发明名称 Aircraft cowl
摘要 To produce a monolithic and composite panel structure, it is fitted with openings such as for access ports, flaps and/or ventilation grills. A network of beams is positioned to take up the forces between the panel linkages and the panel, while avoiding the access points. The network is composed of axial and curved peripheral beams. The cross section is varied along the length of at least one beam. The mold is covered with a composite material, forming the panel body. The network is structured by a honeycomb or a foam material, with closed cells as a core, to be covered by a composite material partially over the panel to form the strengthening beams. The structure is polymerized by heat. The honeycomb core has a high density to take the linkages. The heat polymerization is in two stages, with the first to mold the panel and the second after the beam network has been formed. One of the stages has a layer of high conductivity between the mold and the first layer. An Independent claim is included for a molded panel with openings for service ports (26,28), ventilation flaps and/or grills, with a network of beams (54,56) to take up the forces between the linkages (16,36) for the panel, and avoid the structured openings. Preferred Features: The beams (54,56) have an omega shape. The panel has additional stiffeners (14), and additional equipment such as access shutters (28) or openings (26). The panel has mountings (16) such as hinge supports (36) and hinge locks (20) at the beams. The mountings (16) and/or locks (20) have cores of a high density honeycomb material. Piston cylinders, to open the panel structure, are attached to the same beam as for the hinges (36).
申请公布号 FR2771330(A1) 申请公布日期 1999.05.28
申请号 FR19970015180 申请日期 1997.11.26
申请人 AEROSPATIALE SOCIETE NATIONALE INDUSTRIELLE 发明人 PORTE ALAIN;ANDRE ROBERT
分类号 B29C70/30;B29D99/00;B64C1/14;B64D29/08;(IPC1-7):B29C70/30;B64D29/00;B64C25/00 主分类号 B29C70/30
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