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

Patent metadata

Field	Value
Publication number	US-11396359-B2
Application number	US-202016983828-A
Country	US
Kind code	B2
Filing date	Aug 3, 2020
Priority date	Aug 3, 2020
Publication date	Jul 26, 2022
Grant date	Jul 26, 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 mitt extending forward of the sharp breaker and the blunt breaker when in a deployed position, a forward end of the mitt configured to act as a tertiary breaker of the canopy of the aircraft.

First claim

What is claimed is:

1. 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 mitt extending forward of the sharp breaker and the blunt breaker when in a deployed position, a forward end of the mitt configured to act as a tertiary breaker of the canopy of the aircraft.

2. The canopy fragilization system of claim 1 , wherein the blunt breaker is configured to propagate a first crack generated from the sharp breaker laterally, and wherein the forward end of the mitt is configured to propagate a second crack generated from the blunt breaker and the first crack forward along the canopy.

3. The canopy fragilization system of claim 1 , wherein the mitt is configured to extend forward of a head of an occupant when in the deployed position.

4. The canopy fragilization system of claim 1 , wherein the deployable overhead protection assembly further comprises a piercer disposed at the forward end of the mitt.

5. The canopy fragilization system of claim 4 , wherein the piercer comprises a bracket portion and a sharp portion, the bracket portion coupled to the mitt, the sharp portion configured to pierce the canopy.

6. The canopy fragilization system of claim 1 , 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, the mitt coupled to the base and disposed laterally between the first stabilizer and the second stabilizer.

7. The canopy fragilization system of claim 6 , wherein:
the first stabilizer extends a first forward distance from a headrest when in the deployed position,
the mitt extends a second forward distance from the headrest when in the deployed position, and
the second forward distance being between about 1.5 to 2.5 times the first forward distance.

8. The canopy fragilization system of claim 1 , wherein the mitt is configured to transfer an impact load to the ejection seat during an ejection event.

9. A method for fragilizing a canopy of an aircraft during an ejection event, the method comprising:
exerting a first impulse on the canopy of the aircraft with a primary breaker;
exerting a second impulse the canopy of the aircraft with a secondary breaker; and
exerting a third impulse on the canopy with a deployable overhead protection assembly comprising a mitt extending forward of the primary breaker and the secondary breaker during exerting the third impulse.

10. The method of claim 9 , wherein exerting the third impulse on the canopy with the deployable overhead protection assembly further comprises contacting the canopy with a forward end of the mitt.

11. The method of claim 9 , wherein exerting the third impulse on the canopy with the deployable overhead protection assembly further comprises contacting the canopy with a piercer coupled to the mitt.

12. The method of claim 9 , wherein:
the primary breaker is a sharp breaker,
the secondary breaker is a blunt breaker, and
the deployable overhead protection assembly includes a tertiary breaker.

13. The method of claim 9 , wherein a first crack generated from the primary breaker and a second crack generated from the secondary breaker propagate forward on the canopy in response to third impulse on the canopy with the deployable overhead protection assembly.

14. The method of claim 9 , wherein the first impulse is greater than the second impulse.

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

• B64C1/14

  Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens {accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers}(fairings movable in conjunction with undercarriage elements B64C25/16; bomb doors B64D1/06) · CPC title

• B64C1/32 Primary

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

• B64D25/04

  Seat modifications · CPC title

• B64C1/1476

  Canopies; Windscreens or similar transparent elements · CPC title

• B64D25/08

  Ejecting or escaping means · CPC title