Non-ceramic structural panel with ballistic protection
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B32B-003/06
B32B-005/26
B32B-007/08
B32B-015/14
B32B-015/20
B32B-003/08
출원번호
US-0224677
(2011-09-02)
등록번호
US-9321238
(2016-04-26)
발명자
/ 주소
Bird, Connie E.
Goodworth, Alan R.
Carstensen, Thomas A.
Hamilton, Gary
출원인 / 주소
Sikorsky Aircraft Corporation
대리인 / 주소
Carlson, Gaskey & Olds, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
15
초록
An armor panel includes a multiple of pins which penetrate a first skin, a high molecular weight polyethylene fiber composite material layer and a second skin which integrates ballistic protection into load bearing structure.
대표청구항▼
1. An armor panel comprising: a pressure-consolidated, high molecular weight polyethylene fiber composite material layer;a first skin on a first side of said high molecular weight polyethylene fiber composite material layer;a second skin on a second side of said high molecular weight polyethylene fi
1. An armor panel comprising: a pressure-consolidated, high molecular weight polyethylene fiber composite material layer;a first skin on a first side of said high molecular weight polyethylene fiber composite material layer;a second skin on a second side of said high molecular weight polyethylene fiber composite material layer; anda multiple of pins which penetrate said first skin, said high molecular weight polyethylene fiber composite material layer and said second skin, said polyethylene fiber composite material layer stabilizing said multiple of pins from buckling, wherein said multiple of pins form a truss structure with said first skin and said second skin. 2. The armor panel as recited in claim 1, wherein said first skin is a structural material. 3. The armor panel as recited in claim 2, wherein said structural material is S2 glass composite fibers in API SC-15 toughened epoxy resin. 4. The armor panel as recited in claim 2, wherein said structural material is a metal alloy. 5. The armor panel as recited in claim 4, wherein said metal alloy is titanium. 6. The armor panel as recited in claim 4, wherein said metal alloy is aluminum. 7. An aircraft comprising: an airframe; anda structural panel mounted to said airframe, said structural panel includes a pressure-consolidated, high molecular weight polyethylene fiber composite material layer, a first skin on a first side of said high molecular weight polyethylene fiber composite material layer, a second skin on a second side of said high molecular weight polyethylene fiber composite material layer, and a multiple of pins which penetrate said first skin, said high molecular weight polyethylene fiber composite material layer and said second skin, said polyethylene fiber composite material layer stabilizing said multiple of pins from buckling, wherein said multiple of pins form a truss structure with said first skin and said second skin. 8. The aircraft as recited in claim 7, wherein said first skin is a structural material. 9. The aircraft as recited in claim 7, wherein said first skin is S2 glass composite fibers in API SC-15 toughened epoxy resin. 10. The aircraft as recited in claim 7, wherein said first skin is a metal alloy. 11. The aircraft as recited in claim 7, wherein said airframe includes a multitude of frame members and a multitude of beam members. 12. A method of armoring an aircraft comprising: mounting a structural panel to an airframe, the structural panel includes a pressure-consolidated, high molecular weight polyethylene fiber composite material layer, a first skin on a first side of said high molecular weight polyethylene fiber composite material layer, a second skin on a second side of said high molecular weight polyethylene fiber composite material layer, and a multiple of pins which penetrate said first skin, said high molecular weight polyethylene fiber composite material layer and said second skin, said polyethylene fiber composite material layer stabilizing said multiple of pins from buckling, wherein said multiple of pins form a truss structure with said first skin and said second skin. 13. The method as recited in claim 12, further comprising mounting the structural panel as a floor. 14. The method as recited in claim 12, further comprising mounting the structural panel as a skin. 15. The method as recited in claim 12, further comprising mounting the structural panel within a fan blade containment assembly. 16. The armor panel as recited in claim 1, wherein said pressure-consolidated, high molecular weight polyethylene fiber composite material layer includes a pressure-consolidated matrix material. 17. The armor panel as recited in claim 1, wherein said pressure-consolidated, high molecular weight polyethylene fiber composite material layer is one of a plurality of pressure-consolidated, high molecular weight polyethylene fiber composite material layers arranged in an alternating layer arrangement with non-ballistic layers. 18. The armor panel as recited in claim 17, wherein said non-ballistic layers are foam. 19. The armor panel as recited in claim 1, wherein said first skin and said second skin extend laterally beyond said pressure-consolidated, high molecular weight polyethylene fiber composite material layer, said first skin and said second skin meeting and joining at an edge flange. 20. The armor panel as recited in claim 1, wherein said pressure-consolidated, high molecular weight polyethylene fiber composite material layer is a layer of a carrier including additional layers, said carrier, said first skin and said second skin fully encasing said multiple of pins.
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이 특허에 인용된 특허 (15)
Cordova David S. (Midlothian VA) Kirkland Kevin M. (Richmond VA), Armor systems.
Bouillon,Eric; Coupe,Dominique; Bouvier,R?mi; Philippe,Eric, Making composite material parts from blanks made by reinforcing a fiber structure and/or bonding fiber structures together.
Rein Dimitry,ILX ; Vaykhansky Ley,ILX ; Cohen Yachin,ILX, Ultra-high molecular weight polyolefin fiber composite matrix, and process for the manufacture thereof.
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