India's Future Main Battle Tank (FMBT)

[Zarvan]

yet they can't produce even usable tank ammunition.

I have tagged you on many threads and posts visit them and answer them

 

[IND151]

50 ton missile with 900km range ......which one was that ??

Agni TD

Agni-TD

The original Agni-TD was an amalgam of the Prithvi-I and the SLV-3 booster. The Agni-TD is a two-stage missile with the first stage using the first-stage solid-fuel booster motor of the SLV-3 satellite launch vehicle. This marked the first time that India had used directly a component of its civilian space research program for military purposes. The Agni-TD was a cheap test vehicle to prove re-entry and guidance technology for use on a more advanced platform. The missile used a solid booster that was improved but similar to S-1 stage. Instead of developing a new solid motor for the second stage, which would have involved significant delays, it used a shortened version of the liquid fuelled Prithvi-I motor.

The first Agni launch on 22 May 1989 used a shortened Prithvi-I stage as the second stage. The second Agni test used a second stage with more fuel and longer burn that was ignited before separation thus obviating the need of six-ullage motors used in the earlier launch. The RV used multi-directionally reinforced carbon-fiber preform (MRCP) technology. The last test of the basic Agni-TD on 19 February 1994 was a major technical breakthrough.

First Stage: The booster motor is one meter in diameter and ten meters in length. It has approximately 9 tons solid propellant. The stage features three segments of propellant grain, with an internal star configuration for increased thrust during the initial boost phase. The motor case is made of a high-strength 15CDV6 steel and is fabricated by conventional rolling and welding techniques. The propellant used in Agni-TD consists of the AP-Al-PBAN composite propellant. All later Agni variants use HTPB (hydroxyl-terminated polybutadiene). The propellant is of star configuration with a loading density of 78%. It is case bonded with a liner system between propellant and insulation. The motor's nozzle is built from 15CDV6 steel; a carbon-phenolic thermal protection system is used for the convergent throat, high-density graphite is used for the throat, and carbon and silica-phenolic lining is used in the fore end and aft end of the divergent.
Second Stage: Agni-TD used a Prithvi-I as its second stage, which has two small engines. The initial test flight used a Prithvi-I with lesser fuel of TG-02/AK-20 (Xylidiene + Triethylamine/IRFNA+ NTO), later flights used full fuel configuration. The case material of the second stage is aluminium alloy.

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[kurup]

Agni TD

Agni-TD

The original Agni-TD was an amalgam of the Prithvi-I and the SLV-3 booster. The Agni-TD is a two-stage missile with the first stage using the first-stage solid-fuel booster motor of the SLV-3 satellite launch vehicle. This marked the first time that India had used directly a component of its civilian space research program for military purposes. The Agni-TD was a cheap test vehicle to prove re-entry and guidance technology for use on a more advanced platform. The missile used a solid booster that was improved but similar to S-1 stage. Instead of developing a new solid motor for the second stage, which would have involved significant delays, it used a shortened version of the liquid fuelled Prithvi-I motor.

The first Agni launch on 22 May 1989 used a shortened Prithvi-I stage as the second stage. The second Agni test used a second stage with more fuel and longer burn that was ignited before separation thus obviating the need of six-ullage motors used in the earlier launch. The RV used multi-directionally reinforced carbon-fiber preform (MRCP) technology. The last test of the basic Agni-TD on 19 February 1994 was a major technical breakthrough.

First Stage: The booster motor is one meter in diameter and ten meters in length. It has approximately 9 tons solid propellant. The stage features three segments of propellant grain, with an internal star configuration for increased thrust during the initial boost phase. The motor case is made of a high-strength 15CDV6 steel and is fabricated by conventional rolling and welding techniques. The propellant used in Agni-TD consists of the AP-Al-PBAN composite propellant. All later Agni variants use HTPB (hydroxyl-terminated polybutadiene). The propellant is of star configuration with a loading density of 78%. It is case bonded with a liner system between propellant and insulation. The motor's nozzle is built from 15CDV6 steel; a carbon-phenolic thermal protection system is used for the convergent throat, high-density graphite is used for the throat, and carbon and silica-phenolic lining is used in the fore end and aft end of the divergent.
Second Stage: Agni-TD used a Prithvi-I as its second stage, which has two small engines. The initial test flight used a Prithvi-I with lesser fuel of TG-02/AK-20 (Xylidiene + Triethylamine/IRFNA+ NTO), later flights used full fuel configuration. The case material of the second stage is aluminium alloy.

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Thanks for the information ...... it was a nice informative article .

But even according to the link you provided , Agni TD weighed 16 Tons not 50 Tons .

 

[IND151]

Thanks for the information ...... it was a nice informative article .

But even according to the link you provided , Agni TD weighed 16 Tons not 50 Tons .

Yes right I was reffering to old source which said its weight is 50 tons.

But look now, Agni TD with 16 tons had range of 900 to 1100 KM.

Agni 4 with 17 tons weight has range of 4000 KM