Agni & Prithvi Ballistic Missiles : News & Discussions
- Thread starter Sathya
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The thing has gumball on the top. Has fuel lines , or what looks like fuel lines.
Its very robust heavy metal construction.
My guess is it's a rocket motor with thrust vectoring.
In the program with Pallav Bagla the other day, Dr Saraswat interestingly mentioned Prithvi as strategic weapon, nuke weapon. It was interesting, maybe they do have this role in mind, a tactical nuke.
Prithvi is now old and on verge of retirement. We didn't move past Prithvi 3 aka Dhanush. Angi is the cornerstone and land based leg of our strategic strike capability.
I'm curious whether the PDV which is a direct descendent of the Prithvi could have a secondary S2S role. The USN is doing the same with the SM-3 and PDV is a land-based missile.
Yes true, but army also refurbed the old stock first to Prithvi 2 version, then with the solid fuel version. Now they take out one to test the bmd missiles regularly. So obviously a large stock is available. Navy has retired Dhanush but do not know whether they handed over to land forces or still keeps short stock as makeshift use. They had in 3 digits alone.
PDV is a PGAD project P-394. This is now TOT handed over to 1 pvt partner for large production volume. Most likely it will stay in bmd role only. PDV itself has many improved mk2 components like the roll thrusters, DACS mk2 etc (that we know about). Since this is solid composite propellant rocket , to deploy the bmd across the major metros there is already large need of the motors. Hence unlikely to be part of land attack arsenal unless all other stocks are exhausted.
Could do with a new thread for the Big V when it finally comes online maybe
What a journey it has been for the Prithvi prog though. It has come full circle. Started off as an evolution of Soviet SA-2 SAM, morphed into a surface-ship based AShBM/land attack BM (probably the first of it's kind) and now preparing for a second innings in a BMD role.
VEDA cfrp shells are under NDE test phase currently. Possibly more ground test or maybe they will finally go ahead.
We could have used old stocks of prithvi.
We barely got a chance , intense & aggressive hitting started on the 9th night time, on the 10th at 3:30pm or so the ceasefire issue came into the picture.
Also prithvis are prob in army arsenal now ? IAF got several modern options before considering prithvi 2 s .
A neat circle , quite useful when placed in the interstages
We probably have seen similar test specimens before ?
problem statement
now to match with Ajay Shukla's old pic even though things have moved a lot since , RIR prob meant rear interstage ring
We probably have seen similar test specimens before ?
problem statement
now to match with Ajay Shukla's old pic even though things have moved a lot since , RIR prob meant rear interstage ring
The ring gets fitted in the inner section while the whole ring held onto the canister/article possibly.
Judging from size, it is of a very special article V.
Now this is for body/airframe. if we consider the nozzle only, where the flex seal is assembled with the divergent nozzle. ie below section
sample of flex seal and throat insert
nozzle assy
Nozzle of existing system first stage is mentioned here
Interesting part, existing rockets nozzle end part before with dimesnion rather on small side. maxx at 1800mm. The upcoming one with the composite flex seal, you can pass thru a Brahmos full missile through the smaller gap near the throat assy. That should give some idea about sort of thrust it would have to withstand.
in short, imagine how phat the article would look with many petals on top, exactly like this below.
Judging from size, it is of a very special article V.
Now this is for body/airframe. if we consider the nozzle only, where the flex seal is assembled with the divergent nozzle. ie below section
sample of flex seal and throat insert
nozzle assy
Nozzle of existing system first stage is mentioned here
Interesting part, existing rockets nozzle end part before with dimesnion rather on small side. maxx at 1800mm. The upcoming one with the composite flex seal, you can pass thru a Brahmos full missile through the smaller gap near the throat assy. That should give some idea about sort of thrust it would have to withstand.
in short, imagine how phat the article would look with many petals on top, exactly like this below.
A representative image of the said instance , full brahmos can pass through the throat (no matter how much Gandalf shouts you shall not pass! ) 
Anyway, so the old first gen ognis , that is A1 A2 would have had propellant with Isp in range of 220 s sort of value. Delivered Isp was in the range of 226 s for a test rocket motor generating ~ 15 ton of thrust during ground static test of short duration (hence Dr Saraswat said fuel we use is with Isp in range of 220s to 240s , while western ones are upto 260s -270s with Nitrate ester polymeric propellant)
today with composite propellant , all the ognis with crmc stages now use composite propellant in the each stage motors. So with a metallic stage about 17m long 2 stage A4 with 1200mm first stage filled with regular htpb propellant 236s - 240s Isp can deliver payload to 4000km away , but a shorter 11 meter long A1P with crmc 1200mm both stages delivers payload to ONLY 1000-2000km away
Since the future heavy articles are to be launched from both land , submarine and surface ships ; and also compatible with both the composite solid propellant as well as NEPE based NG propellant with Isp in range of 266s - 268s now proven. Hence it is easy to imagine why the new article needed a flex nozzle of such size and how much thrust it is going to give. So together with weight loss due to composite stages and much higher quality propellant (from 226s Isp to 266s , that is increment of 20% alost) no prize for guessing why such miniaturised rocket stages and payload of > 3 ton.
Now imagine the Boomer that has to withstand pressure of launching such an article underwater.
Anyway, so the old first gen ognis , that is A1 A2 would have had propellant with Isp in range of 220 s sort of value. Delivered Isp was in the range of 226 s for a test rocket motor generating ~ 15 ton of thrust during ground static test of short duration (hence Dr Saraswat said fuel we use is with Isp in range of 220s to 240s , while western ones are upto 260s -270s with Nitrate ester polymeric propellant)
today with composite propellant , all the ognis with crmc stages now use composite propellant in the each stage motors. So with a metallic stage about 17m long 2 stage A4 with 1200mm first stage filled with regular htpb propellant 236s - 240s Isp can deliver payload to 4000km away , but a shorter 11 meter long A1P with crmc 1200mm both stages delivers payload to ONLY 1000-2000km away
Since the future heavy articles are to be launched from both land , submarine and surface ships ; and also compatible with both the composite solid propellant as well as NEPE based NG propellant with Isp in range of 266s - 268s now proven. Hence it is easy to imagine why the new article needed a flex nozzle of such size and how much thrust it is going to give. So together with weight loss due to composite stages and much higher quality propellant (from 226s Isp to 266s , that is increment of 20% alost) no prize for guessing why such miniaturised rocket stages and payload of > 3 ton.
Now imagine the Boomer that has to withstand pressure of launching such an article underwater.
