Morphable ceramic composite skins and structures for hypersonic flight
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64D-029/00
B64C-009/02
B64C-009/00
B32B-005/08
출원번호
UP-0432865
(2006-05-11)
등록번호
US-7516918
(2009-07-01)
발명자
/ 주소
Cox, Brian N.
Davis, Janet B.
dos Santos e Lucato, Sergio Luis
Marshall, David B.
McCabe, Brock S.
Sudre, Olivier H.
출원인 / 주소
The Boeing Company
대리인 / 주소
Toler Law Group
인용정보
피인용 횟수 :
3인용 특허 :
5
초록▼
An exemplary morphable ceramic composite structure includes a flexible ceramic composite skin and a truss structure attached to the skin. The truss structure can morph shape of the skin from a first shape to a second shape that is different than the first shape. The flexible ceramic composite skin m
An exemplary morphable ceramic composite structure includes a flexible ceramic composite skin and a truss structure attached to the skin. The truss structure can morph shape of the skin from a first shape to a second shape that is different than the first shape. The flexible ceramic composite skin may include a single-layer of three-dimensional woven fabric fibers and a ceramic matrix composite. The truss structure may include at least one actuatable element or an actuator may move a portion of the truss structure from a first position to a second position. A cooling component may be disposed in thermal communication with the skin. The cooling component may include thermal insulation or a cooling system that circulates cooling fluid in thermal communication with the skin. The morphable ceramic composite structure may be incorporated into any of an air inlet, combustor, exhaust nozzle, or control surfaces of a hypersonic aircraft.
대표청구항▼
What is claimed is: 1. A morphable ceramic composite structure comprising: a flexible ceramic composite skin including a single-layer of three-dimensional woven fabric fibers that define a plurality of loops; and a truss structure attached to the plurality of loops of the flexible ceramic composite
What is claimed is: 1. A morphable ceramic composite structure comprising: a flexible ceramic composite skin including a single-layer of three-dimensional woven fabric fibers that define a plurality of loops; and a truss structure attached to the plurality of loops of the flexible ceramic composite skin, the truss structure being arranged to morph shape of the skin from a first shape to a second shape that is different than the first shape. 2. The structure of claim 1, wherein the ceramic composite skin further includes a fiber-matrix combination, wherein: the fiber includes a fiber chosen from a group including carbon, SiC, alumina, mullite, refractory carbides, borides, nitrides, and oxides; and the matrix includes a material chosen from a group including carbon, SiC, alumina, mullite, refractory carbides, borides, nitrides, and oxides. 3. The structure of claim 2, wherein the fiber-matrix combination includes a fiber-matrix combination chosen from a group that includes C--SiC and SiC--SiC. 4. The structure of claim 1, wherein the truss structure is made from a material chosen from a group including a superalloy, a molybdenum alloy, a niobium alloy, and a ceramic composite matrix. 5. The structure of claim 1, wherein the truss structure includes at least one actuatable element. 6. The structure of claim 5, wherein the actuatable element includes an actuator chosen from a group including a shape memory alloy actuator and an electric stepper motor and a piezoelectric motor and a piezo-hydraulic motor. 7. The structure of claim 1, further comprising an actuator that is arranged to move a portion of the truss structure from a first position to a second position. 8. The structure of claim 1, further comprising a cooling component in thermal communication with the skin. 9. The structure of claim 8, wherein the cooling component includes thermal insulation. 10. The structure of claim 8, wherein the cooling component includes a cooling system configured to circulate a cooling fluid in thermal communication with the skin. 11. The structure of claim 10, wherein; the skin includes a plurality of ceramic matrix composite tubes; and the cooling system is further configured to circulate the coolant inside the plurality of tubes. 12. A morphable ceramic composite structure comprising: a flexible ceramic composite skin; a truss structure attached to the skin, the truss structure being arranged to morph shape of the skin from a first shape to a second shape that is different than the first shape, the truss structure including at least one actuatable element, the truss structure being made from a material chosen from a group including a superalloy, a molybdenum alloy, a niobium alloy, and a ceramic composite matrix; and a cooling system configured to circulate a cooling fluid in thermal communication with the skin. 13. The structure of claim 12, wherein the actuatable element includes an actuator chosen from a group including a shape memory alloy actuator and an electric stepper motor and a piezoelectric motor and a piezo-hydraulic motor. 14. A morphable ceramic composite structure comprising: a flexible ceramic composite skin including a single-layer of three-dimensional woven fabric fibers that define a plurality of loops; a truss structure attached to the plurality of loops of the flexible ceramic composite skin, the truss structure being arranged to morph shape of the skin from a first shape to a second shape that is different than the first shape, the truss structure being made from a material chosen from a group including a superalloy, a molybdenum alloy, a niobium alloy, and a ceramic composite matrix; and an actuator that is arranged to move a portion of the truss structure from a first position to a second position. 15. A hypersonic aircraft comprising: a fuselage; a plurality of control surfaces; and a scramjet engine including an air inlet, a combustor, and an exhaust nozzle; wherein at least one of the air inlet, the combustor, the exhaust nozzle, and the plurality of control surfaces includes: a flexible ceramic composite skin including a single-layer of three-dimensional woven fabric fibers that define a plurality of loops; and a truss structure attached to the plurality of loops of the flexible ceramic composite skin, the truss structure being arranged to morph shape of the skin from a first shape to a second shape that is different than the first shape. 16. The aircraft of claim 15, wherein the truss structure includes at least one actuatable element. 17. The aircraft of claim 15, further comprising an actuator that is arranged to move a portion of the truss structure from a first position to a second position. 18. The aircraft of claim 15, further comprising a cooling component in thermal communication with the skin.
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이 특허에 인용된 특허 (5)
Webb Brent J. (Richland WA) Antoniak Zen I. (Richland WA) Prater John T. (Chapel Hill NC) DeSteese John G. (Kennewick WA), Composite metal foil and ceramic fabric materials.
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