@Merdog
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Just a Merdog in a sea of BRRR ...
BRRR City
Joined October 2022
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Just A Daily Dose This Beach
Of The Realest Song Reminds Me
For 30% Of The Everyday That
US Population. We Are All Alike.
TURN THAT VOLUME UP!!!
🔊 MYSPACE AUTO-PLAY JUST RESURRECTED IN 2025 🤣🖕
Jon Lajoie – Everyday Normal Guy 2 (FULL)
Turn your shit UP. The beaches aren’t ready. 🌊
#EverydayNormalGuy #FAFO
Theres a modern day, real world example of this exact zcash:native piece @johnkim77
U kan ₿ŁÐ ah’ll C-or-t’s uh-v Rails
‘N
Ᵽ-uh-t ah’ll C-or-t’s uh-v cat-pit-uh’ll en
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I mean 🤣😂🤣
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Small idea for the long-haul / mid-to-low fill zero-g phase that most public tests haven’t fully stressed yet.
Don’t fill the whole tank with anything. Just add a few small, localized porous-metal (or high-porosity alloy) sections sitting between the existing baffles — not a full foam liner.
Two jobs at once:
• Extra viscous damping + liquid “trapping” right where slosh gets ugly at mid/low fill in micro-g
• A bit of distributed thermal mass to fight stratification and help keep usable liquid near the outlets during long coasts
Header tanks + settling burns already do the heavy lifting. This would just be cheap insurance for the exact scenarios that are still lightly tested at full scale (multi-day coasts, depot ops, low residuals). Mass, cleanliness, and LOX compatibility stay manageable because the inserts stay small and modular.
The SpaceX engineering data going into Grok 4.7 is exactly the kind of corpus that could tell you whether this is worth a ground test or not.
nitter.cf/XFreeze/status/2094440…
@SpaceX 🤭🤭
βℝℝℝ 😉😉
@elonmusk an engineering question for you:
For a tanker-fed Starship architecture, what’s the highest-leverage unsolved problem in making orbital cryogenic propellant transfer work at operational scale—settling and slosh in micro-g, boil-off and tank thermal control, docking/berthing loads, transfer-line chill-down losses, and residual-propellant uncertainty—so a Mars or high-energy stack can be filled without tanker count, time on orbit, and unusable residuals eating the payload? In particular, how should the split work between ground test, a small number of on-orbit demos, and closed-loop flight data so transfer becomes a repeatable operations problem rather than a one-off experiment?
Follow-up to the localized porous-insert idea:
Instead of isolated patches between baffles, run short connecting tubes from one ring-baffle compartment to the next. Put a high-porosity metal core in the middle of each tube and add a small secondary baffle ring at both the inlet and outlet.
Completely passive — nothing moves except the LOX itself.
Two jobs at once:
• The packed core + restricted tube diameter kill slosh energy that tries to surge from one compartment to another (especially ugly at mid-to-low fill in micro-g).
• The same porous metal acts as distributed thermal mass and a short heat exchanger, so a warm slug doesn’t instantly mix into the next section.
Header tanks + settling burns still do the heavy lifting. This is just extra cheap insurance for multi-day coasts and depot ops. Mass stays low because the tubes and cores stay short and modular. Ground-testable with subscale tanks and LN2 before anyone cuts flight hardware.
@SpaceX 🤔
🤭
βℝℝℝ βℝℝℝ
😉😉
