Copy and paste link to a browser while using a large screen. There is too much going on here to view it on a phone.

Here’s a widget to help visualize propellant transfer while rotating. claude.ai/artifact/CDDZZmqNB…

The internal atmosphere of Sputnik 1 was N2 gas at 1.3 atmospheres. There was a fan installed, which can be seen when you toggle 'Internals' on the panel. It cycled on and off at 30 °C and 20 °C respectively. It primarily ran when the satellite was in sunlight and turned itself off when Sputnik was in shadow.

Sputnik 1 was launched to LEO 69 years ago today. claude.ai/artifact/W1KZRAt4d… @elonmusk @larsblackmore @NASAAdmin @MarcusHouse @InfographicTony @LunarCaveman @DJSnM @mcrs987 @CrainTim @Erdayastronaut

Synthetic Intelligence.

Here are newest screenshots from my video, showing a viable (maybe the only viable) on-orbit refueling idea for a @SpaceX Starship or HLS. The video works best on a large screen. Let me know what you think about it. claude.ai/artifact/XjNotnzNa… @elonmusk @larsblackmore @NASAAdmin @MarcusHouse @InfographicTony @LunarCaveman @mcrs987 @DJSnM @CrainTim @Erdayastronaut

This is like eating potato chips. You can’t stop. I modified the HLS landing gear. The pads are 1.5m in diameter now. The pad circle diameter is 27m. The ground clearance to the bottom of the skirt is 3m. I used Ti-6Al-4V for the pad ball joints, struts, pistons, and braces. The pads themselves are Al-Li 2195. Claude had defaulted to a high inclination near polar orbit. I changed that to a 28.5° inclination orbit. I deleted the white circular light and I added three flashing amber lights on the docking ring to alert approaching spacecraft that fuel transfer was occurring. I modified the solar array deployment on HLS to minimize drag during ascent. I also changed the rear view of the TLI burn to show the true blue/violet color of LCH4 and LOX combustion in a vacuum. Iterations are ongoing. @elonmusk @larsblackmore @rookisaacman @CrainTim @LunarCaveman @InfographicTony @mcrs987 claude.ai/artifact/XjNotnzNa…

The actual cargo mass to lunar surface is less than 100t (depending on Δv margin selected) when using a 1500t propellant load. Assuming 100t dry mass, an Isp of 375s (average of sea level and vacuum R3 engines): Δv margin Max cargo to surface 0% ≈ 98 t 5% ≈ 58 t 10% ≈ 22 t

To see the second half of the animation, you have to press blue button marked Start Transfer after it lights up.

I made an animation using Claude this morning. It is much better at responding to instructions than any of the other chatbots I have tried. @elonmusk @larsblackmore @NASAAdmin @CrainTim @LunarCaveman @InfographicTony @mcrs987 claude.ai/artifact/XjNotnzNa…

Impressive.

"Synthetic Intelligence" (SI)

Here’s a money shot for all the CAD guys. @mcrs987 @InfographicTony

Check all of the closest stars first!

Good for accurate forensics!

In addition to requiring internal baffles and active thrusters to minimize sloshing during spin-up on both the fuel depot and the HLS, tuning masses will also be needed on the depot to slide rearward as propellants are transferred into the HLS. The tuning masses will keep the spin axis from shifting into the HLS, greatly simplifying attitude control for the coupled pair.

The upcoming Flight 14 (B21/S41) still has the four docking drogues on the Starship that @SpaceX has been saying would be used to transfer cryogenic propellant while on orbit. I did notice that they are missing on the next two Starships. Neither S42 nor S43 has the four docking drogues on the leeward side we are used to seeing. What gives? Is the on-orbit fuel transfer system undergoing a major redesign? I suspect it is. Again, the most promising configuration from a purely physics and engineering point of view, IMO, is a nose-to-nose coupling.

This configuration is not going to work. The depot and HLS lander will have to be mated nose to nose and rotate end over end (cartwheel) during fuel transfer. It is the only way to prevent gas and liquid phases of the propellants from mixing together and destroying the pumps. While cartwheeling in LEO, the gas will move to the center of rotation (top of tanks) and the liquid will move to the bottom of the tanks, where it belongs. The nose to nose configuration also will save RCS and ullage gas mass. The only added mass I see is additional transfer lines. We were supposed to have proof of concept by now. @SpaceX is way behind schedule proving on-orbit cryogenic fuel transfer is viable.

Get U.S. to lunar water ahead of China!