Ben W
Chess Grandmaster (Supervised)
As I said, there would be no good reason for a manned rocket launch vehicle to accelerate that fast. It would be highly wasteful to equip it to do so. 0.25 G's of acceleration for the Apollo/Saturn V at liftoff sounds about right. Playing around with the acceleration vs distance formula, I get approximately 0.32 G of acceleration for the Space Shuttle in the first 6 seconds after liftoff, which of course means ~1.32 G experienced by the Shuttle astronauts at liftoff.
It looks like the truth may be somewhere in the middle. From this graph of the Shuttle acceleration profile, it looks like it starts off around 1.5G's:
https://i.stack.imgur.com/Q7ODR.png
Gravity losses are the most extreme during the first minute of flight, so faster acceleration (all else being equal) would be better. If magical boosters existed that could accelerate BFR at 3G's off the pad for the first 15 seconds or so, that would be fantastic. (How about a vertical railgun?) For a single stack though, since the G's are limited for structural reasons (sometimes requiring throttle-down or partial engine cutoff midway), you'd quickly be carrying a lot of engine dead-weight if you lifted off accelerating anywhere near the max. And Max-Q limits the velocity through transsonic, so a 3G launch couldn't be sustained for more than that 15 seconds or so without throttling back. The lower G-forces (and thus lower stresses) at launch also decrease the probability of a pad-destroying RUD.
For Falcon Heavy, the optimal performance profile would be to fire the side boosters at 100% at launch with the center booster throttled back to ~80%, to conserve more fuel for after booster separation. But structurally, it may be safest to reverse this for the first few seconds of launch (e.g. 80% side boosters, 100% center) to decrease shear stresses in order to reduce the chance of RUD until the vehicle is safely clear of the launch site. I'm curious if SpaceX is actually planning to do this, even if just for the maiden launch.
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