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See the second image, they assembled it at SVAB, it's the first launch campaign at SVAB... it's looks like they are assembling GSLV-F12 at VAB

NET 2035

I never said it will be earlier than 2026, what I said is Not earlier than 2026 i.e only after 2026.....& I know G1 flight won't happen this year, it will happen only in 2024, ISRO chief hinted that earlier this year itself

yep

SC-160 =1 engine SC-400= 4 or 5 engines

@Indx TechStyle @Swesh Also note that Semi-cryo test facility can only test upto SC-160 stage, it cannot be used for Clustered SCE-200 & SC-400, for that an entire new test facility is required. It seems our folks at ISRO never learns from the past .....they are repeating the same mistake...

My mistake, LVM3-SC would be no earlier than 2026

@Indx TechStyle @Swesh as per the reddit user u/Galacticnemesis 1st SCE-200's Pressure Head Test Article (PHTA) is actually ready now, it's waiting for Test stand to be ready, which will take atleast 3-4 months, So we can expect 1st static test in 2nd half of 2023 It will be followed by...

Actual plan was to host Pratush Tech Demo payload on Propulsion Module, but it was cancelled later. Current status is unknown.

@Swesh

Falcon-9 fairing catching

whats your id in reddit

LVM3 with C-32 can directly inject CY-3 into Lunar Transfer Trajectory

Still as per below estimates LVM3-SC can inject atleast 3.5 tons directly in Lunar Transfer Orbit These are estimates below LVM3-SC specs below Payload to 170 × 36000 GTO Payload to 500 × 400000 Lunar Transfer Orbit

@Indx TechStyle @Swesh current LVM3 itself can put Vikram Lander + Pragyan Rover (together 1500KG) directly into Lunar Transfer Orbit

These are estimates below LVM3-SC specs below Payload to 170 × 36000 GTO Payload to 500 × 400000 Lunar Transfer Orbit

LM-3B/E has same 5.5T to GTO & 4T to LTT, so based on that we can guess it

no need for new upper stage, LVM3-SC can directly put 4 ton class payload in Lunar transfer trajectory

Dr. Somnath's presentation

Yes it's needed....let me explain why.... As Apogee of the orbit increases payload decreases... For eg: LEO: 170 × 400km, 8tons (Gaganyaan): PO: 170 × 45000Km, 3.85 tons (CY-2) PO: 170 × 186000Km,less than 3t (CY-3) GTO: 170 × 36000Km, 4.3 tons As seen above as Apogee increases payload...