| Country of origin | United States |
|---|---|
| Size | |
| Height | 58.00 m (190.00 ft) |
| Diameter | 8.38 m (27.49 ft) |
| Mass | 1,154,000 kg (2,544,000 lb) |
| Stages | 3 |
| Capacity | |
| Payload to LEO |
38 000 kg |
| Payload to GTO |
13 000 kg |
| First Stage | |
| Engines | 2x F-1 |
| Thrust | 15,481.26 kN |
| Specific impulse | 304 seconds (vacuum) |
| Burn time | 170 seconds |
| Fuel | LOX/RP-1 |
| Second Stage | |
| Engines | 1x J-2 |
| Thrust | 1 031,98 kN |
| Specific impulse | 425 seconds (vacuum) |
| Burn time | 525 seconds |
| Fuel | LOX/LH2 |
| Third Stage | |
| Engines | 8x R-4D |
| Thrust | 3,92 kN (vacuum) |
| Specific impulse | 312 seconds[1] |
| Fuel | N2O4/MMH |
Studied in 1985, long after the Saturn V had been retired, the Jarvis would be used for Pacific launches and would once again utilize the engines from the Saturn V, except that the Jarvis' third stage would use an R-4D engine that was developed for the Apollo Service and Lunar Module used in preparations for landing on the moon from 1968–72. The R-4D was currently at the time of study used on numerous spacecraft manufactured by Hughes, including Syncom 4 launched by the Space Shuttle from 1984–85, but the other engines were definitely retired at the end of Project Apollo.
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