ISRO Project Surya: Next Generation Launch Vehicle (NGLV)

[Blademaster]

First official render of LOX-METHANE engine LME-1100
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Source: Annual Report 2024-25
Updates about NGLV & LME-1100 from Annual Report
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@Indx TechStyle time for dedicated thread for LME-1100

When will ISRO ever go on the full flow staged combustion engine route? That route, even though it involves more complexity, offers the most bang for the buck once you get down to it as proven by Elon Musk's Raptor program.

Even the Chinese programs are going for such technology. This is the pinnacle of rocket engine technology.

 

[Aaj Ka Hero]

When will ISRO ever go on the full flow staged combustion engine route? That route, even though it involves more complexity, offers the most bang for the buck once you get down to it as proven by Elon Musk's Raptor program.

Even the Chinese programs are going for such technology. This is the pinnacle of rocket engine technology.

for that India need to develop sce-200 engine first.

 

[Anants]

When will ISRO ever go on the full flow staged combustion engine route? That route, even though it involves more complexity, offers the most bang for the buck once you get down to it as proven by Elon Musk's Raptor program.

Even the Chinese programs are going for such technology. This is the pinnacle of rocket engine technology.

Blade we do have Full Stage combustion engine tech in form of CE7.5 used in GSLV MK2. For Semi Cryo - Let them complete GG based engine first. Developing Full Staged would have delayed the program even more.

 

[TopWatcher]

When NGLV going to be developed & realized ??

Everytime we lack in timing & start looking into import.

 

[fire starter]

 

[FalconSlayers]

View: https://x.com/ISROSpaceflight/status/1891782788480635324

 

[Anonymous Bharata]

NGLV-SH for crewed Lunar Landing

 

[Anonymous Bharata]

View attachment 25464

This engine is hot af ...... Only whitepill among ocean of blackpills

 

[RedPhantom]

NGLV-SH for crewed Lunar Landing

View attachment 25493

Are the dimensions in centimetres? Because that would make even the non-human rated version the second tallest rocket in history, just behind Starship. A few meters taller than China's planned LM-9 and just a few inches taller than the Saturn V.

And the Human Rated version is 7 more metres taller.

 

[Anonymous Bharata]

Are the dimensions in centimetres? Because that would make even the non-human rated version the second tallest rocket in history, just behind Starship. A few meters taller than China's planned LM-9 and just a few inches taller than the Saturn V.

And the Human Rated version is 7 more metres taller..

They are in mm

 

[RedPhantom]

They are in mm

True. But I calculated (incorrectly) taking 1m = 1000cm. So everything else I said remains true (as 1m =1000mm).

A 110.7m tall rocket would be the second tallest in history.

 

[Anonymous Bharata]

True. But I calculated (incorrectly) taking 1m = 1000cm. So everything else I said remains true (as 1m =1000mm).

A 110.7m tall rocket would be the second tallest in history.

Yep, not just that, they have to do 2 launches within 2 hours,if they decided to go with current Earth Orbit Rendezvous plan... So they have to build 4th LP as well in SHAR

 

[Blademaster]

Blade we do have Full Stage combustion engine tech in form of CE7.5 used in GSLV MK2. For Semi Cryo - Let them complete GG based engine first. Developing Full Staged would have delayed the program even more.

Well ISRO has a plan to reuse NGLV multiple times. The problem with the gas generator engine is that it leaves soot buildup and can steadily degrade the performance of the engine over time if not addressed on a regular basis and that contributes to a higher maintenance cost. Whereas by going for full stage combustion engine route, you can tackle that issue headon in the beginning and not deal with such issues. SpaceX was able to get a Raptor engine working within a decade. Surely ISRO can do the same.

 

[karn]

Well ISRO has a plan to reuse NGLV multiple times. The problem with the gas generator engine is that it leaves soot buildup and can steadily degrade the performance of the engine over time if not addressed on a regular basis and that contributes to a higher maintenance cost. Whereas by going for full stage combustion engine route, you can tackle that issue headon in the beginning and not deal with such issues. SpaceX was able to get a Raptor engine working within a decade. Surely ISRO can do the same.

A gas generator design has no connection with soot build up. Also it's a methane engine soot accumulation would be minimal compared to kerosene.

 

[Anants]

Well ISRO has a plan to reuse NGLV multiple times. The problem with the gas generator engine is that it leaves soot buildup and can steadily degrade the performance of the engine over time if not addressed on a regular basis and that contributes to a higher maintenance cost. Whereas by going for full stage combustion engine route, you can tackle that issue headon in the beginning and not deal with such issues. SpaceX was able to get a Raptor engine working within a decade. Surely ISRO can do the same.

Blade Its better they Go via GG route. Timelines shall be relatively shortened. They have clear goals to achieve including manned mission to moon. Who knows someone in private develops staged combustion based Methalox engine parallelly?

 

[pipebomb]

Maybe this has been asked before but why is ISRO purposely avoiding a two stage partially reusable launch vehicle ?

F9 lands 300km down range in sea, whereas distance between Sriharikota to Malaysia is 2000km approx. ISRO can easily re-enter upper stage above Philippine sea or beyond ?

This doesn't make sense. What am I missing here ?

 

[Anonymous Bharata]

Maybe this has been asked before but why is ISRO purposely avoiding a two stage partially reusable launch vehicle ?

F9 lands 300km down range in sea, whereas distance between Sriharikota to Malaysia is 2000km approx. ISRO can easily re-enter upper stage above Philippine sea or beyond ?

This doesn't make sense. What am I missing here ?View attachment 36462

2 stage vehicle with 10T to GTO payload using LOX Methane is very difficult even with advanced materials...u need insane structural factors, almost impossible to achieve, hence 3 stage

 

[pipebomb]

2 stage vehicle with 10T to GTO payload using LOX Methane is very difficult even with advanced materials...u need insane structural factors, almost impossible to achieve, hence 3 stage

No! A two stage vehicle is simpler, LESS RISKER & CHEAPER. The last two are exactly what ISRO needs to up it's launch cadence. No one builds 3 stage rockets anymore

I am failing to see why ISRO is not building a two stage launch vehicle

 

[Anonymous Bharata]

No! A two stage vehicle is simpler, LESS RISKER & CHEAPER. The last two are exactly what ISRO needs to up it's launch cadence. No one builds 3 stage rockets anymore

I am failing to see why ISRO is not building a two stage launch vehicle

I have just explained you in my above post why two stage to orbit is not technically feasible for 10T GTO payload requirement, read again. You have to break laws of Physics to achieve that, even NASA or SpaceX cannot achieve that

 

[pipebomb]

I have just explained you in my above post why two stage to orbit is not technically feasible for 10T GTO payload requirement, read again. You have to break laws of Physics to achieve that, even NASA or SpaceX cannot achieve that

Wait a minute ! Who said we have to use methlox in upper stage ? Because I surely didn't !

My only question is why we don't build a 2 stage LV with reusable 1st stage. THAT'S IT

New glenn - 13.6 t to GTO

And BTW a 4-6t to GTO & 10-16t to LEO would suffice our 99% of needs