|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||181/213 ; 298/900.8|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 19 인용 특허 : 22|
An acoustic panel (26) for the nacelle (20) of a high bypass jet engine. The acoustic panel (26) has a perforated composite inner sheet (54), an outer composite sheet (96, 98), and a honeycomb-core material (74) sandwiched therebetween. The acoustic panel (26) includes an integral forward ring (36) and integral wedge fairings (44).
[ What is claimed is:] [1.] A method of forming a forward ring integral with a composite panel, comprising the steps of:stacking an inner face sheet, a honeycomb core, and first outer face sheet on a lay-up mandrel;arranging composite material for an integral ring against the lay-up mandrel having a contour that substantially matches an intended final shape of the integral ring;placing a plug against the side of the composite material for the integral ring opposite of the contour of the lay-up mandrel;bagging the acoustic panel with a vacuum bag so that ...