When doing the initial sizing of a space craft, a simple two step approach must be followed:

1. Size for dynamic loads: The natural frequencies of the spacecraft > the natural frequencies of the launcher. The natural frequency is defined as:

2. Check that design can withstand the quasi static-loads.

The second step is realised by checking that:

1. The resulting stress due to the launch load < allowable stress, which is equal to the ultimate stress divided by the safety factor
2. The axial load < buckling load of the structure.

Launch loads and minimum natural frequencies for each launcher are specified in the launch vehicles user manual. So the adagio RTFM (Read that fine manual) really does apply!

[image NASA, Public Domain]