Agni missile system
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| Agni-II Missile at the Republic Day Parade | |
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| Basic data | |
| Function | Short (Agni-I) and Intermediate (Agni-II) Range Ballistic Missile IRBM |
| Manufacturer | Integrated Guided Missile Development Program (IGMDP) |
| Unit cost | Rs 250-350 million (INR) or $ 5.6-7.9 million (USD)[1] |
| Entered service | (Tests) 04/11/99, 01/17/01 and 08/29/04 |
| General characteristics | |
| Engine | Single Stage (Agni-I)/ Two-and-half-stage (Agni-II) solid propellant engine |
| Launch mass | 12,000 KG (Agni-I)/16,000 KG (Agni-II) |
| Length | 15 m (Agni-I)/20 m (Agni-II) |
| Diameter | 1.0 m |
| Wingspan | Unknown |
| Speed | 7-8 km/sec (Agni-II)[2] |
| Range | 850 km (Agni-I)/3300-4800 km (Agni-II) |
| Flying altitude | >90 km |
| Warhead | Strategic nuclear (15 KT to 250 KT), conventional[3] HE-unitary, penetration, sub-munitions, incendiary or fuel air explosives. |
| Guidance | Strap Down - INS (Inertial Navigation System), optionally augmented by GPS terminal guidance with possible radar scene correlation |
| Launch platform | 8 x 8 Tatra TELAR (Transporter erector launcher) Rail Mobile Launcher |
The Agni missile (from Sanskrit Agnī meaning "Fire", one of the 5 elements of nature) is an intermediate-range ballistic missile developed under the Integrated Guided Missile Development Program by India. It was first tested at the Interim Test Range in Chandipur in 1989, and is capable of carrying a conventional payload of 1000 kg (2,200 lb) or a nuclear warhead. It consists of one (short range) or two stages (intermediate range). It is rail and road mobile. It is powered by solid and/or liquid propellants.
Agni-III is the third in the Agni series of missiles. The Agni I has a range of 700-800 km while the Agni-II as a range of 2,000–2,500 km. They are claimed to be a part of the "credible deterrence" against China and Pakistan. The Agni-II can only reach some parts of western China. Right now most of eastern China remains out of range from the Indian missiles.
Agni-III was tested on July 9, 2006 from Wheeler island off the coast of the eastern state of Orissa.[1] After the launch, it was reported that the second stage of the rocket had failed to separate and the missile had fallen well short of its target.[2] It can hit strategic targets deep inside China, including Shanghai and Beijing with a strike range of more than 3,000 km. It falls short of the range of ICBMs (inter-continental ballistic missiles) which have ranges over 5,000 km.
The Indian Missile Program has been a largely indigenous one with almost all of the equipment developed by Indian scientists. However it is delayed by some years as more variants of Agni are expected. Some parts of the missile have benefited from India's Space Program.
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[edit] Agni I
The earlier version of the Agni Missile (Agni-I) is a single stage, solid fuel, road and rail mobile, short-range ballistic missile (SRBM). It was the successor to the prototype "Agni-TD". It is propelled by solid fuel, giving it a shallow re-entry angle and manoevering RV body-lift aerodynamics gives it the ability to correct trajectory errors and reduce thermal stresses. The MRV has a velocity correction package to correct launch trajectory variances.Some Agni RV versions use a set of solid fuelled thruster cartridges of predetermined impulse, allowing the onboard guidance controller to trim velocity, using discrete combination of impulse quantum along desired spatial orientation.
[edit] Agni II
The Agni missile family is envisaged to be the mainstay of the Indian missile-based strategic nuclear deterrence. The Agni family will continue to grow its stable, providing a breadth of payload and range capabilities. The Agni-I is a short range ballistic missile (SRBM) with a single stage engine. While the Agni-II is an intermediate range ballistic missile (IRBM) with two solid fuel stages and a Post Boost Vehicle (PBV) integrated into the missile's Re-entry Vehicle (RV). The Agni's manoeuvring RV is made of a carbon-carbon composite material that is light and able to sustain high thermal stresses of re-entry, in a variety of trajectories. The Agni-IIAT is a more advanced version of Agni-II, albeit with more sophisticated and lighter materials, yielding a better range and operating regime.
[edit] Preface: Evolving Indian Security Environment
During the 1990s, India's security situation gradually worsened with security challenges from China, blatant Chinese nuclear and missiles proliferation to Pakistan, and mutual proliferation between Pakistan and North Korea. The strategic redline was crossed in 1998 when Pakistan tested the North-Korean supplied nuclear capable Ghauri (North Korean No-Dong) missile, that could threaten India's heartland. The international complicity in allowing nuclear proliferation by proxy into the hands of Pakistan and ability to deliver it over long ranges, obtained by trading in black-market North Korean No-Dong missiles, in return for Pakistani nuclear design and enrichment equipment by Pakistani scientist A.Q. Khan and the Pakistani Military. This and other international security developments forced India to go fully nuclear, resulting in the Pokhran-II (POK-II) nuclear test series and its weaponization by developing the Agni family of ballistic missiles that could deliver a variety of payloads over long ranges.
Quick deployment of the Agni-II was possible, by building on the earlier Agni-TD program that provided proven critical technologies and designs required for long range ballistic missiles. Thus when the decision was made to build the Agni weapon system, some quick optimization and ruggedization was done to the basic '1980 vintage' design, including a solid fuelled second stage. Further the solid fuel chemistry, RV and avionics were brought up to state-of-the-art levels. As the Pokhran-II (PoK-II) nuclear test proved a family of more powerful and lighter nuclear weapons, the 200 KT thermonuclear weapon is far lighter compared to 1000 kg earlier budgeted for the 200 KT boosted nuclear weapon. Thus a high yield weapon configuration now assumes a payload of 500 kg, including weapon and RV. However, in the interest of rapid development the basic design that was earlier developed continued to be used and keeping the future options open, for more optimized missile design and lighter payload. The Agni-II missile will be used by 555th Missile Group of the Indian Army.
[edit] Description
The Agni-II was first tested on 11 April 1999 at 9:47 a.m. IST (Indian Standard Time), from a converted rail carriage, with a carriage roof that slides open to allow the missile to be raised to the vertical for launch by two large hydraulic pistons. The launch process is controlled from a separate railcar. The missile was launched from the IC-4 pad at Wheeler Island, Balasore. Splash down was 2000 - 2100 km. down range in the Bay of Bengal, on a trajectory designed to simulate a range of 2800 - 3000 km. The Agni-II missile can also be launched from a road TEL vehicle, as demonstrated in the second test flight on 17 January 2001, at 10:01 a.m. IST (Indian Standard Time) to a range of 2100 km. This missile has a theoretical maximum range of some 3000 km with a 1000 kg payload (conventional or strategic).
Tested to range of over 2000 km, the Agni-II has an all-solid propellant system. After the January 17th test, the missile was cleared for production and it is possible that a production capacity (under-utilised at present) exists for 12 Agni-II missiles per year. On the January 17th test, the missile was alleged to have covered a range of over 2100 km with a 700 kg warhead. The Agni-II is designed to be launched from a rail-mobile launcher, it is also available in road-mobile configuration. This lends flexibility and reduces vulnerability to first strike.
The Agni-II will always be in a ready-to-fire mode and can be launched within 15 minutes as compared to almost half a day of preparation for the previous generation Agni-TD. In May 2001, and again in July 2001, the then-incumbent Defence Minister Jaswant Singh informed the Cabinet Committee on Security (CCS) that the Agni-II missile is operational, limited production had begun and induction being planned during 2001-2002. On 14 March 2002, Defence Minister George Fernandes informed Indian Parliament that the Agni-II has entered the production phase and is under induction. Agni-II is made by BDL in Hyderabad, with a production capacity of 18 missiles/year and costs about Rs.35 crore [34] for each missile.
[edit] Propulsion
First Stage: The Agni-II's first stage is largely similar to that of Agni-TD's first stage. However the Agni-II booster is believed to employ more energetic fuel; Booster ISP of 269 (vacuum) and 237 (sea-level). It has a propellant mass of about 9 tons and estimated mass fraction of 0.865.
Second Stage: The Agni-II's second stage weighs ~4200 kg and uses solid fuel propellant. Its case is presumably made of the same material, high-strength 15CDV6 steel, as the booster stage for ease of manufacturing. This solid propellant stage has flex nozzles for thrust vectoring, for precise trajectory control. Unlike the Agni-TD, the solid fuel second stage does not require retro motors for proper stage separation. It uses a vented inter-stage.
[edit] Manoeuvring Re-Entry Vehicle: Agni RV-Mk.2
The 1980-vintage RV was reportedly designed to be able to carry a BARC-developed, boosted nuclear weapon of 200 KT yield weighing 1000 kg, also of 1980 vintage design. After making room for new and lighter Indian thermonuclear weapon payload, of 1995 vintage design, the MRV has room for about 200 kg (estimated) liquid fuel in pressurized vessels. Although for velocity correction, approximately 50 to 80 kg is estimated to be sufficient. At least one MRV variant type uses a set of solid fuelled cartridges for velocity trimming. The RV is reported to have an attitude control system and aerodynamic manoeuvre fins, presumably to make missile defense more difficult. Unconfirmed reports suggest that an improved optical or radar terminal phase correlation system has been developed to provide accuracy of around 40 meters CEP, although later reports have suggested that the accuracy was around 100 to 200 meters CEP. The RV largely inherits the basic shape, design and technology of the earlier Mk.1 RV of the Agni-TD.
Agni is unlike long-range missiles developed by western missiles where the RV is a passive ballistic load, whose accuracy depends on the launching vehicle's exact insertion into the sub-orbital trajectory. A large inaccuracy associated with the first generation RV, involved spinning the RV for greater stability during re-entry. Second generation western missiles were mostly MIRV (Multiple Independently targetable Re-entry Vehicle) and the accuracy was greatly improved by the payload bus with HAM velocity correction package for more accurate sub-orbit insertion. It also allowed individual MIRV payloads to impart different velocities, so that each can be independently targeted to a different target, albeit in nearby vicinity of each other. As before the RV continued to be passive and purely ballistic. The Agni-RV Mk.2 is more advanced than the western RVs, because it embodies proposition, navigation and control all the way to the target. The RV re-enters at an altitude of 100 km, at a shallow angle, with a gliding trajectory [38].
[edit] Key Features of the Agni-RV Mk.2
- The manoeuvring fins that allows it to;
- Execute a non-ballistic trajectory to make interception more difficult.
- Overcome any perturbation due to high altitude atmospheric disturbance.
- Enable use of body lift at hypersonic velocity to glide the missile over longer ranges, thus reducing the thermal and physical stress at a modified Max-Q point.
- Trajectory error to be determined late into the fight and corrected using aerodynamic force during re-entry.
- Terminal manoeuvre dive for a more acute target interdiction angle improving CEP.
- Support a wider range of payload weight and configuration.
- Integrated velocity correction package for greater precision; has a set of solid fuelled cartridge(s) that are used to correct impulse variances of solid fuelled stages and subtle launch trajectory perturbation.
- Integrated High Altitude Motor (HAM) which is liquid fuelled. Depending on the actual payload configuration, the HAM fuel load can be increased to trade range for a lighter and more compact weapon.
- Larger internal volume allows more sophisticated ABM (anti-ballistic missile) counter-measures.
[edit] Avionics, Navigation and Control
The Agni family of missiles uses a strap-down INS system for flight control and navigation. Necessary inertial sensors were indigenously developed for the purpose, including laser rate gyros.
Agni-II introduced a new concept in missile control system by adopting MIL-STD-1553 databus for all on-board communication and control device interconnection --> mainly INS system, Flight Control Computer, actuators and sensors [42]. It is the standard that is adopted in new civilian & military aircraft (circuit routing and device mounting) and all the software in the Agni-II has been designed around this bus. DRDO sources claim that this reduces the number of connections and also makes the missile more rugged. However, some missile analysts feel that a standard databus may not be the best path to follow. It is said that a customized databus is better because in a standard databus, one tends to use off-the-shelf electronic devices whose performance may not be optimal. However most new missiles are moving towards digital buses using commercial off-the-shelf technology and which enables affordable sub-system replacement.
[edit] Accuracy
The Agni-II's navigation and aiming uses an advanced ground based beacon system using a TDOA (Time Delay Of Arrival) technique, similar to a GPS system, that constantly provides missile flight position and velocity updates and has been proven in test flights. The TDOA system reportedly improved the accuracy by three times. India has demonstrated a measure of mastery in navigation sensors and flight control through its space program. The placement accuracy in GTO (involving powered flight of 1000 seconds much of it in sub-G or gravity free environment) is far more complicated and delicate than that of the sub-orbital trajectory of an IRBM. Thus the GSLV-D2 and F01 GTO Apogee accuracy of 1965 PPM and 361 PPM respectively that compares with Agni-II's 40 meter CEP at IRBM ranges with 13 PPM accuracy.
It is worthwhile to note that INS error differs for a ballistic missile versus an aircraft. Ballistic missile accuracy is only dependent on the INS accuracy up to the point when rocket fuel is expended (100 seconds for Agni-II) and it exits the atmosphere (> 90 km altitude), after that the trajectory is purely ballistic that is predetermined and easily computed. INS in a combat aircraft requires continuous operation of IMU and navigation computer throughout the flight during which the error keeps building as IMU sensors drift. A ballistic missile that can update its position and velocity from auxiliary means, can completely eliminate the built up error from INS and continue flight at a precise predetermined path, if necessary correcting the launch error by using:
- Small velocity correction thruster package and/or
- Aerodynamic manoeuvring during re-entry (this requires active RV configuration with integrated INS and control system).
The Agni-II missile reportedly makes use of both the above techniques. The Agni-II exits atmosphere and expends the second stage at an altitude of 120 km and at a distance of about 150 km. This allows the ground based TDOA system to operate well within Indian Territory and at close range (i.e. robustness against Electronic Warfare interference). The missile maintains LOS (line of sight) well beyond apogee. The overall accuracy is the cumulated sum of:
- Accuracy of determining geographic coordinate of target and launcher.
- Accuracy of hitting the designated coordinates that is determined by missile's navigation and control system.
Launching the Agni from a surveyed site is one aspect of item 1 above. The sub-meter target coordinates, using national surveillance assets, (aerospace, sensors, etc) would largely address the accuracy of target coordinate designation. A long-range ballistic missile (passive RV) targeting error is typically spread in a highly elliptic pattern. The CEP is thus adversely biased by a wide error spread in a longitudinal axis (due to shallow incidence angle). The Agni's active manoeuvring RV with onboard IMU (INS) and control system can perform terminal manoeuvre to correct errors and make a more accurate top attack profile using greater incidence angle significantly reducing the longitudinal spread and overall CEP.
[edit] Range
The Bharat Rakshak Agni page » MISSILE ARMOURY » AGNI - STRATEGIC BALLISTIC MISSILE has extensive data and analsyis that uses public domain data and ballistic calculations to show that the range is greatly influenced by use or non-use of thrusters on the RV (required for velocity trimming) for propulsion as a HAM (High Altitude Motor). There seems to be room in the RV for about ~200 kg fuel (solid or liquid) after allowing for a long but lightweight TN weapon. This RV integrated HAM is referred to as the half stage after the two solid fuelled stages. This stage provides a disproportional increase in range for a lighter RV payload. Thus development of lightweight nuclear weapons is paramount to the missile's range.
When the Agni-II was first launched, then Defence Minster George Fernandes indicated that the maximum range of the Agni-II was 3000 km. Since then, ranges from 2000 km to 2500 km have been bandied about while Dr. Kalam, at Aero India '98, stated that Agni-II had a maximum range of 3,700 km! The range of 2000 km can be excluded, as the system has been tested to greater range in both 1999 and 2001. Given the test to 2300 km in 1999 and 2100 km in 2001, with an apparently lighter payload, would indicate that a variation in trajectory was used and it may be possible to extrapolate some more accurate estimates of Agni-II's maximum range.
It would appear that Agni-II has a theoretical ability to hit a target 3000 km away with a 1000 kg overall payload – (a 250 kg RV's deadweight and a 750 kg warhead). It is suggested that a 200 kiloton 'boosted fission' warhead was earlier developed for the Agni system when it was on the drawing board in the late 80s, however after the Pokhran-II series of nuclear test in May 1998, the 200 KT boosted fission design has clearly given way to a 200 - 300 KT two stage thermonuclear design that is expected to be much lighter. From the tables at Effect of payload and stage configuration on Agni-II range, one can see that a number of permutations and combinations are available to DRDO based on the existing Agni-II design and Indian propulsion technology. Range changes can be made by either varying the payload or by altering the engine configuration.
Given the available data, it is therefore clear that Agni-II has a maximum range of somewhere in excess of 3000 km, and possibly as high as 3500 km with a 1000 kg payload. Greater range with a lighter payload however requires the RV to be qualified for higher re-entry velocity and corresponding Max-Q for thermal stress.
[edit] Conclusion
As the backbone of the Indian land-based nuclear deterrent, the real significance of the Agni-II is the fact that it is both road and rail mobile. This is an indication of India's desire not to put its missiles into vulnerable silos. The mobility of the Agni-II, combined with the sheer physical size of India renders the mobile IRBM a very secure and survivable delivery system. Its range of strategic weapons payload and good accuracy make this strategic weapon useful for counter value as well as first strike role.
[edit] Agni III
Agni III an intermediate-range ballistic missile currently being developed by India as the successor to Agni-II.[4] Designed by the Indian government's Defence Research and Development Organisation, Agni III is intended to be a two-stage ballistic missile that is capable of nuclear weapons delivery.
Agni III is expected to be India's nuclear deterrent against People's Republic of China. Agni III development began when relations with China were still negative. However, the rapid improvement in friendly relations between the two nations has reduced the need for rapid development of the missile. Testing of Agni-III missile has been repeatedly delayed and until that time, the details must be considered as tentative, but provide insight to its potential configuration, capability and impact on strategic outlook. Some of the following is estimated based on fragmented news reports and anticipated features based on India's security concerns and capability.
The Agni-III has two stages with an overall diameter of 1.8 m. The first stage mass is about 24 tonnes and 7 m long, the second stage mass is about 8 tonnes and 2.5 m long. The missile is likely to support a wide range of warhead configurations, with a 3,500 km range and a total payload weight of 1000 kg.[4]
The stubby two-stage solid fuel missile is compact and small enough for easy mobility and flexible deployment on various surface/sub-surface platforms.
[edit] Propulsion
The Agni-III features two solid fuelled stages and with overall diameter of 1.8 meters. This diameter is compatible with a recently tested Indian sub-surface launch system, which has a 2.4 meter diameter launch tube aperture [93]. Pontoon underwater launching platforms for Project K-15. Image © DRDO
[edit] First stage booster
The first stage booster is made of advanced carbon composite materials to provide high mass fraction. It is anticipated to weigh 24 tonnes and have a length of 7 meters and diameter of 1.8 meter. The Isp is comparable to similar large solid motor of ISRO.
[edit] Second stage
The second stage made of advanced carbon composite materials is expected to be around 8 tonnes and have a length of 2.5 meters. The second stage reportedly incorporate flex nozzles, to provide necessary flight trajectory control.
[edit] Maneuvering re-entry vehicle: Agni RV-Mk.4
Agni-III supports a wide range of weapons, with total payload weight ranging from ~600 kg to 1,800 kg including decoys and other ABM countermeasures. Instead of conventional bus architecture, the RV (Re-Entry Vehicle) is likely to be self-contained with high altitude thrusters, navigation and re-entry control systems.
Lighter and tougher RV body 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 6000 degrees Celsius, and capable of greater re-entry velocity. The all composite RV has no metal backup.
[edit] Failed Launch
India test fired Agni III from Wheelers Island off the Bhadrak coast on July 9, 2006.[4] The launch was unsuccessful as the missile developed a snag and fell into the sea off the coast of Orissa. The failure was attributed to the missile's second-stage, which failed to ignite and hence did not separate.[5] Indian Defence Minister Pranab Mukherjee first claimed it was a "partial success", then later acknowledged that the test was a failure, and the missile was only air-born for 5 minutes instead of the expected 15 minutes.[6]
[edit] Conclusion
Agni-III is critical to Indian Credible Minimum Nuclear Deterrence. This missile is designed for heavy duty strategic role and capable of launch from multiple platforms. A successful test flight will signal a major watershed to realizing the elements of India's nuclear triad. However, India would need to improve the range of the missile from present 3500 km to 5000 km to pose any significant threat to Beijing.
[edit] See also
[edit] Web References
- ^ Technical tune to Agni test before talks,The Telegraph
- ^ [http://www.thehindubusinessline.com/2005/07/25/stories/2005072501331400.htm ASL: From long-range missiles to lightweight callipers],The Hindu Business Line
- ^ Interview: Dr. APJ Abdul Kalam, India Today (New Delhi), 26 April 1999
- ^ a b c "Agni-III test fired by India". The Indian Express. Retrieved on 2006-07-09.
- ^ "Agni-III develops snag, falls into sea". The Hindustan Times. Retrieved on 2006-07-09.
- ^ "Indian missile test 'was failure'", BBC, 2006-07-10.
