Re: After the shuttle

I designed a system that consisted of a single SSME derivative and four
RL10 in the first stage and four RL10 in the second stage. The system
could place 9,000 kg into LEO. This fully reusable system collected
the first stage downrange and returned it to the launch center after
it made a soft landing. The orbiting portion landed at the launch
center. Both landed under rocket power like the DC10.

Then, there is the potential to use the ET along with a 'pod'
containing seven SSME. The pod is placed under the ET and the pod is
recovered downrange. A more advanced version allows the ET plus pod to
be recovered. This advanced ET deploys winglets and the vehicle glides
to a landing. Aircraft downrange snag the ET and tow it back to base
for release.

The simplest system has a single ET combined with a first stage of the
system described above to place 45,000 kg into LEO.

Next, is a system containing 3 stages to put 9,000 kg on a lunar free
return trajectory.

The next system consists of three ET with cross feeding. These ET place
150,000 kg into LEO. More payload than Apollo. This permits landing
9,000 kg on the lunar surface

The next system consists of 7 ET with cross feeding. These ET place
500,000 kg into LEO. Thispermits landing 50,000 kg on the lunar
surface.

The three element system is configured as;

1 -> 2 <- 3

The seven element system is configured as

1 2
3 4 5
6 7

1 and 6 feed fuel into 3, 3 feeds fuel into 4
2 and 7 feed fuel into 5 5 feeds fuel into 4

Here 1,2, 6,7 drain and are dropped. Then, 3 and 5 drain and are
dropped. 4 is the remaining sustainer.

.