This is a tricky one given that I believe said helium pressurization was added to the CH4 header tank to mitigate what happened with SN8. That's why it's a test program, of course.https://twitter.com/elonmusk/status/1369379914139451406 …
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Replying to @NASASpaceflight
Fair point. If autogenous pressurization had been used, CH4 bubbles would most likely have reverted to liquid. Helium in header was used to prevent ullage collapse from slosh, which happened in prior flight. My fault for approving. Sounded good at the time.
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Replying to @elonmusk @NASASpaceflight
Are there baffles in future designs to prevent slosh?
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Replying to @Erdayastronaut @NASASpaceflight
There were baffles, but one may have acted like a straw to suck bubbles in from above liquid/gas level. Something similar happened on an early Falcon 1 flight, resulting in unexpectedly high liquid oxygen residuals at main engine cutoff.
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Has the SpaceX team concluded with a better landing leg design for Starship?
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Might just catch the ship with the launch tower, same as booster
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Starship’s belly flop terminal velocity is already only like 75 m/s... what if... remove the 30 tones of landing prop, add 10 more tones of flaps, get that down to like 50 m/s and just use the world’s largest and most ridiculous net?

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Yeah, we talked about that internally. Could just have it land on a big net or bouncy castle. Lacks dignity, but would work. But, optimized landing propellant is only ~5% of dry mass, so it’s not a gamechanger.
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(wondering) how it compared to payload to orbit so i did some calcs, starship payload to orbit 100+t, starship 1200t, superheavy 3400t propellant dry weight (i’m guessing a great 20 mass ratio -> 230t? 5% of that is 11.5t, so maybe 10% of payload, maybe dignity is worth it
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Replying to @DanielleFong @elonmusk and
Why not just float up a small rocket attached to a helium balloon ?
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