"Proponent" wrote in message
ups.com...

Then there's the S-II stage, which seems to have been the bottleneck in
the development of the Saturn V. Why was it so troublesome? Was it
incompetence at North American Aviation? The stage's mass structure
fraction was lower than that of the other H2 stages. Although that's
natural for a larger stage, does it indicate that the S-II design was
sailing closer to the wind? Was that a source of development problems?

The reason I ask is that I'm wondering when a Saturn C-3-class booster
might have become operational under the previously posted question
about multi-launch LOR missions.


Start with this book and reference: Stages of Saturn
Should answer most questions asked.

gb