Spacecraft panel and method

A method of manufacturing a spacecraft panel, comprising:

• printing a first skin with a first outer surface, a first inner surface, and a first thickness;
• printing a first grid of stiffeners along the first inner surface comprising one or more first grid units;
• printing a second skin with a second outer surface, a second inner surface, and a second thickness, the second skin being spaced apart from the first skin with the second inner surface facing the first inner surface;
• printing a second grid of stiffeners along the second inner surface comprising one or more second grid units;
• and
• printing a plurality of cross-shaped truss members of a first truss structure connecting the first skin to the second skin,
• wherein:
• each cross-shaped truss member consists of:
• two first legs that extend from first nodes on the first inner surface of the first skin and converge to a central join region situated between the first skin and the second skin;
• and
• two second legs that diverge and extend from the central join region to second nodes on the second inner surface of the second skin;
• the first nodes are defined at first intersections of the first grid of stiffeners;
• the second nodes are defined at second intersections of the second grid of stiffeners;
• the first grid units are offset from the second grid units such that when viewed along a direction normal to the first skin, each one of the first nodes is aligned with a geometric center of one of the second grid units;
• and
• each cross-shaped truss member is integral to and spans a gap between the first skin and the second skin and the first skin, the second skin, and the first truss structure collectively form a single monolithic joint-free structure.