greatindian
New Member
AgniII is technological better than Shaheen.
Both stages of the Agni-II have a solid propulsion system, which allows the missile to be mobile and flexible. This was confirmed, as the test which was conducted on 11 April 1999, was a rail-based missile launcher. The solid-fuel motor in the first stage of Agni-II, is similar to the first stage in the technology test-bed, itself based on the SLV-3 Space Launch Vehicle. However the solid-fuel motor in the second stage of Agni-II, has been reportedly designed anew for the missile. For manoeuvrability and thrust control, the second stage has a flex nozzle which enables small changes in the thrust vector direction in flight. The flex nozzle can be exploited with the help of an on-board closed-loop guidance & control system. Till now, the flex nozzle has been used only in the third-stage motor of the PSLV. At a range of 2000+ km, Agni-II has an apogee (the farthest point from earth) of 405 km, a re-entry speed of 3.9 km/second and a boost phase of 110 seconds. The re-entry vehicle uses its manoeuvring fins to porpoise the warhead, to avoid missile defenses while manoeuvring to its target, employing a terminal guidance radar operating in the C- and S-bands.
The then-incumbent Scientific Advisor to the Government and DRDO Chief, Dr. Abdul Kalam, has said that what is unique about the Agni-II is the trajectory shaping and guidance that is possible through software. Agni-II, has appropriate on-board thrusters fitted on the second stage of the missile. This is because solid fuel is allowed to burn completely, which means that the velocity increment achieved before re-entry could be more or less from the mission perspective. Further, there is considerable dispersion or variation in the burn and thrust time of solid fuels. Any compensation that is given to the missile during its ballistic phase (which happens once the second stage is fully burnt out) should be based on the on-board sensor data and should be amenable to being adjusted reactively. These on-board thrusters are driven by liquid-fuel and provide small increments in the appropriate directions to shape the trajectory depending upon the target of the mission. It is these thrusters that give the manoeuvrability during the missile's re-entry phase. This has apparently been optimised through on-board software which, based on the initial trajectory fed in, does an appropriate velocity trimming. In effect this is a hot gas active velocity correction system.
Source: bharat-rakshak.com
Both stages of the Agni-II have a solid propulsion system, which allows the missile to be mobile and flexible. This was confirmed, as the test which was conducted on 11 April 1999, was a rail-based missile launcher. The solid-fuel motor in the first stage of Agni-II, is similar to the first stage in the technology test-bed, itself based on the SLV-3 Space Launch Vehicle. However the solid-fuel motor in the second stage of Agni-II, has been reportedly designed anew for the missile. For manoeuvrability and thrust control, the second stage has a flex nozzle which enables small changes in the thrust vector direction in flight. The flex nozzle can be exploited with the help of an on-board closed-loop guidance & control system. Till now, the flex nozzle has been used only in the third-stage motor of the PSLV. At a range of 2000+ km, Agni-II has an apogee (the farthest point from earth) of 405 km, a re-entry speed of 3.9 km/second and a boost phase of 110 seconds. The re-entry vehicle uses its manoeuvring fins to porpoise the warhead, to avoid missile defenses while manoeuvring to its target, employing a terminal guidance radar operating in the C- and S-bands.
The then-incumbent Scientific Advisor to the Government and DRDO Chief, Dr. Abdul Kalam, has said that what is unique about the Agni-II is the trajectory shaping and guidance that is possible through software. Agni-II, has appropriate on-board thrusters fitted on the second stage of the missile. This is because solid fuel is allowed to burn completely, which means that the velocity increment achieved before re-entry could be more or less from the mission perspective. Further, there is considerable dispersion or variation in the burn and thrust time of solid fuels. Any compensation that is given to the missile during its ballistic phase (which happens once the second stage is fully burnt out) should be based on the on-board sensor data and should be amenable to being adjusted reactively. These on-board thrusters are driven by liquid-fuel and provide small increments in the appropriate directions to shape the trajectory depending upon the target of the mission. It is these thrusters that give the manoeuvrability during the missile's re-entry phase. This has apparently been optimised through on-board software which, based on the initial trajectory fed in, does an appropriate velocity trimming. In effect this is a hot gas active velocity correction system.
Source: bharat-rakshak.com