Composite sandwich panel and method of making same

An air cargo container for carrying cargo in the lower deck or upper deck of a wide-bodied airplane, comprising:

• a floor,
• a top;
• a plurality of wall panels joining the floor and the top, wherein one or more of the top, the floor and the wall panels include a first skin, a second skin, and a core;
• and
• a plurality of distinct groupings of Z-axis fibers that extend through the core from the first skin to the second skin, the Z-axis fibers including opposite ends respectively terminating at and integrated into the first skin and the second skin, wherein the plurality of distinct groupings of Z-axis fibers form structural stringers and recesses, the structural stringers formed by absence of second skin other than areas where the Z-axis fibers terminate at and are integrated into the second skin and absence of substantially all of the core other than areas of the Z-axis fibers.

A composite panel, comprising:

• a first skin;
• a second skin;
• a core;
• and
• a plurality of distinct groupings of Z-axis fibers that extend through the core from the first skin to the second skin, the Z-axis fibers including opposite ends respectively terminating at and integrated into the first skin and the second skin,
• wherein the plurality of distinct groupings of Z-axis fibers form structural stringers and recesses in the composite panel, the structural stringers formed by absence of second skin other than areas where the Z-axis fibers terminate at and are integrated into the second skin and by absence of substantially all of the core in and around the Z-axis fibers.