Saturday, October 11, 2008

TRISHUL SAM

TRISHUL SAM
The Trishul (Trident) is a short range, quick reaction, all weather surface-to-air missile designed to counter a low-level attack. It has been flight tested in the sea-skimming role and also against moving targets. It has a range of 9 km and is fitted with a 5.5 kg HE-fragmented warhead. It's detection of target to missile launch is around 6 seconds. The missile can engage targets like aircraft and helicopters, flying between 300 m/s and 500 m/s by using its radar command-to-line-of-sight guidance. It operates in the K-band (20 - 40 GHz), which makes it difficult to jam. In the K-band three-beam system, the missile is initially injected into a wide beam, which then hands it over to a medium beam, which passes over to a narrow beam, guiding it to the target.

The Trishul SAM, being test-fired from a launcher at INS Dronacharya


The Trishul has high manoeuvrability and is powered by a two-stage solid propellant system, with a highly powered HTBP-type propellant similar to the ones used in the Patriot. It is constructed of maraging steel to withstand the stress. Successful flight trials in a tube launched mode using folded fins against balloons and Pilot-less Target Aircraft (PTA) targets were carried out. One flight trial was guided throughout the trajectory using fixed line of sight and infra-red gathering guidance systems as per programmed flight. The army variant, Trishul Combat Vehicle (TCV), is based on a tracked BMP-1 infantry combat vehicle and houses all equipment including radars, command-guidance system and missiles.
David C Isby of Jane's Defence Weekly reported that after a spate of unsuccessful tests, it was decided that the Trishul SAM will not be fielded as an operational system but will be continued as a technology demonstration program. Trishul was one of the longest-running Indian Defence Research & Development Organisation (DRDO) missile development programs. The program began in 1984, and more than 40 test flights have been conducted. Defence Minister George Fernandes told Indian Parliament that while the Trishul had demonstrated a number of complex technologies, including an ability to defeat sea-skimming targets, it still had not been proved to be effective. By continuing the program as a technology demonstrator, India hopes that some of the technology from Trishul can be incorporated in other missile projects. The official cost of the Trishul program has been some Rs.3 billion (US $62.5 million).

The Trishul SAM being test-fired from the Trishul Combat Vehicle (TCV)

The Trishul missile had been intended to be a multi-service design. The Indian Air Force, which had intended to adopt the Trishul for an airfield-defence role, recently turned against the project. The Army has also stated that the Trishul was unlikely to meet its requirements for a replacement for the Russian-designed OSA-AKM (SA-8b Gecko) self-propelled SAM system. The Indian Navy had designed recent warships to include the Trishul as their armament, so the decision not to make the system operational is likely to require selection of an alternative system and modification of the warships that were to use the Trishul missile. This lead to an expansion of the Indian procurement of the Israeli-built Barak SAM system, of which seven systems were already ordered and another 10 systems have been planned for.

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ASTRA BVRAAM

ASTRA BVRAAM
© Arun Vishwakarma
Astra is a state-of-the-art beyond visual range air to air missile (BVRAAM) designed for a range of over 80 km in head-on mode [1] and 20 km in tail-chase mode. It can engage highly manoeuvring targets. The Astra missile programme is headed by the Defence Research & Development Organisation (DRDO). The goal of this programme is to provide the Indian Air Force (IAF) with an indigenously-designed BVRAAM to equip the IAF's Mirage 2000, MiG-29, Su-30MKI and the Light Combat Aircraft (LCA). A model of the Astra missile was first shown to the public at Aero India '98. On 25 July 2001 in Indian Parliament, then-incumbent Defence Minister Jaswant Singh said that a feasibility study for the Astra has commenced, after the completion of which a project for development of the Astra is planned to be undertaken.

Model of the Astra BVRAAM at Aero India '98. The other 'missile' model in the background is also another DRDO creation --> the medium-range Akash surface-to-air missile.
Development of this missile is likely to take about seven to eight years. The Indian government funded the Rs.1000-crore national project to develop a futuristic BVRAM missile Astra in June 2004 for delivery by 2009. Led by the Hyderabad-based Defence Research & Development Laboratory (DRDL), this indigenously developed missile is estimated to cost Rs. 3 to 5 crore. The missile is expected to be at the high-end of tactical missiles, and propel India into the exclusive club of countries to possess such missiles. The US has a similar missile but heavier, while Israel also has a BVR missile, but the range is comparatively shorter [2]. The Mirage 2000H has been designated as the first potential platform for the Astra when the weapon enters service at the end of this decade. The Astra was first test fired on 09 May 2003.
Model of the Astra BVRAAM at Aero India '03 with its inner components on display.


The missile is capable of operating in the altitude bracket from sea level to 20 km. It has a single stage smokeless solid fuel rocket with a burn time of 5.4 seconds. It's low drag low aspect ratio wings allows it to reach long range. It uses dual mode guidance i.e. inertial navigation during midcourse and active radar homing in terminal phase. Secure data link allows midcourse re-tasking [3]. On board autopilot and guidance software uses Artificial Intelligence (AI) for accurate guidance and optimized trajectory. The on-board ECCM capability allows it to stay on course in spite of enemy ECM (deception or noise jamming) by target aircraft (self protection jammer or dedicated EW aircraft). The 15 kg high explosive payload is pre-fragmented and proximity fuse armed. The guidance computer aims the shape charge to focus the explosive energy towards the target.

A front side perspective view of a model of the Astra BVRAAM at Aero India '05.

The Astra is intended to have performance characteristics similar to the R-77RVV-AE (AA-12), which currently forms part of the IAF's missile armoury. The missile is 3.8 metres long and is said to be configured like a longer version of the Super 530D, narrower in front of the wings. Astra uses a HTPB solid-fuel propellant and a 15 kg HE (high-explosive) warhead, activated by a proximity fuse. The missile has a maximum speed of Mach 4+ and a maximum altitude of 20 km. The missile is designed to pull a lateral acceleration of 40g in both yaw and pitch planes using 4 fins at the rear as all moveable control surfaces. The missile can also be launched in close combat. Although designed to use a locally developed solid fuel propellant, DRDO is also looking at rocket/ramjet propulsion to provide greater range and enhanced kinematic performance.
A rear side perspective view of a model of the Astra BVRAAM at Aero India '05.


Robert Hewson, editor of Jane's Air Launched Weapons (JALW), in a March 2003 issue of Jane's Defence Weekly (JDW) stated, "The basic Astra design uses a metallic airframe with a long low aspect-ratio wing and a single-stage smokeless rocket motor. After launch, the missile will use a combination of inertial mid-course guidance and/or data-linked targeting updates before it enters its terminal acquisition phase. In a head-on engagement, the Astra will have a maximum range of 80 km. The missile's onboard radio-frequency seeker has been largely designed in India but incorporates a degree of outside assistance, according to DRDO sources. It will have an autonomous homing range of 15 km. The missile's warhead is a pre-fragmented directional unit, fitted with a proximity fuze. A radar fuze already exists for the Astra, but the DRDO is currently working on a new laser fuze.

A cross section diagram of of the Astra BVRAAM , on display at Aero India '05.

Specifications
• Length: 3570 mm• Body Diameter: 178 mm• Wing Span: Not Known• Launch Weight: 154 kg
• Air Launcher Weight: 60 kg• Launch Altitude: Sea level (minimum) to 20 km (maximum).
• Launch Speed: 0.6 to 2.2 Mach.
• Warhead: 15 kg pre-fragmented, high explosive, directional warhead.• Propulsion: One solid rocket motor.• Burn Time: 5.4 seconds.
• Range: 80 km head on, 20 km tail chase.
• Maximum Turning Acceleration: 40 Gs (Yaw & Pitch)
• Fuse: Radar Proximity (laser proximity to follow).• Guidance: Inertial midcourse with data-linked updates, active-radar terminal homing.

AKASH SAM

AKASH SAM
The Akash (Sky) is a medium-range, theatre defence, surface-to-air missile. It operates in conjunction with the Rajendra surveillance & engagement radar. This system will replace the SA-6 / Straight Flush in Indian service and is also expected to be integrated with the S-300V (SA-10 Grumble) low-to-high altitude SAM in an integrated air defence system to counter SRBM / IRBM threats along the Pakistani and Chinese borders.

Test fire of an Akash SAM from a specially modified BMP-1 IFV chassis.
The missile is based heavily on the SA-6 and is claimed that Rajendra is similar to the 30N6 Flap-Lid B engagement radar, used by the S-300 ATBM system. The Akash's first flight occurred in 1990, with development flights up to March 1997. Operational tests and evaluations are currently ongoing and the missile is expected to enter service with the army and air force only in 2003. Officials have said that the missile will also undergo user trials with the Army for integration with the S-300PMU-1 anti-tactical ballistic missile systems, of which the Army has purchased an unspecified number, as well as with AEW aircraft. Plans exist for a navalised version in VLS mode.
The Akash uses an integral ramjet rocket propulsion system to give a low-volume, low-weight (700 kg launch weight) missile configuration, and has a low reaction time - from detection to missile launch - of 15 seconds. This allows the missile to carry a heavier warhead (60 kg). The solid-propellant booster accelerates the missile in 4.5 seconds to Mach 1.5, which is then jettisoned and the ramjet motor is then ignited for 30 seconds to Mach 2.8 - 3.5 at 20g. Akash has a range of 27 km, with an effective ceiling of 15 km. It is capable of detecting & destroying aircraft flying at tree-top height. Development is on to increase speed, maximum altitude and range to 60 km. A dual mode radar/infra-red seeker is also being developed as is a longer range version of the Rajendra radar, to give earlier warning and tracking of ballistic missile targets.

An Akash SAM battery mounted on a specially modified BMP-1 IFV chassis.

In appearance, Akash is very similar to the ZRK-SD Kub (SA-6), with four long tube ramjet inlet ducts mounted mid-body between wings. Four clipped triangular moving wings, mid-body, for pitch/yaw control. Forward of tail, four inline clipped delta fins with ailerons for roll control. Flight control surfaces operated by pneumatic actuators. The warhead has a lethal radius of 20 metres, weighs 60 kg and has Doppler radar proximity/contact fusing. The missile is believed to have tail G/H-Band beacon to assist tracking by engagement radar. Guidance system is inertial with mid-course command updates from Rajendra and semi-active radar seeker for terminal phase (final 3-4 seconds).
Rajendra is a 3D phased-array surveillance/engagement radar developed by the Electronic Research & Development Establishment (ERDE). Also mounted on a modified BMP-1 chassis, like the Akash, the radar is capable of tracking 64 targets, engage 4 simultaneously and guide up to 12 missiles. The system is reportedly similar to the 30N6 (Flap-Lid B) engagement radar. Has air surveillance, multiple target tracking and multiple missile guidance functions via multi-channel monopulse. Features fully digital signal processing system with adaptive moving target indicator, coherent signal processing, FFTs, and variable pulse repetition frequency.

The 3D Rajendra radar mounted on a specially modified BMP-1 IFV chassis.

Mounted on a turntable at the front of a raised platform behind the driver's station, the multi-element antenna arrangement folds flat when the vehicle is in motion. Radar comprises surveillance antenna array with 4000 elements operating in the G/H-Band (4-8 GHz), engagement antenna array with 1000 elements operating in the I/J-Band (8-20 GHz), a 16-element IFF array and steering units. The surveillance radar range is 60 km against aircraft targets. A longer range version is being developed. The Army intends to use the Rajendra radar in the artillery locating role as well. An Akash battery consists of three missile launch vehicles (triple launcher on a modified BMP-1 chassis), a Rajendra fire control radar vehicle, a long-range surveillance radar vehicle and an armoured command vehicle. Series production of ~25 missiles per year, was expected to commence in 2000 at Bharat Dynamics Ltd. No reliable information has been received so far, as to whether Akash missile production has begun.

INTRODUCTION: AGNI-TD/TTB

India's long-range missile program first started in around 1972 as Project Valiant, a three stage (liquid engine) ICBM missile. The project envisaged the use of three 30 tonne thrust liquid propulsion engines[5], developed in 1974, for the first stage booster and the second stage using one engine. The project was subsequently brought to a close and a more integrated missile development program was launched under the aegis of the IGMDP.
The Agni-TD/TTB (Technology Demonstrator / Technology Test Bed) project objectives were to test and validate:
1. Re-entry test vehicle to evaluate structure, guidance and control during re-entry into earth's atmosphere at hypersonic velocity. The RV used multi-directionally reinforced carbon-fiber preform (MRCP) technology.
2. Inertial Navigation System.
3. Rocket Staging.
Compared to the Prithvi, the Agni is a much larger system with a range of 2,500 km and a payload of 1,000 kg[6].The original Agni-TD/TTB was an amalgam of the Prithvi and the SLV-3 booster. The Agni-TD/TTB was a cheap test vehicle to prove re-entry and guidance technology for use on a more advanced platform[7]. 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 motor.

The first Agni launch on 22 May 1989 used a shortened Prithvi 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[8]. The RV used multi-directionally reinforced carbon-fiber preform (MRCP) technology[9]. The last test of the basic 'Agni-TD/TTB' on 19 February 1994 was a major technical breakthrough for India. The system tested, included a manoeuvrable re-entry vehicle for increased accuracy with terminal guidance[10]. This terminal guidance system reportedly consists of a scanning correlation optical system based on a scanning focal plane homing head in the infrared and millimeter wavelengths of the electromagnetic spectrum[11]. Considerable un-informed comments exist regarding the fact that Agni was only tested to a range of 1,450 km. No missile actually needs to be tested to a full range. It is possible to lift or depress the trajectory of the missile to simulate a longer range.
Dr. APJ Abdul Kalam stated that the missile could be fully deployed within two years[12]. Dr. Kalam also asserted that the Agni was ready for serial production while some simultaneous development flights aimed at achieving a much greater performance are undertaken[13]. Dr. Kalam claimed that no further test flights are necessary for the basic Agni system and that it is ready for production. In April 1995, Prime Minister PV Narasimha Rao (correctly) denied allegation[14] that under US and G7 pressure, India temporarily paused the Agni program after completion of the TD phase and after three test flights. In fact during the time, Prime Minister Rao secretly sanctioned the development of an augmented version of the Agni[15]as well as speed up efforts to build more advanced nuclear weapons[16] and set up a nuclear command and control system for the safe custody, deployment, and employment of such weapons, distributed over the country to ensure survivability and safety but totally under civilian control[17]. The Agni-TD program ran its course with the development and proving of crucial technologies for full-fledged, multi-staged, long-range ballistic missiles, including re-entry and navigation avionics. This missile reached engineering status and it is believed that none were released to the military, although during the Kargil imbroglio few units were made ready as nuclear deterrence[18]. This model is not believed to exist anymore, having being superseded by the Agni-II that has been put on line production and operationalized[19].
Description
Generally liquid fuelled missiles are more accurate because the navigation & control system can precisely control the impulse from the engine by controlling or limiting its thrust. Solid fuelled rockets can't turn off thrust on demand and further due to subtle manufacturing variances and actual operating conditions the exact impulse from a solid motor isn't known beforehand. All this makes control & aiming more challenging and the missile accuracy suffers unless mitigated by other means. The solid fuelled Agni's trajectory has a shallow re-entry angle and manoeuvring RV (MRV) use body-lift aerodynamics to correct trajectory error, as well as reduce the thermal stress of re-entry. The Agni's RV has a velocity correction package to correct launch trajectory variances. Some Agni RV versions use a set of solid fuelled thruster cartridges[20] of predetermined impulse, allowing the onboard guidance controller to trim velocity, using discrete combination of impulse quantum along desired spatial orientation.
Re-Entry Vehicle: Agni RV-Mk.1
The Agni's re-entry vehicle is designed to ensure that the temperature inside the vehicle does not exceed 60° Celsius, a condition necessary to protect the warhead and electronic systems placed inside. The high beta RV uses blunt nose tip made of carbon-carbon-composite, to generate a separating shockwave that takes away most of the heated plasma and a carbon-phenolic RV cover protects the body from high ambient temperature and pressure. During tests, the re-entry vehicle technology was fully demonstrated when the nose-cone withstood temperatures of 3,000° Celsius while the inside temperature was only 30° Celsius. The Agni RV-MRV Mk.1 nose tip is made of a multi-directionally woven, reinforced carbon-carbon fiber composite material[21]. The 0.8 meter diameter and ~4 meter long, re-entry vehicle consists of five sections. Each of these sections is made up of a two-layer composite construction. The inner layer is made up of carbon/epoxy filament mould constructed on a CNC winding machine and is designed to bear structural loads. The outer layer is made up of carbon/phenolic filament wound construction and cured in an autoclave at 7 bar pressure[22]. The outer ablative layer ensures high thermal robustness for shock and temperature extremes.
The RV appears to house an integrated High Altitude Motor (HAM), instead of a separate Post Boost Vehicle and classic purely passive ballistic warhead seen in western missiles, that is liquid fuelled and is used to correct impulse variance of solid fuelled stages and subtle launch trajectory variance. 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. There are indications that the MRV is intended to enter a gliding trajectory[23] when it enters atmosphere at an altitude of 100 km[24]. This has following implications:
1. The missile's range is extended.2. Less acute re-entry thermal stress.3. The manoeuvring makes it difficult for ABM defenses to intercept the missile.
Interestingly in 1987 IGMDP/ASL first envisaged developing a re-entry vehicle "designed for 100-250 Kg payload at speed of 7-8 km/sec"[25], clearly corresponding to a just a light weight fission-weapon & ICBM range[26]. But strategic requirement clearly also required high yield weapons that imposes bigger space and weight envelop. After some serious thinking, reviews and debates, the RV was to be designed for bigger payloads to match BARC's high yield weapon. The RV envelop was driven by weapon size and weight parameters corresponding to 200 Kt yield. In the 1980's BARC came up with boosted fission weapon design for the purpose with 1000Kg mass resulting in the Agni RV-MK.1. As evident from Agni-III RV design this first RV-MK.1 design was designed for the ultimate long range.
It is useful to note that Agni's advanced blunt nose high beta RV design using carbon-carbon nose tip and separating shockwave and is only now being incorporated in US ICBM replacing their mainstay RVs that hitherto used high beta RV using heat-sink concept employing sharp graphite nose tip and ablative cover sheath, with blunt nosed MK4A RV. Strangely it also looks very similar to Indian Agni-RV Mk-1 [26A].

Propulsion
First Stage: The booster motor is one meter in diameter and ten meters in length. It has approximately 9 tons solid propellant and a mass fraction of 0.865 (estimated). The stage features three segments of propellant grain, with an internal star configuration[27] 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 and later Agni variants use HTPB [hydroxyl-terminated polybutadiene]. The propellant is of star configuration[28] 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[29].
Second Stage: Agni-TD used a reduced Prithvi stage as its second stage. The initial test flight used a shortened version of Prithvi with lesser fuel, later flights used full fuel configuration. The liquid fuelled second stage of Agni-TD required in addition, two types of 'Ullage and Retro Motors' to maintain positive G-forces during stage separation and liquid engine startup. Both the ullage and retro motors are made of HE-15 aluminum alloy and use a double-base propellant. The motors are lined inside with high silica glass-phenolic ablative liners. Defense Research & Development Laboratory (DRDL) has expertise in the design, production, inspection, qualification, static-testing, and flight-testing of propulsion systems[30].

AGNI - STRATEGIC BALLISTIC MISSILE

AGNI - STRATEGIC BALLISTIC MISSILE
Agni-TD, Agni-I, Agni-II, Agni-IIAT, Agni-3, Agni-3++
© Arun Vishwakarma
Agni is a Sanskrit/Hindi word meaning Fire, given that it is a strategic ballistic missile. 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, providing better range and wider operating regime. Agni-III is a compact long range missile in test phase. Agni-3SL is a compact version of Agni-3 suitable for submarine launch.
Variants
Chronologically Agni-TD was first developed to quickly prove critical technologies, followed by the Agni-II IRBM, and then a short range version missile called Agni-I. In defense literature/publications this numbering system jumble, leading to the Agni-I name, often confuses readers. Indian reports mention development of the Agni-III-TD and Agni-III missiles with greater range and payload capability, albeit with great obfuscation of actual configuration and specification. Recently video images of Agni-III were released by DRDO. Based on technical viability and data from news fragments, the Agni family of missiles can be referred to the following likely configurations with what is believed to be the saner nomenclature.

Development
India launched the Integrated Guided Missile Development Program (IGMDP) in 1983 to concurrently develop and produce a wide range of missiles for surface-to-surface and surface-to-air roles. The IGMDP mandated development of the Agni, Prithvi, Trishul, Akash, Nag and Astra missile systems is managed by the DRDO. After successfully delivering all missiles except Trishul IGDMP program will conclude by Dec 2008. Bharat Dynamics Limited (BDL) manufactures Agni missiles and has the capacity to manufacture 18 missiles per year. A small number (less than five) of Agni-II missiles were believed to be operational in late 2000, and a production rate of 15 to 20 missiles per year has been suggested.
The Agni missile series consist of following missiles (in chronological order):
· Agni-TD/TTB (Technology Demonstrator / Technology Test Bed)
· Agni-II - IRBM (3300 km range, 1000 kg payload)
· Agni-I - SRBM (850 km range, 1000 kg payload)
· Agni-III - ICBM (5500 Km @ 1500Kg, 12,000 km @ 450 kg)
Agni variants under development (estimated performance):
· Agni-IIAT - ICBM (4,000 km range, 1500 kg payload)
· Agni-III++ - ICBM (10,000+ km range, 1000 kg payload)
Warhead Options
India's nuclear warhead options are still relatively limited, though adequate. Since the first Peaceful Nuclear Explosion (PNE) in 1974 (PoK-I), India adopted the recessed deterrence posture initially consisting of fission weapons (~15 KT yield) followed by boosted fission weapons of 200 KT yield, suitable for the Agni-TD/TTB. The PoK-II 1998 'Shakti' series of nuclear tests in Pokhran were reportedly done to validate multiple weapon designs, of 1995 vintage. Interestingly the 200 KT boosted fission design of 1980 was not tested in PoK-II, evidently its core components and technologies were validated in newer designs, and giving way to a lighter and more efficient S1 design. It is interesting to note that India has access to large quantities[135] of Tritium - produced at an extremely low cost - which lends flexibility to Indian weapon design options, an option that is not available or viable to prior nuclear weapon states.
The primary warhead for the Agni family would be a 200-300 Kt fusion weapon based on the Shakti-1 (Pokhran-II) test in 1998. The weapons yield is adjustable from 45-300Kt by changing the amount and quality of tertiary fuel. Yield of 45-200Kt range using natural Uranium and 45-300Kt range using moderately enriched fuel (U235 or Pu).
The fusion weapon based on the S-1 design reportedly weighs less than 450 Kg, however other sources indicate a mass of between 300 to 200 Kg[137A]. The 45kT S1 device reportedly weighed 450 kg and used an inert mantle to ensure third stage did not generate any yield[141]. It has also emerged that by 1982, the BARC/DRDO team had produced a design for a (pure) fission device that weighed between 170 and 200 kg for a yield of 15 KT - a huge change from the 1000 kg monster tested in 1974[142]. This would mean that a missile warhead based on this 1982 vintage design would weigh some 250 - 350 kg. On the eve of Agni-III D1 test flight on 12 April 2007, Union Minister of State for Defence MM Pallam Raju confirmed that "the strategic payload of the missile is between 100 kg to 250 kg"[142a]. One can conservatively deduce that the 250 kg mentioned by the minister corresponded to Indian Thermo-nuclear weapon, and 100Kg correspond to either 20Kt medium yield boosted fission weapon because low yield sub-KT weapon are tactical & not considered as strategic weapons. Therefore, when considering the range and payload parameters of the Agni and Prithvi missiles, these figures must be borne in mind.


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