RL10  
Initial Operational Capability (IOC): 1963
Maiden Flight: 1959
Total Production: ?
Also Known As: RL10A and RL10B
Origin: United States of America
Corporations: Aerojet Rocketdyne
Parent System: RL10
Initial Operational Capability (IOC): 1963
Maiden Flight: 1959
Total Production: ?
Family Members: RL10C
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Description: The RL10 upper stage rocket motor was developed by Aerojet, now Aerojet Rocketdyne, in the 1950s to support the Atlas Centaur space launch system. The engine burns a mixture of liquid hydrogen and liquid oxygen (LOx). The first RL10 upper stage conducted its first flight in 1959 and entered service in 1963. With more than 500 engines produced so far the RL10 is currently being used by the Delta IV (RL10B-2) and Atlas V (RL10A-4-2) space launch systems. The RL10 rocket engines are expected to play a major role in the space exploration programs in the late 2010s and early 2020s.

RL10 Applications


Space Systems Atlas V Delta III Delta IV

RL10 Specifications

Dimensions
Diameter: 85 inch (2,146 millimeter)
Length: 87 inch (2,197 millimeter)
Time
Burn Time: 466 second (7.76 minute)
Weight
Dry Weight: 664 pound (301 kilogram)
Thrust: 24,750 pound (11.2 ton)
CEP: Circular Error Probable
Meters (m)   Kilometers (km)   Nautic Miles (nm)   Inch (in)   Yard (yd)   Foot (ft)   Millimeter (mm)
Pound (lb)   Kilogram (kg)   kN (KiloNewton)   Ton (t)
Meters per Second (mps)   Kilometers per Hour (kph)   Knot (kt)   Miles per Hour (mph)
Liter (l)   Galon (gl)
Year (yr)   Minutes (min)   Second (sec)
Shaft-Horse-Power (shp)

Operators & Related Equipment


OperatorsItems

Grand Total ?1
 
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