| Manufacturer | Hughes Aircraft / Boeing |
|---|---|
| Country of origin | United States |
| Size | |
| Height | 58 m (190 ft) |
| Diameter | 8.38 m (27.5 ft) |
| Mass | 1,154,000 kg (2,544,000 lb) |
| Stages | 3 |
| Capacity | |
| Payload to LEO | |
| Mass | 38,000 kg (84,000 lb) |
| Payload to GTO | |
| Mass | 13,000 kg (29,000 lb) |
| Launch history | |
| Status | None built |
| Total launches | 0 |
| First stage | |
| Powered by | 2x F-1 |
| Maximum thrust | 15,481.26 kN (3,480,330 lbf) |
| Specific impulse | 304 seconds (vacuum) |
| Burn time | 170 seconds |
| Propellant | RP-1 / LOX |
| Second stage | |
| Powered by | 1x J-2 |
| Maximum thrust | 1,031.98 kN (232,000 lbf) |
| Specific impulse | 425 seconds (vacuum) |
| Burn time | 525 seconds |
| Propellant | LH2 / LOX |
| Third stage | |
| Powered by | 8x R-4D |
| Maximum thrust | 3.92 kN (880 lbf) |
| Specific impulse | 312 seconds |
| Propellant | MMH / N2O4 |
Jarvis was a proposed American medium-lift launch vehicle for space launch, designed by Hughes Aircraft and Boeing during the mid-1980s as part of the joint United States Air Force (USAF)/National Aeronautics and Space Administration (NASA) Advanced Launch System (ALS) study. Intended to utilize engines and tooling in storage from the Saturn V rocket program along with Space Shuttle components, and projected to be capable of carrying up to six satellites into multiple orbits using a single launch (e.g. GPS constellation), the proposal failed to meet the ALS requirements, and the Jarvis rocket was never built.