I'm looking for specifics as to how preliminary analysis on spacecraft primary structure is performed (prior to CLA).

I understand LV providers include CG load factors in their user manuals, but how exactly is this information used? Is it as simple as creating a FEM, fixing the spacecraft base (how it would be secured to the LV), and then applying the different loads through the corresponding axes?

For example, the below table is taken from ECSS-E-HB-32-26A: Spacecraft Mechanical Loads Analysis Handbook for Ariane 5. Would I step through each flight phase and apply the combination of longitudinal and lateral accelerations? What is meant by "static" acceleration here and what is the additional line load?

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