Spacecraft Structural Design & Analysis Mastery Hub: The Ind

In the context of spacecraft primary structure design, what is the primary rationale for utilizing a monocoque or semi-monocoque construction over a simpler frame-and-skin design when dealing with significant launch vehicle loads?

During the preliminary design phase of a spacecraft primary structure, which of the following analyses is MOST critical for assessing the potential for global buckling of the pressurized structure under external vacuum conditions?

When designing a primary structural element for a spacecraft that will experience significant thermal gradients, what is the MOST appropriate approach to mitigate the risk of thermal stress-induced deformation and potential failure?