Editing RL10 (section)

=== Cancelled ===
* OmegA Upper Stage: In April 2018, [[Northrop Grumman Innovation Systems]] announced that two RL10C-5-1 engines would be used on [[Omega (rocket)|OmegA]] in the upper stage.<ref>{{Cite web |date=April 16, 2018 |title=RL-10 Selected for OmegA Rocket |url=http://www.rocket.com/article/rl10-selected-omega%E2%84%A2-rocket |access-date=May 14, 2018 |publisher=Aerojet Rocketdyne}}</ref>  [[Blue Origin]]'s [[BE-3U]] and [[Airbus]] Safran's [[Vinci (rocket engine)|Vinci]] were also considered before Aerojet Rocketdyne's engine was selected.  OmegA development was halted after it failed to win a National Security Space Launch contract.<ref name="SpaceNews 2020">{{Cite web |date=2020-09-09 |title=Northrop Grumman to terminate OmegA rocket program |url=https://dev.spacenews.com/northrop-grumman-to-terminate-omega-rocket-program/ |access-date=2020-11-23 |website=SpaceNews |language=en-US}}</ref>
* [[Advanced Cryogenic Evolved Stage]]: {{as of|2009}}, an enhanced version of the RL10 was proposed to power the Advanced Cryogenic Evolved Stage (ACES), a long-duration, low-boiloff extension of existing [[United Launch Alliance|ULA]] [[Centaur (rocket stage)|Centaur]] and [[Delta Cryogenic Second Stage]] (DCSS) technology for the [[Vulcan (rocket)|Vulcan]] launch vehicle.<ref name="aiaa20096566">{{Cite journal |last1=Kutter |first1=Bernard F. |last2=Zegler |first2=Frank |last3=Barr |first3=Jon |last4=Bulk |first4=Tim |last5=Pitchford |first5=Brian |date=2009 |title=Robust Lunar Exploration Using an Efficient Lunar Lander Derived from Existing Upper Stages |url=https://info.aiaa.org/tac/SMG/STTC/White%20Papers/DualThrustAxisLander(DTAL)2009.pdf |url-status=dead |journal=AIAA |archive-url=https://web.archive.org/web/20110724230154/https://info.aiaa.org/tac/SMG/STTC/White%20Papers/DualThrustAxisLander%28DTAL%292009.pdf |archive-date=July 24, 2011 |access-date=March 9, 2011 |ref=AIAA 2009–6566}}</ref>  Long-duration ACES technology is intended to support [[geosynchronous]], [[cislunar]], and [[interplanetary mission|interplanetary]] missions. Another possible application is as in-space [[propellant depot]]s in [[low Earth orbit|LEO]] or at {{L2}} that could be used as way-stations for other rockets to stop and refuel on the way to beyond-LEO or interplanetary missions. Cleanup of [[space debris]] was also proposed.<ref name="aiaa20100902">{{Cite web |last1=Zegler |first1=Frank |last2=Bernard Kutter |date=September 2, 2010 |title=Evolving to a Depot-Based Space Transportation Architecture |url=http://www.ulalaunch.com/site/docs/publications/DepotBasedTransportationArchitecture2010.pdf |url-status=dead |archive-url=https://web.archive.org/web/20111020010301/http://www.ulalaunch.com/site/docs/publications/DepotBasedTransportationArchitecture2010.pdf |archive-date=October 20, 2011 |access-date=January 25, 2011 |website=AIAA SPACE 2010 Conference & Exposition |publisher=AIAA |quote=''ACES design conceptualization has been underway at ULA for many years. It leverages design features of both the Centaur and Delta Cryogenic Second Stage (DCSS) upper stages and intends to supplement and perhaps replace these stages in the future. ...'' |df=mdy-all}}</ref>