AGNI RV MK 2 manoeuvring missile

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  1. LETHALFORCE

    LETHALFORCE Moderator Moderator

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    http://wapedia.mobi/en/Agni-II


    Agni-II

    [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 the Walmart of nuclear and missile black-market run 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 option 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 is 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. On 19 May 2009, user trial of Agni-II was undertaken by Indian Army, while DRDO scientists provided required logistical support. The Agni-II missile was tested at 10.06 IST from a defence base in Orissa.[5] The missile was test fired from launch pad-4 from Integrated Test Range. Integrated Test Range is the missile testing facility on the Wheeler Island, near Dhamara in the district of Bhadrak. Initially it was announced by Indian media that India has successfully tested the nuclear capable Agni-II missile from a defence base in Orissa. According to official sources, the aim of the test was to give the Indian Army confidence to fire the missile on its own. The May 2009 test however ended in failure of the Agni II [6] when the second stage failed to operate correctly and the missile started to veer wildly off course. In a subsequent re-test at night time on Nov 2009,[7] the missile once again failed completely at the second stage, this time dropping directly into the sea. These repeated failures at user trials puts its operational viability in serious doubt.
    [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]. However it does not carry a MIRV payload, which is not to be intended to mean that India does not have the technology: the country launched and accurately placed ten satellites in a single launch in 2007, on its GSLV space vehicle, which was the first evidence of the country having revealed its expertise in this arena.
    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.
    While earlier test versions of the missile had a CEP of ±100 metres, the latest versions will have a CEP of around 30 metres.[8]
    [edit]Range
    The Bharat Rakshak website has extensive data and analysis 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 Minister 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. 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 soils. 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.
     
    Last edited: Feb 3, 2010
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  3. LETHALFORCE

    LETHALFORCE Moderator Moderator

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    http://www.indiandefencereview.com/2007/04/strategic-missiles.html

    Agni-II and Agni-I Maneuvering Re-entry Vehicle: MRV-Mk.2


    This RV largely inherits the basic structure, design and technology of the earlier Mk.1 RV of the Agni-TD, but has more functionality and superior performance. After making room for new and lighter Indian thermonuclear weapon payload, the RV has room for about 200 kg liquid fuel in pressurised vessels to serve as High Altitude Motor for propulsion, as well as velocity correction. At least one variant uses a set of solid fuelled impulse cartridges for velocity trimming. The less than perfect mating of lightweight TN weapon an RV designed for heavier 1,000 Kg payload imposed its own challenges (different CG and lowered ‘²’ due to lighter payload) that also required addition of aero-fins. The lowered ‘²’ more rapidly slows the RV makes it susceptible to atmospheric disturbances and interception. On the other hand, reduced payload mass significantly increased the missile velocity & range
    The RV has an attitude control system and aerodynamic maneuver fins, for better control, accuracy and survivability. Unconfirmed reports suggest that an improved optical or radar terminal phase correlation system has been developed to provide accuracy of around 40 metres CEP.Agni-II and Agni-I Maneuvering Re-entry Vehicle: MRV-Mk.2
    This RV largely inherits the basic structure, design and technology of the earlier Mk.1 RV of the Agni-TD, but has more functionality and superior performance. After making room for new and lighter Indian thermonuclear weapon payload, the RV has room for about 200 kg liquid fuel in pressurised vessels to serve as High Altitude Motor for propulsion, as well as velocity correction. At least one variant uses a set of solid fuelled impulse cartridges for velocity trimming. The less than perfect mating of lightweight TN weapon an RV designed for heavier 1,000 Kg payload imposed its own challenges (different CG and lowered ‘²’ due to lighter payload) that also required addition of aero-fins. The lowered ‘²’ more rapidly slows the RV makes it susceptible to atmospheric disturbances and interception. On the other hand, reduced payload mass significantly increased the missile velocity & range
    The RV has an attitude control system and aerodynamic maneuver fins, for better control, accuracy and survivability. Unconfirmed reports suggest that an improved optical or radar terminal phase correlation system has been developed to provide accuracy of around 40 metres CEP. It is interesting to note that long-range missiles developed by other countries use RVs that are passive ballistic mass, thus their accuracy depends on ability of missile’s RV-bus to place RV on precise ballistic trajectory. The Agni-RV Mk.2 on the other hand, is more advanced because it embodies propulsion, navigation and control all the way to the target.
    It is interesting to note that long-range missiles developed by other countries use RVs that are passive ballistic mass, thus their accuracy depends on ability of missile’s RV-bus to place RV on precise ballistic trajectory. The Agni-RV Mk.2 on the other hand, is more advanced because it embodies propulsion, navigation and control all the way to the target.
     
  4. LETHALFORCE

    LETHALFORCE Moderator Moderator

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    http://www.bharat-rakshak.com/SRR/Volume13/sanjay.html#3

    Manoeuvring Re-Entry Vehicle: Agni RV-Mk2


    The Agni’s re-entry vehicle is designed to ensure that the temperature inside the vehicle does not exceed 60°C, a condition necessary to protect the warhead and electronic systems placed inside. The Agni’s Manoeuvring Re-entry Vehicle (MRV) is made of multi-directionally carbon fibre woven reinforced carbon-carbon composite material.34 The 0.8m diameter and 4 metre 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 a carbon/epoxy filament mould constructed on a CNC winding machine. The inner layer 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.35 The outer ablative layer ensures high thermal robustness for shock and temperature extreme.

    The 1980 vintage RV was reportedly originally designed to be able to carry a BARC developed boosted nuclear weapon of 200kT yield weighting 1,000 kg (1980 vintage design). After making room for a new and lighter Indian Thermo-nuclear weapon payload (1995 vintage design), the MRV has room for about 200 kg (estimated) liquid fuel in pressurised vessels. For velocity correction though, approximately 50-80 kg is estimated to be sufficient. At least one variant type uses a set of solid fuelled cartridges for velocity trimming.

    The Re-entry Vehicle (RV) is reported to have an attitude control system and aerodynamic manoeuvre fins, that also make missile defence more difficult.36 Unconfirmed reports suggest that an improved optical or radar terminal phase correlation system has been developed to provide accuracy of around 40m CEP, although later reports have suggested that the accuracy was around 100 to 200m CEP. The RV largely inherits the basic shape, design and technology of the earlier Mk.1 RV of the Agni-TD.

    The Agni is unlike long-range missiles developed by western countries, where the RV is purely a passive ballistic load whose accuracy depends on the launching vehicle’s exact insertion into the desired sub-orbital trajectory. Large inaccuracy associated with first generation RV involved spinning the RV for greater stability during atmospheric re-entry. Second-generation western missiles were mostly MIRV and the accuracy was greatly improved by use of a payload bus with a HAM velocity correction package for more accurate sub-orbit insertion. It also allowed individual MIRV payload to be imparted slightly different velocity so that each could be independently targeted to a different target albeit in the vicinity of each other. As before, the RV continued to be passive and purely ballistic.

    Agni-RV Mk-2 is more advanced than western RVs, for it embodies propulsion, 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.37

    The manoeuvring fins allow:

    – Trajectory error to be determined late into the flight and corrected using aerodynamic force during re-entry.38

    – Execute 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 range,39 reducing the thermal and physical stress40 at a modified Max-Q point.

    – Support a wider range of payload weight and configuration.

    – Terminal manoeuvre dive for a more acute target interdiction angle improving CEP.

    Velocity correction package for greater precision; using an integrated High Altitude Motor (HAM) (liquid fuelled or a set of solid-fuel cartridges) to correct impulse variance of solid fuelled stages and subtle launch trajectory perturbation.

    Depending on actual payload configuration, the HAM fuel load can be increased to trade range for a lighter / compact weapon.

    The larger volume allows more sophisticated ABM counter measures.

    Avionics, Navigation and Control

    The Agni family of missiles uses a strap-down INS system for flight control and navigation.

    The Agni introduced a new concept by adopting MIL-STD-1553 databus for all on-board communication and control device interconnections (mainly INS system, Flight Control Computer, actuators and sensors).41 It is the standard that is adopted in new civilian and 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 making 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 customised 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 modern missiles are moving towards digital buses using commercial off-the-shelf technology, which enables affordable sub-system replacement or enhancement.

    Accuracy

    Agni-II navigation and aiming utilises an advanced ground based beacon system using TDOA (Time Delay Of Arrival) technique similar to GPS42 that constantly provides missile flight position and velocity update that has been proven in test flights.43 The TDOA system reportedly improved the accuracy by three times.44

    India has demonstrated a measure of mastery in navigation sensors and flight control through its space programme. The placement accuracy in GTO (involving powered flight of 1,000 seconds, much of it in sub-G or gravity free environment) is a far more complicated and delicate matter45 than that of the sub-orbital trajectory of an IRBM. Thus the GSLV-D2 and GSLV-F01 GTO Apogee accuracy of 1965 PPM46,47 and 361 PPM48,49 respectively, compares with Agni-II’s 40 metres CEP at IRBM range with 13 PPM accuracy.

    It is worthwhile to note that the 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. On the other hand, the INS in a combat aircraft requires continuous operation of IMU(Inertial Measurement Unit) 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 the 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 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 a cumulated sum of:

    Accuracy of determining geographic coordinate of target and launcher;

    Accuracy of hitting the designated coordinates that is determined by the missile’s navigation and control system.
     

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