Deployable overhead protection assembly and methods of use for canopy fragilization system

Patent metadata

Field	Value
Publication number	US-11345458-B2
Application number	US-202016938780-A
Country	US
Kind code	B2
Filing date	Jul 24, 2020
Priority date	Jul 24, 2020
Publication date	May 31, 2022
Grant date	May 31, 2022

Abstract

A canopy fragilization system for use in an aircraft ejection system may comprise: a sharp breaker disposed on a first side of an ejection seat, the sharp breaker configured to act as a primary breaker of a canopy of an aircraft; a blunt breaker disposed on a second side of the ejection seat, the blunt breaker configured to act as a secondary breaker of the canopy of the aircraft; and a deployable overhead protection assembly comprising a first tertiary breaker and a second tertiary breaker.

First claim

What is claimed is:

1. A deployable overhead protection assembly, comprising:
a base configured to pivotably couple to a headrest of an ejection seat;
a first stabilizer extending from a first side of the base, the first stabilizer having a first breaker disposed distal from the base;
a second stabilizer extending from a second side of the base, the second side opposite the first side, the second stabilizer including a second breaker disposed distal to the base; and
a mitt coupled to the base and disposed laterally between the first stabilizer and the second stabilizer.

2. The deployable overhead protection assembly of claim 1 , wherein the first breaker and the second breaker are configured to propagate cracks in a canopy of an aircraft forward during an ejection event.

3. The deployable overhead protection assembly of claim 1 , wherein:
the first stabilizer comprises a stabilizing portion and a breaker portion,
the stabilizing portion configured to stabilize a head of an occupant during an ejection of the occupant, and
the breaker portion including the first breaker and configured to impact a canopy of an aircraft during an ejection event.

4. The deployable overhead protection assembly of claim 1 , wherein the first breaker and the second breaker are blunt breakers.

5. The deployable overhead protection assembly of claim 1 , wherein the first stabilizer and the second stabilizer extend vertically above the mitt when in a deployed position.

6. The deployable overhead protection assembly of claim 1 , further comprising a first cable configured to extend from the first breaker to a sharp breaker of a canopy fragilization system, and a second cable configured to extend from the second breaker to a blunt breaker of the canopy fragilization system.

7. A canopy fragilization system for use in an aircraft ejection system, the canopy fragilization system comprising:
a sharp breaker disposed on a first side of an ejection seat, the sharp breaker configured to act as a primary breaker of a canopy of an aircraft;
a blunt breaker disposed on a second side of the ejection seat, the blunt breaker configured to act as a secondary breaker of the canopy of the aircraft; and
a deployable overhead protection assembly comprising a first tertiary breaker and a second tertiary breaker.

8. The canopy fragilization system of claim 7 , wherein:
the first tertiary breaker is disposed on a first stabilizer of the deployable overhead protection assembly, and
the second tertiary breaker is disposed on a second stabilizer of the deployable overhead protection assembly.

9. The canopy fragilization system of claim 8 , wherein the first tertiary breaker and the second tertiary breaker are disposed forward of the sharp breaker and the blunt breaker.

10. The canopy fragilization system of claim 8 , wherein the deployable overhead protection assembly further comprises a first cable extending from the first tertiary breaker and a second cable extending from the second tertiary breaker to the blunt breaker.

11. The canopy fragilization system of claim 10 , further comprising the canopy of an aircraft, wherein the first cable and the second cable are configured to saw through the canopy of the aircraft.

12. The canopy fragilization system of claim 7 , wherein the deployable overhead protection assembly further comprises a base, a first stabilizer extending from a first side of the base and a second stabilizer extending from a second side of the base, a mitt coupled to the base and disposed laterally between the first stabilizer and the second stabilizer.

13. The canopy fragilization system of claim 12 , wherein the first stabilizer and the second stabilizer extend vertically above the mitt when in a deployed position.

14. The canopy fragilization system of claim 7 , wherein the first tertiary breaker and the second tertiary breaker are configured to propagate cracks in the canopy of the aircraft forward during an ejection event.

15. A method for fragilizing a canopy of an aircraft during an ejection event, the method comprising: exerting a first impulse on the canopy of an aircraft with a sharp breaker; exerting a second impulse on the canopy of the aircraft with a blunt breaker; exerting a third impulse on the canopy with a first tertiary breaker disposed forward of the sharp breaker and the blunt breaker; and exerting a fourth impulse on the canopy with a second tertiary breaker disposed forward of the sharp breaker and the blunt breaker, wherein: the first tertiary breaker is disposed on a first stabilizer of a deployable overhead protection assembly, and the second tertiary breaker is disposed on a second stabilizer of the PHNP assembly.

16. The method of claim 15 , further comprising sawing through the canopy with a first cable and a second cable.

17. The method of claim 16 , wherein the first cable extends from the first tertiary breaker to the sharp breaker and the second cable extends from the second tertiary breaker to the blunt breaker.

18. The method of claim 15 , wherein a first crack generated from the sharp breaker and a second crack generated from the blunt breaker propagate forward on the canopy in response to contacting the canopy with the first tertiary breaker and the second tertiary breaker.

19. The method of claim 15 , further comprise pushing the canopy with the blunt breaker.

Assignees

• Ami Ind Inc

Inventors

• Holstine Steven A
• Eischeid Nathan
• Mastrolia Bradley
• Hampton John
• Cross Neil
• Carson Kassidy L
• Haas Ian Walter
• Hyde Patrick Emmett
• Keene Aaron H
• Teal Cyle
• Wade John

Classifications

• B64D25/08

  Ejecting or escaping means · CPC title

• B64D25/04

  Seat modifications · CPC title

• B64C1/32 Primary

  Severable or jettisonable parts of fuselage facilitating emergency escape · CPC title

• B64D25/10 Primary

  Ejector seats · CPC title