Sandwich panel with integrated reinforcing structure and method for the production thereof
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B32B-003/08
B32B-003/12
B29C-070/86
B29C-073/06
B29D-024/00
B29D-099/00
B64C-001/18
B29K-105/08
B29L-031/30
B29L-031/60
출원번호
US-0013558
(2011-01-25)
등록번호
US-8741416
(2014-06-03)
우선권정보
DE-10 2008 041 788 (2008-09-03)
발명자
/ 주소
Juergens, Manuela (Richter)
출원인 / 주소
Airbus Operations GmbH
대리인 / 주소
Jenkins, Wilson, Taylor & Hunt, P.A.
인용정보
피인용 횟수 :
2인용 특허 :
10
초록▼
A Sandwich panel with a core structure, in particular with a honeycomb-shaped core structure, and plane-parallel cover layers applied to both sides of this core structure, to form a floor surface in a fuselage airframe of an aircraft, the core structure having at least one recess into which at least
A Sandwich panel with a core structure, in particular with a honeycomb-shaped core structure, and plane-parallel cover layers applied to both sides of this core structure, to form a floor surface in a fuselage airframe of an aircraft, the core structure having at least one recess into which at least one reinforcing structure is integrated, wherein the at least one reinforcing structure is formed with at least one core, said core having at least one recess into which a stopper is introduced, into which at least one attachment element can be introduced to attach at least one further component to the sandwich panel, and a plurality of prepreg strips which each have a uniform fiber running direction being wound around the core. In addition, the invention relates to a method for the production of a sandwich panel according to the invention.
대표청구항▼
1. An aircraft comprising at least one sandwich panel with a core structure comprising a honeycomb-shaped core structure, and plane-parallel cover layers applied to both sides of the core structure, the core structure having at least one recess into which at least one reinforcing structure is integr
1. An aircraft comprising at least one sandwich panel with a core structure comprising a honeycomb-shaped core structure, and plane-parallel cover layers applied to both sides of the core structure, the core structure having at least one recess into which at least one reinforcing structure is integrated, wherein the at least one reinforcing structure is formed with at least one core, said at least one core having at least one recess into which a stopper is introduced, wherein at least one attachment element can be introduced into the stopper to attach at least one further component to the sandwich panel, and a plurality of prepreg strips which each have a uniform fibre running direction being wound around the core, wherein the prepreg strips are guided around the outer edges of the core and surround the core on all sides. 2. The aircraft according to claim 1, wherein the uniform fibre running direction is ±45°. 3. The aircraft according to claim 1, wherein the at least one reinforcing structure is provided at least in certain regions with at least one two-dimensional blank, the at least one two-dimensional blank being formed from a prepreg material comprising reinforcing fibres, the reinforcing fibres of the prepreg material having a fibre running direction of 0° and/or 90°. 4. The aircraft according to claim 1, wherein the at least one reinforcing structure can be introduced into the at least one recess inside the core structure in an interlocking manner at least in certain regions, and forms a material bond with the at least one recess. 5. The aircraft according to claim 1, wherein the at least one core is formed with a core structure comprising a honeycomb-shaped core structure, and/or with a rigid foam. 6. The aircraft according to claim 1, wherein the at least one reinforcing structure is formed by a combination of at least two reinforcing structures. 7. The aircraft according to claim 1, wherein the stopper is configured cylindrically. 8. The aircraft according to claim 1, wherein the stopper is formed from a fibre-reinforced plastics material comprising a plurality of plane parallel superimposed circular layers formed using a prepreg material which has not fully cured at the time of processing. 9. The aircraft according to claim 1, wherein the at least one sandwich panel with a core structure is a floor panel. 10. The aircraft according to claim 1, wherein a filling compound is introduced at least in one region of the core structure. 11. The aircraft according to claim 10, wherein the region is peripheral region surrounding the reinforcing structure. 12. The aircraft according to claim 10, wherein the filling compound is a curable plastics material.
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