As always, the devil's in the details. In particular for a stage that participates in ascent, losing thrust from an engine will likely change the disposal location of the stage.Looking at the SLS configuration with ICPS, launched to a 28.5° orbital inclination (i.e. due East), I believe the intended drop zone for the core is the middle of the Pacific Ocean, with the instantaneous impact point (IIP) trace crossing Africa and possibly Australia. Somewhat obviously when the strap-on boosters are jettisoned the IIP is still close to the Atlantic coast of the U.S., so the vehicle is being powered by the core engines as the IIP crosses those major land masses.I'm betting that if a core engine fails during a crewed launch before the IIP reaches Africa NASA will shut down the other engines, abort the mission, and recover the crew from the Atlantic. They would do this even if an abort-to-orbit were theoretically still possible on the remaining engines to protect against subsequent engine failures which might result in the core coming down in Africa.Once the IIP is over Africa they would instead press on, though whether they would then abort into the Indian Ocean is unclear. There's not much population density in Australia, and by then the IIP is moving much faster across the Earth's surface.Somebody at NASA has almost certainly done this kind of analysis already. Have they shared their results publicly yet?
I do believe the Shuttle had exactly one Abort-to-Orbit when it lost an SSME several minutes into the flight.
Quote from: Hyperion5 on 03/26/2013 04:20 amI do believe the Shuttle had exactly one Abort-to-Orbit when it lost an SSME several minutes into the flight.You're likely thinking of 51-F. Read the attached write-up from the JSC Space News Roundup. They were headed for a 49.5° inclination orbit. (Not sure why.) That makes for a markedly different IIP trace. It overflies Europe rather than Africa, and then goes south of Australia.
There's a recent paper, AAS 20-589 "Space Launch System Engine Out Capabilites" It is an analysis of engine-out possibilities specifically for the Artemis-I mission. Dated July 16, 2020https://ntrs.nasa.gov/citations/20205004525Based on a cursory reading of this paper, it looks like the earliest it can lose an engine, assuming that the LOX feedline for that engine is also lost, while still achieving orbit is about 11 seconds, otherwise it could lose an engine at T-0. The earliest it can lose an engine while still being able to pressurize for MECO is about 230 seconds. For reference, the SRBs are jettisoned at about 120 seconds. My understanding may be in error. Paper attached.