  Emergency apparatus or devices, not otherwise provided for · CPC title