RL10A-3-3A
Retired Pratt & Whitney RL10A-3-3A cryogenic upper-stage engine variant. NASA's launch-vehicle tables list two RL10A-3-3A engines on Centaur I for Atlas I and two on Centaur II for Atlas II; the model-specific Atlas I/II boundary is retained distinctly from the later RL10A-4 Atlas IIA/IIAS variant.
Identity
- Domains
- spaceflight
- Identity Level
- variant
- Kind
- liquid-rocket-engine
- Name
- RL10A-3-3A
- Status
- retired
Details
- Description
- Retired Pratt & Whitney RL10A-3-3A cryogenic upper-stage engine variant. NASA's launch-vehicle tables list two RL10A-3-3A engines on Centaur I for Atlas I and two on Centaur II for Atlas II; the model-specific Atlas I/II boundary is retained distinctly from the later RL10A-4 Atlas IIA/IIAS variant.
- Developers
- Family
- Manufacturers
- Propellants
- liquid hydrogenliquid oxygen
- Rocket Specs
- Vacuum Thrust Kn
- 73.4
Links
Assets & Meta
- Creation Time
- July 29, 2026 at 09:02:50 UTC
- Updated Time
- August 15, 2026 at 06:20:14 UTC
Other
- Sources
- Accessed Date
- 2026-07-29
- Publisher
- NASA Technical Reports Server
- Title
- Cryogenic upper stage propulsion: RL10 and derivative engines
- Accessed Date
- 2026-07-29
- Note
- NASA's vehicle table lists RL10A-3-3A twice on Centaur I for Atlas I and twice on Centaur II for Atlas II, with 73.4 kN thrust per engine.
- Publisher
- NASA
- Title
- Aeronautics and Space Report of the President, Fiscal Year 2003
- Accessed Date
- 2026-08-14
- Note
- NASA identifies the Centaur upper stage as powered by two Pratt & Whitney liquid-hydrogen-fueled RL-10 engines, establishing the actor and cryogenic application boundary.
- Publisher
- NASA
- Title
- Rocket Systems Area - Centaur Program