RL10
Type: Upper Stage Engine
Country of Origin: United States
Manufacturer: Pratt & Whitney / Aerojet Rocketdyne
RL10A-1
First Flight:
Status: REtired
Propellant (O/F): Liquid Oxygen/Liquid Hydrogen
Mixture Ratio (O/F by mass):
Cycle: Gas Generator
Chambers: 1
Thrust (vac.): 67 kN
Thrust (s.l.):
Throttle: none
ISP (vac.): 425 s
ISP (s.l.):
Chamber Pressure:
Nozzle Ratio: 40:1
Burn time: 430 sec
Ignitions:
Mass: 131 kg
Length: 1.73 m
Diameter: 1.53 m
Used in:
RL10A-3
First Flight:
Status: Retired
Propellant (O/F): Liquid Oxygen/Liquid Hydrogen
Mixture Ratio (O/F by mass): 5:1
Cycle: Gas Generator
Chambers: 1
Thrust (vac.): 65.6 kN
Thrust (s.l.):
Throttle: none
ISP (vac.): 444 s
ISP (s.l.):
Chamber Pressure:
Nozzle Ratio: 57:1
Burn time: 470 sec
Ignitions:
Mass: 131 kg
Length: 2.49 m
Diameter: 1.53 m
Used in:
RL10A-4
First Flight:
Status: Retired
Propellant (O/F): Liquid Oxygen/Liquid Hydrogen
Mixture Ratio (O/F by mass): 5.5:1
Cycle: Gas Generator
Chambers: 1
Thrust (vac.): 92.5 kN
Thrust (s.l.):
Throttle: none
ISP (vac.): 449 s
ISP (s.l.):
Chamber Pressure:
Nozzle Ratio: 84:1
Burn time: 392 sec
Ignitions:
Mass: 168 kg
Length: 2.29 m
Diameter: 1.17 m
Used in:
RL10A-4-1
First Flight:
Status: Retired
Propellant (O/F): Liquid Oxygen/Liquid Hydrogen
Mixture Ratio (O/F by mass): 5.5:1
Cycle: Gas Generator
Chambers: 1
Thrust (vac.): 99.1 kN
Thrust (s.l.):
Throttle: none
ISP (vac.): 451 s
ISP (s.l.):
Chamber Pressure:
Nozzle Ratio: 84:1
Burn time: 740 sec
Ignitions:
Mass: 167 kg
Length:
Diameter: 1.53 m
Used in:
RL10A-4-2
First Flight:
Status: Active
Propellant (O/F): Liquid Oxygen/Liquid Hydrogen
Mixture Ratio (O/F by mass): 5.5:1
Cycle: Gas Generator
Chambers: 1
Thrust (vac.): 99.1 kN
Thrust (s.l.):
Throttle: none
ISP (vac.): 451 s
ISP (s.l.):
Chamber Pressure:
Nozzle Ratio: 84:1
Burn time: 740 sec
Ignitions:
Mass: 167 kg
Length:
Diameter: 1.17 m
Used in: Atlas V
RL10A-5
First Flight:
Status: Retired
Propellant (O/F): Liquid Oxygen/Liquid Hydrogen
Mixture Ratio (O/F by mass): 6:1
Cycle: Gas Generator
Chambers: 1
Thrust (vac.): 99.1 kN
Thrust (s.l.):
Throttle: none
ISP (vac.): 373 s
ISP (s.l.):
Chamber Pressure:
Nozzle Ratio: 4:1
Burn time: 127 sec
Ignitions:
Mass: 167 kg
Length: 1.07 m
Diameter: 1.02 m
Used in: DC-X
RL10B-2
First Flight:
Status: Active
Propellant (O/F): Liquid Oxygen/Liquid Hydrogen
Mixture Ratio (O/F by mass): 5.88:1
Cycle: Gas Generator
Chambers: 1
Thrust (vac.): 110 kN
Thrust (s.l.):
Throttle: none
ISP (vac.): 462 s
ISP (s.l.):
Chamber Pressure:
Nozzle Ratio: 280:1
Burn time: 700 sec
Ignitions:
Mass: 277 kg
Length: 4.14 m
Diameter: 2.13 m
Used in: Delta III, Delta IV
RL10C-1
First Flight:
Status: Active
Propellant (O/F): Liquid Oxygen/Liquid Hydrogen
Mixture Ratio (O/F by mass): 5.5:1
Cycle: Gas Generator
Chambers: 1
Thrust (vac.): 101.8 kN
Thrust (s.l.):
Throttle: none
ISP (vac.): 449.7 s
ISP (s.l.):
Chamber Pressure:
Nozzle Ratio: 130:1
Burn time: 2000 sec
Ignitions:
Mass: 190 kg
Length: 2.22 m
Diameter: 1.44 m
Used in: Atlas V
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