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

Diameter: 85 inch (2,146 millimeter)
Length: 87 inch (2,197 millimeter)
Burn Time: 466 second (7.76 minute)
Dry Weight: 664 pound (0.30 ton)
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)

RL10 News

There is 1 news
on 12 Dec 2019
Thursday, December 12, 2019Northrop Grumman Signs Customer for First Flight of OmegA

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