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?? Maybe you meant chandrayaan-2 orbiter? Upcoming missions: December 7th: PSLV C-36/RESOURCESAT-2A Later in december: Pad abort test of crew module for human space flight program January: GSLV MK-3 D-1/GSAT-19E Late January/Early feb: PSLV C-37/CARTOSAT-2D + 82 other satellites Next...

This sat is well within simorghs payload capablity so why would iran even need a foreign launcher?

PSLV C-36 launch date moved to december 7th due to some problems with rocket

According to some media channels there is planned safir launch early 2017. The payload is either sharifsat or tadbir.

LEO is anywhere between 200km to 2000km. If you want to send humans you would launch to 200-400km LEO, if you want to send earth observation satellite you would launch to 500km+ LEO for maximum imaging range. GTO from my understanding is 180 by 36000 km orbit which is used as a initial stage...

Your YF-73 engine that flew in 84 was a gas generator design. Such design is childs play compared to stage combustion cycle that ISRO's CE-7.5 uses. YF-73 specific impulse: 420 seconds CE-7.5 specific impulse: 452 seconds Look at wikipedia or ISRO's site

GSLV MK-3 non-existent? Are you aware that it has already flown in suborbital config?

It is 8 tons to 620km high circular LEO while long march five is 25 tons to 200 km by 400 km eplitical LEO. They are not the same it takes more delta v to place at 620km than it does at 200-400 km. If long march 5 launched into 620km high orbit its capablity would be somewhere between 10 - 15...

According to some tenders they are converting a old sounding rocket pad at sriharikota for pad abort tests

If launched in march this would be a 6 month turn around time. The shortest time between any two GSLV launches so far.

So it is total coincidence that specs of RD-801 and YF-100 are 99% the same? YF-100 specs Sea level thrust: 120 tons Sea level impulse: 300 seconds Fuel: LOX/RP-1 Cycle: Oxidiser rich staged combustion cycle RD-801 specs: Sea level thrust: 120 tons Sea level impulse: 300 seconds...

SCE-200 specs: Sea level thrust: 182 tons Sea level impulse: 299 seconds Dry mass: 2700 kg Fuel: LOX/RP-1 Engine cycle: Oxidiser rich staged combustion cycle Some info on semi-cryo stages in development: SC-200 - One SCE-200 engine with 200 ton propellant loading. It will serve as replacement...

What practical application is there for 14 tons to GTO? Is china planning geostatonary space station?

Is Iran still developing simorgh? Or will it violate their deal with the US?