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So with the stage change, will they call it LVM-4 or LVM-3 Mark 2?

Oh. I thought TLP was the old plan to have third one at SDSC for Manned Missions. Thought they'd call the Tamil Nadu launch pad as FLP of that new spaceport. Isn't that how it is in other countries with multiple spaceports?

25 ton was the propellant loading right? I was talking about the engine. Not the stage.

Wasn't TLP ditched and Gaganyaan to happen from SLP only? Did they change the plan. We have two cryogenic engines designed and developed in India: CE-20 and CE-7.5:- In this launch, LVM-3/GSLV Mk-III upper stage is cryogenic powered by CE-20 cryogenic engine with 20 ton-force of thrust and gas...

Well, what can I say? @Indx TechStyle paaji and I are soulmates. We are always on the same wavelength.

No idea then. Maybe some other mod accidentally did this.

Dunno. I do remember posting those slides after looking at this post and then thinking it would be a shame if the tweet got deleted so I should post the images directly in DFI. I mean I positively remember making that post. Maybe you posted the same slides in another thread?

Didn't catch your meaning there. Owner of the video?

Always post the images so that even if tweet gets deleted, record remains:- (None of this is an official plan, just something being discussed as a possibility)

I was talking about reusability and if SpaceX approach to it is the right one or if its all marketing bluster. And while I agree with your larger point, optimizing LVs to lower launch costs is in the larger interests of ISRO and its mission of leveraging space tech for nation building.

Agreed that we shouldn't blindly follow them, but SpaceX has managed to bring launch costs down to below ISRO's launch costs while hiring only Americans. That is the proof of the pudding. And if Starship Superheavy stack can achieve even half of what they aim to do with it, it will be rather...

SCE-200 and Merlin have similar enough specific impulse. As for deep throttling, yes it won't go down to 40% but SCE-200 can throttle down to 60%. Rest, clustering should take care of it. And ISRO did say they are designing it with reusability upgrades in mind. No matter, even if SCE-200 isn't...

Good to see PS4 being used for our more practical ASAT capability development: co-orbital killer sats. (although they have announced this before as well) But I seriously hope they aren't going to go for Methalox based Reusable HLV from the get go. Given how long we will have to wait for a...

Streamlined Industrial ecosystem and the ability to shrug off failures. That and larger budgets. At least for PSLV, this is happening in India as well. The thing about PSLV is recently Godrej made some statement about how a recent decision of GoI will pave the way for higher PSLV launch...

When Modi announced that the real deal will happen by 2022, I was skeptical yet hopeful. But when covid happened, I thought it won't happen till 2025. And now it looks like it will happen in 2026. . Meanwhile, Space Station, MOM-2, SCE-200, HLV all getting delayed similarly I guess? The only...

Like I said, it would be a brachistochrone trajectory meaning your spacecraft would be thrusting the ENTIRE duration of the journey. You are accelerating towards your destination for the first half of the journey, then you cut thrust, flip your spaceship around and start decelerating towards...

Dude, they did the mission planning already. Its not for traveling up and down a gravity well, so its sufficient. 4 months travel time to Mars is also doable. MN range thrust!? At 2000 sec ISP? That feels like torchdrive level performance. But the radioactive fuel is still scary.....

Ofcourse a high thrust, high isp engine is the best. And there is usually always the trade off that the high isp thrusters (like ion thrusters) have abysmally low thrust and chemical rockets have high thrust but low isp. And that is what fusion drives are eventually meant to overcome. Ofcourse...

https://www.osti.gov/servlets/purl/1182281 ^ But this study here has a configuration with 6 engines, each producing 11.5 MW which would be almost 700N thrust. Also, why would you need 100kN range thruster? These rockets won't be going up and down the gravity well all that often. That will still...

That still looks like a NASA diagram was used, even if paper is by ISRO people. It just talks about the kind of mission architecture would be needed for a Manned Mars Expedition. Link to the paper: http://cosmology.com/Mars128.html Fission on a rocket is a scary prospect. If you take a...