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, except it consisted of an ordinary S-IC first stage and S-IVB second stage.[1]: 1102 For deep-space missions, a Centaur third stage could also have been used.
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Transcription
Details
Details [2] 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
- ^ Scott, Ronald D.; Corcoran, William L. (1968). "Saturn V Derivatives". SAE Transactions. 77. SAE International: 1099–1112. JSTOR 44565202.
- ^ "Saturn V-A". Archived from the original on 2011-10-11. Retrieved 2011-09-29. Saturn V-A
| Early proposals |  | |
|---|---|---|
| "C" series | ||
| Saturn I series | ||
| Saturn II series | ||
| Saturn V series | ||
This page was last edited on 6 January 2024, at 21:17