Also known as Rocketdyne F-1, Rocketdyne F1
rocket engine by Rocketdyne
Key facts
- Country of origin
- United States
- First flight
- November 9, 1967 ( 1967-11-09 ) ( Apollo 4 )
- Last flight
- May 14, 1973 ( 1973-05-14 ) ( Skylab 1 )
- Designer
- Rocketdyne
- Manufacturer
- Rocketdyne
- Associated launch vehicle span lv
- Saturn V , Saturn C-3 , Saturn C-4 , Saturn C-8
- Propellant
- LOX / RP-1
- Mixture ratio
- 2.27:1, (69% LOX, 31% RP-1)
- Cycle
- Gas-generator
- Thrust vacuum
- 7,770 kN (1,746,000 lbf)
- Thrust sea level
- 6,770 kN (1,522,000 lbf)
- Thrust to weight ratio
- 94.1:1
- Chamber pressure
- 70 bar (1,015 psi; 7 MPa)
- Specific impulse vacuum
- 304 s (2.98 km/s)
- Specific impulse sea level
- 263 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 time
- 150 to 163 seconds
- Length
- 5.6 m (18.5 ft)
via Wikipedia infobox
~20 min read
Encyclopedic overview
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.
History
Excerpted from Wikipedia’s “F-1” article, available under the CC BY-SA 4.0 licence.