Thermally activated variable stiffness composites for aircraft seals
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
H05B-006/64
B64C-003/56
출원번호
US-0166770
(2008-07-02)
등록번호
US-8476564
(2013-07-02)
발명자
/ 주소
Henry, Christopher P.
McKnight, Geoffrey P.
Herrera, Guillermo A.
Doty, Robert E.
Clemons, Richard Lee
Drouin, Jr., Donald V.
출원인 / 주소
The Boeing Company
대리인 / 주소
Yee & Associates, P.C.
인용정보
피인용 횟수 :
4인용 특허 :
2
초록▼
An apparatus has a first structure, a second structure, and an activated seal. The second structure has a first position adjacent to the first structure such that the first structure is not in contact with the second structure. The activated seal is attached to at least one of the first structure an
An apparatus has a first structure, a second structure, and an activated seal. The second structure has a first position adjacent to the first structure such that the first structure is not in contact with the second structure. The activated seal is attached to at least one of the first structure and the second structure. The activated seal has a variable stiffness that may be changed in response to a stimuli such that the activated seal is capable of being deformed when at least one of the first structure and the second structure are moved relative to each other.
대표청구항▼
1. An apparatus comprising: a first structure connected to a hinge;a second structure connected to the hinge, such that the first structure and the second structure are, in at least one position, beside each other but not in contact with each other; andan activated seal attached to at least one of t
1. An apparatus comprising: a first structure connected to a hinge;a second structure connected to the hinge, such that the first structure and the second structure are, in at least one position, beside each other but not in contact with each other; andan activated seal attached to at least one of the first structure and the second structure, the activated seal having a variable stiffness that may be changed in response to a stimulus, the activated seal being configured to deform from a first shape when at least one of the first structure and the second structure move from an original orientation relative to each other, the active seal further configured to substantially reform to the first shape when the first structure and the second structure return to their original orientation relative to each other. 2. The apparatus of claim 1, wherein the activated seal is a thermally activated seal, wherein the thermally activated seal is attached to the first structure and extends over a surface of the second structure in a first position and extends over the second structure when the second structure is in a second position, the stimulus is heat, and the activated seal is substantially rigid at a first temperature and substantially compliant at a second temperature such that the thermally activated seal is configured to be deformed when at least one of the first structure and the second structure are moved relative to each other. 3. The apparatus of claim 2, wherein the thermally activated seal is attached to the second structure. 4. The apparatus of claim 3, wherein the thermally activated seal provides an electrical connection between the first structure and the second structure. 5. The apparatus of claim 3, wherein the thermally activated seal comprises a first part and a second part, wherein the first part and the second part are configured to engage each other when the thermally active seal is substantially rigid at the first temperature. 6. The apparatus of claim 1, wherein the activated seal further comprises: a reinforcement material. 7. The apparatus of claim 6, wherein the reinforcement material is at least one of carbon fibers and an electrically conductive reinforcement material. 8. The apparatus of claim 1, wherein the activated seal is selected from one of a cantilevered bending seal, a stretching seal, and a compression gasket seal. 9. The apparatus of claim 1, wherein the first structure is a first aircraft structure and the second structure is a second aircraft structure. 10. The apparatus of claim 9, wherein the first aircraft structure and the second aircraft structure are part of an aircraft wing. 11. The activated seal of claim 1, configured to at least one of: fill, and cover, a gap between the first structure and the second structure. 12. The activated seal of claim 1, such that the stimuli is at least one of: a stress, a moisture, a pH, an electrical field, and a magnetic field. 13. An aircraft comprising: a fuselage;an outboard wing structure;an inboard wing structure;a hinge unit configured to allow the outboard wing structure to move relative to the inboard wing structure between a deployed position and a stowed position;an activated seal attached to at least one of the outboard wing structure and the inboard wing structure, such that the activated seal has a variable stiffness that may be changed in response to a stimulus to the activated seal such that the activated seal is configured to be deformed from a first shape when the outboard wing structure moves from a deployed position to a stowed position, and to substantially reform to the first shape when the outboard wing structure moves from the stowed position to the deployed position; andan activation unit configured to apply the stimulus to the activated seal activated seal is substantially compliant. 14. The hinge of claim 13, such that the hinge does not comprise a path motion that is initially downward and out before the outboard wing structure folds with inward rotation towards the inboard wing structure. 15. The hinge of claim 13, such that the hinge does not comprise a complex hinge mechanism that causes the outboard wing structure to move in a linear motion and a rotational motion. 16. The activated seal of claim 13, such that the stimulus comprises at least one of: a temperature, a stress, a moisture, a pH, an electrical field, and a magnetic field. 17. An apparatus comprising: a first structure;a second structure beside the first structure such that a gap exists between the first structure and the second structure;a hinge between the first structure and the second structure, configured such that the first structure and second structure move relative to each other unimpinged by each other without requiring either structure to move in both a rotational and linear motion relative to each other; andan activated seal attached to at least one of the first structure and the second structure, such that the activated seal is configured to at least one of: fill, or cover the gap, the activated seal further having a variable stiffness that may be changed in response to a stimulus, the stimulus comprising at least one of: a temperature, a stress, a moisture, a pH, an electrical field, and a magnetic field, the activated seal being further configured to deform from a first shape when at least one of the first structure and the second structure move from an original orientation relative to each other, the activated seal being further configured to substantially reform to the first shape when the first structure and the second structure return to their original orientation relative to each other.
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이 특허에 인용된 특허 (2)
Sanderson, Terry M.; Clark, Jamie W., Methods and apparatus for adjustable surfaces.
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