초록 ▼

An aircraft panel comprising a sandwich construction with an outer skin portion of high strength material, an inner portion of high strength material and an intermediate core material. The core material includes areas with low density core material and a reinforcement grid of high strength material,

An aircraft panel comprising a sandwich construction with an outer skin portion of high strength material, an inner portion of high strength material and an intermediate core material. The core material includes areas with low density core material and a reinforcement grid of high strength material, with longitudinal and transversal grid members.

대표청구항 ▼

The invention claimed is: 1. An aircraft fuselage skin panel comprising a sandwich construction with an outer skin portion of high strength material, an inner skin portion of high strength material and an intermediate core material, wherein the core material includes areas with low density core mat

The invention claimed is: 1. An aircraft fuselage skin panel comprising a sandwich construction with an outer skin portion of high strength material, an inner skin portion of high strength material and an intermediate core material, wherein the core material includes areas with low density core material and a reinforcement grid of high strength material, the reinforcement grid of high strength material including a plurality of axially aligned longitudinal grid members dispersed within the outer ends of the core material for the aircraft panel and a plurality of transverse grid members, wherein a set of circumferential frames is attached to the aircraft fuselage skin panel and each circumferential frame in the set of circumferential frames attaches to the aircraft fuselage skin panel by using a set of fasteners extending through at least one of the plurality of transverse grid members. 2. The aircraft panel in accordance with claim 1, wherein the high strength material is aluminum. 3. The aircraft panel in accordance with claim 1, wherein the low density core material is a lightweight plastic foam. 4. The aircraft panel in accordance with claim 1, wherein the low density core material is a lightweight aluminum foam. 5. The aircraft panel in accordance with claim 1, wherein the transverse grid members are arranged to support and provide fixing points for frames. 6. An aircraft fuselage skin panel comprising a sandwich construction with an outer aluminum slain portion, an inner aluminum skin portion and an intermediate core material, wherein the core material includes areas with lightweight plastic foam and a reinforcement grid of aluminum the reinforcement grid of high strength material including a plurality of axially aligned longitudinal grid members dispersed within the outer ends of the core material for the aircraft panel and a plurality of transverse grid members and that the core material, the inner and outer skin form a sandwich panel, wherein a set of circumferential frames is attached to the aircraft fuselage skin panel and each circumferential frame in the set of circumferential frames attaches to the aircraft fuselage skin panel by using a set of fasteners extending through at least one of the plurality of transverse grid members.