 | This article includes a list of general references, but it lacks sufficient corresponding inline citations. (June 2012) |
 M-1 rocket engine specifications | |
| Country of origin | United States |
|---|---|
| First flight | Development abandoned at pre-prototype stage |
| Manufacturer | Aerojet |
| Status | Abandoned in development stage |
| Liquid-fuel engine | |
| Propellant | LOX / liquid hydrogen |
| Cycle | Gas-generator cycle |
| Performance | |
| Thrust, vacuum | 1,500,000 lbf (6.67 MN) |
| Thrust-to-weight ratio | 60 |
| Chamber pressure | 1,000 psia |
| Specific impulse, vacuum | 428 seconds (4.20 km/s) |
| Dimensions | |
| Length | 7.72 m |
| Diameter | 4.28 m |
| Dry mass | 9068 kg |
The Aerojet M-1 was one of the largest and most powerful liquid-hydrogen-fueled liquid-fuel rocket engines to be designed and component-tested. It was originally developed during the 1950s by the US Air Force. The M-1 offered a baseline thrust of 6.67 MN (1.5 million lbf) and an immediate growth target of 8 MN (1.8 million lbf). If built, the M-1 would have been larger and more efficient than the famed F-1 that powered the first stage of the Saturn V rocket to the Moon.