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RL10B-2

RL10B-2 is a restartable liquid-hydrogen/liquid-oxygen upper-stage engine with an extendible nozzle, used on Delta IV and the SLS interim cryogenic propulsion stage. On Artemis I, a single RL10B-2 powered ICPS through perigee-raise and translunar-injection burns. NASA identifies its Artemis I thrust as 24,750 lbf, approximately 110 kN.

RL10B-2
NASA (RL10B-2 engine nozzle extension testing, KSC-05PD-0161) · NASA official image, public-domain U.S. Government work; NASA/KSC image catalogued as KSC-05PD-0161. Credit NASA and imply no endorsement. Context: https://images.nasa.gov/details/05pd0161 · Source

Identity

Domains
spaceflight
Identity Level
variant
Kind
liquid-rocket-engine
Name
RL10B-2
Status
active

Details

Description
RL10B-2 is a restartable liquid-hydrogen/liquid-oxygen upper-stage engine with an extendible nozzle, used on Delta IV and the SLS interim cryogenic propulsion stage. On Artemis I, a single RL10B-2 powered ICPS through perigee-raise and translunar-injection burns. NASA identifies its Artemis I thrust as 24,750 lbf, approximately 110 kN.
Developers
Family
First Flight Date
2002-11-20
Manufacturers
Propellants
liquid hydrogenliquid oxygen
Rocket Specs
Restartable
Yes
Vacuum Specific Impulse
…
Vacuum Thrust
…

Links

Assets & Meta

Creation Time
July 29, 2026 at 09:03:01 UTC
Updated Time
October 29, 2026 at 13:12:19 UTC

Other

Sources