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Agnit II ATArun S Viswakarma

Agni-IIAT.

Length (m)20Max Diameter (m)1.2

Launch Weight - kg (Including Payload)2 7,000PropellantSolid (HTPB/AP/AI)Number of Stages2.5Payload - kg 300 - 1,000Range (Payload)4,000 km (1,500 kg)CEP Accuracy20 meters (estimated)

INTRODUCTION: AGNI-IIAT

The Agni-II was a quick and proven design, albeit of1980s vintage. The Agni-IIAT is theresult of a CIP (Continuous Improvement Program) with Agni-II. Different reports indicate

India developing a more advanced technology (AT) version ofAgni-II[82] putting into use,state-of-the-art technologies to significantly improve the Agni-II performance[83]as well as to

adapt it to the newer andlighter nuclear payload, that was proven by the Pokharan-II seriesof nuclear tests[84]. The new propulsion system could greatly increase the missile's range to4000 km (1500 kg payload) and potentially to ICBM range for lighter payload.

The Agni-IIAT is likely toincorporate the following changes:

y A larger diameter booster stage made of stronger 250-Marging steel, improving fuelloading andfuel mass-fraction (~0.88).

y Lightweight carbon composite motor casing[85, 86]for the second stage, insteadof steelcasing, improving its mass-fraction (~0.92).

y Lighter, tougher and higher (beta) RV, with allcarbon composite re-entry heat-shield, multidirectionalcarbon re-entry nose tip andcontrol surfaces[87]. Very likely aunary version of the Agni-III's RV Mk-4.

We refer to this postulatedconfiguration as Agni-IIAT that wouldbe validated when it is

tested sometime in the future[88]. However this paper gives an insight to potency of such

technologicalimprovement.

Comparative Line drawing of Agni-II and Agni-IIAT

[Image Arun Vishwakarma]

New improved 1.2m diameter rocket case of maraging steel being handed over to

M. Natarajan

[Source: The HINDU, 10-Nov-06]

Composite casing of Agni-II's second stage

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[Image : Advanced Systems Laboratory, Hyderabad]

Description

After Agni-II development DRDO has reported major success in developing superior sub-

systems ranging

from newer h

igher per

forman

ce RV,

lighter

cas

ing

ofse

cond

stage and

booster case made of stronger Maraging steel. The new missile's form factor is almost same

as the Agni-II, but qualitative improvements in propulsion and warhead significantly

improves its range and effectiveness.

Accuracy of this longer range missile is augmentedby space based precision navigation

system. India and Russia are working together on the development andlaunch of a new

generation ofGlobal Navigation Satellite System (GLONESS) that willbe operationalby

2007[89]. India is alsobuilding its own IRNSS (Indian Regional Navigation Satellite System)[90]

covering 35%of earth surface, centered around India for assured access to space based

precision navigation.

Manoeuvring Re-Entry Vehicle:

New lighter and tougher RV, with allcarbon composite re-entry heat shield with multi

directionalcarbon re-entry nose tip andcontrol surfaces, the new lightweight composites

can withstand temperatures ofup to6,000 centigrade, thus capable of greater re-entry

velocity[91, 92]. The new RV smaller in diameter &length but higher (beta) compared to the

RV ofAgni-I/II, similar to RV-MK4ofAgni-III & Agni-III++.

Propulsion

First Stage: A new 1.2 meter diameter[92.A]booster case made of250-Maraging steel with

improvedchamber pressure andfuel mass-fraction (estimated 0.88). Approximately 12

meter long and 20 tonne mass

Second Stage: Lightweight filament woundcarbon composite motor casing[93, 94]for Stage-II

with improvedfuel mass-fraction (estimatedbetween 0.90 - 0.92[95]).

Agni-IIATConfiguration

Agni-IIAT Stage 1_____Agni-IIAT Stage 2_____PBV/HAM_____RV

Gross Mass ____ 20,000 kg ____ 6,000 kg____ 220 kg ____ 50 kg

Fuel Mass ____ 17,600 kg____ 5,400 kg ____ 40 - 180 kg

Empty Mass____ 2,400 kg ____ 600 kg ____ 20 - 50 kg

Fuel-Mass-Ratio[96]____ 0.88 ____ 0.90 ____ 0.82

Thrust @ Vacuum ____ 78,600 Kgf____ 42,580 Kgf

Thrust @ Sea Level____ 70,400 Kgf --

(Burn Time)____ (58 seconds)____ (35 seconds)

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