Rocketdyne F-1

F-1
F-1 engine on display at Kennedy Space Center
Country of originUnited States
First flightNovember 9, 1967 (1967-11-09) (Apollo 4)
Last flightMay 14, 1973 (1973-05-14) (Skylab 1)
DesignerRocketdyne
ManufacturerRocketdyne
Associated LVSaturn V, Saturn C-3, Saturn C-4, Saturn C-8
Liquid-fuel engine
PropellantLOX / RP-1
Mixture ratio2.27:1
(69% LOX, 31% RP-1)
CycleGas-generator
Performance
Thrust, vacuum7,770 kN (1,746,000 lbf)
Thrust, sea-level6,770 kN (1,522,000 lbf)
Thrust-to-weight ratio94.1:1
Chamber pressure70 bar (1,015 psi; 7 MPa)
Specific impulse, vacuum304 s (2.98 km/s)
Specific impulse, sea-level263 s (2.58 km/s)
Mass flow
  • LOX: 1,789 kg/s (3,945 lb/s)
  • RP-1: 788 kg/s (1,738 lb/s)
Burn time150 to 163 seconds
Dimensions
Length5.6 m (18.5 ft)
Diameter3.7 m (12.2 ft)
Dry mass8,400 kg (18,500 lb)
Used in
S-IC

The F-1 is a rocket engine developed by Rocketdyne. The engine uses a gas-generator cycle developed in the United States in the late 1950s and was used in the Saturn V rocket in the 1960s and early 1970s. Five F-1 engines were used in the S-IC first stage of each Saturn V, which served as the main launch vehicle of the Apollo program. The F-1 remains the most powerful single combustion chamber liquid-propellant rocket engine ever developed.[1]

  1. ^ W. David Woods, How Apollo Flew to the Moon, Springer, 2008, ISBN 978-0-387-71675-6, p. 19