Indian Missile News And Discussion

[Arun_S]

And this is excerpts on A2-AT from by missile page that was previously posted on BR.



Sorry I have been so busy I have not yet hosted my material somewhere else for greater public good.



Recent reports suggest 1.3 meter diameter. And I think this missile was secretly tested in early 2010, and with Ballistic Glide RV. Let us see the actual dimension when the fat lady sings tomorrow.







[left] [/left]

[left][size="2"][url="http://www.bharat-rakshak.com/MISSILES/Agni.html#INTRO:%20AGNI-IIAT"]Agni-IIAT (A-2AT)[/url] [/size][/left]

[left][size="2"]Improved A-2 variant using more advanced and lighter material. Two stage, solid fuel, road & rail mobile IRBM.[/size][/left]



[size="4"]INTRODUCTION: AGNI-IIAT[/size]



[size="2"]The Agni-II was a quick and proven design, albeit of 1980s vintage. The Agni-IIAT is the result of a CIP (Continuous Improvement Program) with Agni-II. Different reports indicate India developing a more advanced technology (AT) version of Agni-II[/size][size="1"][sup][[url="http://www.bharat-rakshak.com/MISSILES/Agni.html#82"]82[/url]][/sup][/size][size="2"] putting into use, state-of-the-art technologies to significantly improve the Agni-II performance[/size][size="1"][sup][[url="http://www.bharat-rakshak.com/MISSILES/Agni.html#83"]83[/url]][/sup] [/size][size="2"]as well as to adapt it to the newer and lighter nuclear payload, that was proven by the Pokharan-II series of nuclear tests[/size][size="1"][sup][[url="http://www.bharat-rakshak.com/MISSILES/Agni.html#84"]84[/url]][/sup][/size][size="2"]. The new propulsion system could greatly increase the missile's range to 4000 km (1500 kg payload) and potentially to ICBM range for lighter payload. [/size]



[size="2"]The Agni-IIAT is likely to incorporate the following changes:[/size]

1. [size="2"]A larger diameter booster stage made of stronger 250-Marging steel, improving fuel loading and fuel mass-fraction (~0.88).[/size]
2. [size="2"]Lightweight carbon composite motor casing[/size][size="1"][sup][[url="http://www.bharat-rakshak.com/MISSILES/Agni.html#85"]85[/url], [url="http://www.bharat-rakshak.com/MISSILES/Agni.html#86"]86[/url]][/sup][/size][size="2"] for the second stage, instead of steel casing, improving its mass-fraction (~0.92).[/size]
3. [size="2"]Lighter, tougher and higher [/size][size="2"]β[/size] [size="2"](beta) RV, with all carbon composite re-entry heat-shield, multi directional carbon re-entry nose tip and control surfaces[/size][size="1"][sup][[url="http://www.bharat-rakshak.com/MISSILES/Agni.html#87"]87[/url]][/sup][/size][size="2"]. Very likely a unary version of the Agni-III's RV Mk-4.[/size]

[size="2"]We refer to this postulated configuration as Agni-IIAT that would be validated when it is tested sometime in the future[/size][size="1"][sup][[url="http://www.bharat-rakshak.com/MISSILES/Agni.html#88"]88[/url]][/sup][/size][size="2"]. However this paper gives an insight to potency of such technological improvement. [/size]



[url="http://www.bharat-rakshak.com/MISSILES/Images/A-2_&_Agni-AT_Line_drawing_R11A.jpg"][/url]



[center][url="http://www.bharat-rakshak.com/MISSILES/Images/Agni28.jpg"][/url][/center]

[size="2"]Comparative Line drawing of Agni-II and Agni-IIAT [/size][size="1"][url="http://www.bharat-rakshak.com/MISSILES/Images/A-2_&_Agni-AT_Line_drawing_R11A.jpg"][/url][/size][size="2"] [/size]



[size="1"][Image [/size][size="1"][color="#000000"]©[/color][/size][size="1"] Arun Vishwakarma] [/size]



[size="2"]New improved 1.2m diameter rocket case of maraging steel being handed over to M. Natarajan[/size]



[size="1"][Source: The HINDU, 10-Nov-06] [/size]



[size="2"]Composite casing of Agni-II's second stage [/size][size="1"][url="http://www.bharat-rakshak.com/MISSILES/Images/Agni28.jpg"][/url][/size]



[size="1"][Image [/size][size="1"]: Advanced Systems Laboratory, Hyderabad] [/size]



[size="2"]Description[/size]



[size="2"]After Agni-II development DRDO has reported major success in developing superior sub-systems ranging from newer higher performance RV, lighter casing of second 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.[/size]



[size="2"][color="#000000"]Accuracy of this longer range missile is augmented by space based precision navigation system. India and Russia are working together on the development and launch of a new generation of Global Navigation Satellite System (GLONASS) that will be operational by 2007[/color][/size][size="1"][sup][[url="http://www.bharat-rakshak.com/MISSILES/Agni.html#89"]89[/url]][/sup][/size][size="2"][color="#000000"]. India is also building its own IRNSS ([/color][/size][size="2"]Indian Regional Navigation Satellite System[/size][size="1"])[/size][size="1"][color="#000000"][sup][[url="http://www.bharat-rakshak.com/MISSILES/Agni.html#90"]90[/url]][/sup][/color][/size][size="2"][color="#000000"] covering 35% of earth surface, centered around India for assured access to space based precision navigation[/color][/size][size="2"].[/size]



[size="2"]Manoeuvring Re-Entry Vehicle: [/size]



[size="2"]New lighter and tougher RV, with all carbon composite re-entry heat shield with multi directional carbon re-entry nose tip and control surfaces, the new lightweight composites can withstand temperatures of up to 6,000º centigrade, thus capable of greater re-entry velocity[/size][size="1"][sup][[url="http://www.bharat-rakshak.com/MISSILES/Agni.html#91"]91[/url], [url="http://www.bharat-rakshak.com/MISSILES/Agni.html#92"]92[/url]][/sup][/size][size="2"]. The new RV smaller in diameter & length but higher [/size][size="2"]β[/size] [size="2"](beta) compared to the RV of Agni-I/II, similar to RV-MK4 of Agni-III & Agni-III++.[/size]



[size="2"]Propulsion[/size]



[size="2"]First Stage: A new 1.2 meter diameter[sup][[url="http://www.bharat-rakshak.com/MISSILES/Agni.html#92.A"]92.A[/url]][/sup] booster case made of 250-Maraging steel with improved chamber pressure and fuel mass-fraction (estimated 0.88). Approximately 12 meter long and 20 tonne mass[/size]



[size="2"]Second Stage: Lightweight filament wound carbon composite motor casing[/size][sup][size="1"][[url="http://www.bharat-rakshak.com/MISSILES/Agni.html#93"]93[/url], [url="http://www.bharat-rakshak.com/MISSILES/Agni.html#94"]94[/url]][/size][/sup][size="2"] for Stage-II with improved fuel mass-fraction (estimated between 0.90 - 0.92[/size][size="1"][sup][[url="http://www.bharat-rakshak.com/MISSILES/Agni.html#95"]95[/url]][/sup][/size][size="2"]).[/size]



[size="2"]Agni-IIAT Configuration[/size]



[size="2"]Agni-IIAT Stage 1[/size] ---- [size="2"]Agni-IIAT Stage 2[/size] ---- [size="2"]PBV/HAM[/size] ---- [size="2"]RV[/size] [size="2"]



Gross Mass [/size] ----[size="2"]20,000 kg[/size] ----[size="2"] 6,000 kg[/size] ---- [size="2"]220 kg [/size]

[size="2"]Fuel Mass [/size] ----[size="2"]17,600 kg[/size] ---- [size="2"]5,400 kg [/size] ---- [size="2"]40 - 180 kg[/size]

[size="2"]Empty Mass[/size] ----[size="2"]2,400 kg[/size] ---- [size="2"]600 kg[/size] ---- [size="2"]20 - 50 kg[/size] ---- [size="2"]50 kg[/size]

[size="2"]Fuel-Mass-Ratio[/size][size="1"][sup][[url="http://www.bharat-rakshak.com/MISSILES/Agni.html#96"]96[/url]][/sup][/size] ---- [size="2"]0.88[/size] ----[size="2"]0.90[/size] ---- [size="2"]0.82[/size]

[size="2"][color="#ffffff"].[/color][/size]



[size="2"]Thrust @ Vacuum [/size] ---- [size="2"]78,600 Kgf[/size] ----[size="2"]42,580 Kgf[/size] ---- ----

[size="2"]Thrust @ Sea Level [/size] ---- [size="2"]70,400 Kgf[/size] ---- ---- ----

[size="2"][color="#ff0000"](Burn Time)[/color][/size] ---- [size="2"][color="#ff0000"](58 seconds)[/color][/size] [size="2"][color="#ff0000"]--- (35 seconds)[/color][/size]





[size="2"]Length[/size] ---- [size="2"]12 meters[/size] ---- [size="2"]4.8 meters[/size] ---- ---- [size="2"]2.6 meters[/size]

[size="2"]Diameter [/size] ---- [size="2"]1.2 meter[/size] ---- [size="2"]1.2 meter[/size] ---- ---- [size="2"]1.0 meters[/size]



---------------------------



[left][size="1"][83] 'Agni missile will travel lighter soon', PTI [ THURSDAY, OCTOBER 13, 2005 12:45:45 PM] Economic Times. " Agni, with a power plant made of composite materials that would considerably reduce the weight of this IRBM class missile". "Agni is an intermediate range ballistic missile with two solid fuel stages and a Post Boost Vehicle integrated into the missile's Re-entry Vehicle, which is made of a light-weight carbon-carbon composite material able to sustain high thermal stresses." [url="http://economictimes.indiatimes.com/articleshow/1261173.cms"]http://economictimes...how/1261173.cms[/url][/size][/left]

[left][size="1"] [url="http://timesofindia.indiatimes.com/articleshow/1261170.cms"]Agni missile to travel light from next year- The Times of India[/url][color="#000000"], [/color]October 13, 2005 PTI [url="http://timesofindia.indiatimes.com/articleshow/1261170.cms"]http://timesofindia....how/1261170.cms[/url] [/size][/left]

[left][size="1"][84] Pokharan-II test resulted in a lighter weapon payload, whereas the original RV was intended for a much heavier boosted fission weapon. In view of rapid developments however, the basic design earlier developed continued to be used and keeping the future option open, for more optimized and lighter payloads.[/size][/left]

[left][size="1"][85] Sify News, 08 August 2003: India develops world's first re-entry heat shield.[/size][/left]

[left][size="1"][86] [url="http://www.ias.ac.in/currsci/feb102004/372.pdf"]Composites: Use in saucepan handles, artificial limbs and the AGNI[/url] CURRENT SCIENCE, VOL. 86, NO. 3, 10 FEBRUARY 2004 Advanced Systems Laboratory (ASL), Hyderabad: "The front-end technologies being developed include ultra high temperature composites, high performance composite rocket motor casings, radome for missiles and aircrafts, all-carbon re-entry vehicle structures, carbon composite canister technology, thrust vectoring through flex nozzles for large rocket motors, solid propulsion, control systems, system integration and explicit energy management guidance systems." [url="http://www.ias.ac.in/currsci/feb102004/372.pdf"]http://www.ias.ac.in...b102004/372.pdf[/url] [/size][/left]

[left][size="1"][87] Sify News, 08 August 2003: 'India develops world's first re-entry heat shield'.[/size][/left]

[left][size="1"][88] Technical Tune to Agni Test before Talks. The Telegraph: 30 August 2004. "The range of the solid-propellant Agni-II intermediate range ballistic missile can be varied according to payload and trajectory. The objective of today's test would be to reduce the circular error of probability for the longer-range variant, meaning that the missile was probably carrying a reduced payload." [url="http://www.telegraphindia.com/1040830/asp/nation/story_3694401.asp"]http://www.telegraph...ory_3694401.asp[/url][/size][/left]

[left][size="1"][89] Deccan Herald, 20 Dec 2005. "Indo-Russian tie-up on GLONASS satellite system". [url="http://www.deccanherald.com/deccanherald/dec202005/state1861820051219.asp"]http://www.deccanher...61820051219.asp[/url][/size][/left]

[left][size="1"][90] 'Indian Regional Navigation Satellite System approved', 9/5/2006 [url="http://www.india-defence.com/reports/1894"]http://www.india-def...om/reports/1894[/url][/size][/left]

[left][size="1"][91] Sify News, 08 August 2003: 'India develops world's first re-entry heat shield'. Quote: "...developed and successfully flight-tested the unique all carbon composite re-entry heat shield with multi directional carbon re-entry nose tip and control surfaces in the Agni systems."[/size][/left]

[left][size="1"][92] Defence scientists embark on making 'smart' missiles. The Hindu Businessline, 02 October 2004.

[url="http://www.thehindubusinessline.com/2004/10/03/stories/2004100301340500.htm"]http://www.thehindub...00301340500.htm[/url][/size][/left]

[left][size="1"][92.A]Review panel studying Agni III failure: scientific adviser[color="blue"], The HINDU Date:10/11/2006 [url="http://www.thehindu.com/2006/11/10/stories/2006111015800700.htm"]http://www.thehindu....11015800700.htm[/url] "[/color]The first rocket motor case of the improved design, of maraging steel and with 1.2 metre diameter, for the Agni programme was handed over to the M. Natarajan, scientific advisor to the Defence Minister by the Ramakrishna Engineering Company." [/size][/left]

[left][size="1"][93] Sify News, 08 August 2003: India develops world's first re-entry heat shield. Quote: "The carbon composite motor casings are some of the inputs to enhance the performance of long-range systems."[/size][/left]

[left][size="1"][94] Composites: Use in saucepan handles, artificial limbs and the Agni missile. Current Science, Vol.86, No.3, 10 February 2004. Advanced Systems Laboratory (ASL), Hyderabad. "The front-end technologies being developed include ultra high temperature composites, high performance composite rocket motor casings, radome for missiles and aircrafts, all-carbon re-entry vehicle structure, carbon composite canister technology, thrust vectoring through flex nozzles for large rocket motors, solid propulsion, control systems, system integration and explicit energy management guidance systems". "The carbon composite motor casings are some of the inputs to enhance the performance of long-range systems." [url="http://www.ias.ac.in/currsci/feb102004/372.pdf"]http://www.ias.ac.in...b102004/372.pdf[/url][/size][/left]

[left][size="1"][95] Author's Note: "Mass-fraction comparable to filament wound stage of similar rocket stages."[/size][/left]

[left][size="1"][96] Propulsion System Status and Development Pathways In the Indian Context. 6th International Symposium, Propulsion for Space Transportation of the XXIst Century, Versailles, May 14 - 17, 2002.[/size][/left]

[size="1"][97] ISP is based on ASLV-1 information at ****[/size]



[size="1"][98]ISP is based on ASLV-2 information at ****[/size]



[left][size="1"][99] Assumes the HAM engine is like Indian LAM or R40A with N[sub]2[/sub]O[sub]4[/sub]/MMH fuel (10 kg engine weight). ISP (Vac) of 306 thrust of 394 Kgf.[/size][/left]

[left][size="1"][100] School of Mechanical & Aerospace Engineering Seoul National University. [url="http://rpl.snu.ac.kr/databank/india/india.html"]http://rpl.snu.ac.kr...ndia/india.html[/url][/size][url="http://rpl.snu.ac.kr/databank/india/india.html"]

[/url][/left]