Saturn V-A was a proposed American orbital launch vehicle. It was studied by Marshall Space Flight Center in 1968. the Saturn V-A was identical to the

Saturn INT-20 The Saturn INT-20 was a proposed intermediate-payload follow-on from the Apollo Saturn V launch vehicle. A conical-form interstage would be fitted on top of the S-IC stage to support the S-IVB stage, so it could be considered either a retrofitted ...

, except it consisted of an ordinary S-IC first stage and

S-IVB The S-IVB (pronounced "S-four-B") was the third stage on the Saturn V and second stage on the Saturn IB launch vehicles. Built by the Douglas Aircraft Company, it had one J-2 rocket engine. For lunar missions it was fired twice: first for Earth ...

second stage. For deep-space missions, a Centaur third stage could also have been used.

Details

Details Saturn V-A of Saturn V-A:
Gross mass: 2,478,120 kg (5,463,310 lb).
Payload: 60,000 kg (132,000 lb).
Height: 72.00 m (236.00 ft).
Diameter: 10.06 m (33.00 ft).
Thrust: 33,737.90 kN (7,584,582 lbf).
Apogee: 185 km (114 mi).

References

{{Saturns Saturn (rocket family)