Patent ID: 7628358

Claim:
A panel structure for an aerospace vehicle, comprising: a first portion of the panel structure; a second portion of the panel structure; an outer layer of material having a predetermined thickness and extending across both the first portion and the second portion of the panel structure; a core structure placed on the outer layer of material and included in the first portion of the panel structure; an inner layer of material formed at least on the core structure, wherein the inner layer of material has a selected thickness less than the predetermined thickness of the outer layer of material; a stiffener formed on the outer layer of material and included in the second portion of the panel structure, wherein the stiffener has a predetermined structural shape comprising a flange formed on the outer layer and a member extending from the flange on an opposite side from the outer layer; and a support rib formed on the inner layer of material between the stiffener and an assembly including the core structure and the inner layer of material, wherein the inner layer of material extends under the support rib and overlaps a portion of the flange of the stiffener.