mrbm1

MEDIUM RANGE BALLISTIC MISSILE

Seminar ID: 1121

A Technical Seminar ReportSubmitted in partial fulfilment of

The requirements for theDegree of Bachelor of Technology

Under BijuPatnaik University of Technology

By

K Prasant Kumar Roll # CSE 200911067

April - 2012

Under the guidance of

Mr. Agyan Kumar Prusty

NATIONAL INSTITUTE OF SCIENCE &TECHNOLOGYPalur Hills, Berhampur, Orissa – 761008, India

ABSTRACT

MRBM is an exciting new technology with enormous potential for the security

community. It is resource which is intended to be attacked and compromised

to gain more information about the attacker and his attack techniques.

They are a highly flexible tool that comes in many shapes and sizes. This

report deals with understanding what a MRBM actually is ,and how it works.

There are different varieties of MRBM. Based on their category they have

different applications. This report gives an insight into the use of MRBM in

productive as well as educative environments. It also discusses the

advantages and disadvantages of MRBM , and what the future hold in store

for them.

i

ACKNOWLEDGEMENT

It is our proud privilege to epitomize our deepest sense of gratitude and

indebtedness to our guide, Mr. Agyan Kumar Prusty for his valuable

guidance, keen and sustained interest, intuitive ideas and persistent

endeavour. His inspiring assistance, laconic reciprocation and affectionate

care enabled me to complete my work smoothly and successfully.

I am also thankful to My Parents, for giving his valuable time and support

during the preparation of this report.

I acknowledge with immense pleasure the sustained interest, encouraging

attitude and constant inspiration rendered by Prof. Sangram Mudali,

Director, N.I.S.T. His continued drive for better quality in everything that

happens at N.I.S.T. and selfless inspiration has always helped us to move

ahead.

Last but not the least I cannot forget the co-operation my friends in this

endeavor.

K Prasant Kumar

ii

TABLE OF CONTENTS

ABSTRACT....................................................................................................................i

ACKNOWLEDGEMENT.............................................................................................ii

TABLE OF CONTENTS..............................................................................................iii

LIST OF FIGURES......................................................................................................iv

1. INTRODUCTION......................................................................................................1

2. MRBM BASICS........................................................................................................3

3. TYPES OF M R B M.................................................................................................4

3.1 BackOfficer Friendly............................................................................................5

3.2 Specter..................................................................................................................6

3.3 Homemade M R B M...........................................................................................7

3.4 Honeyd.................................................................................................................7

3.5 Mantrap................................................................................................................9

3.6 Honeynets...........................................................................................................10

4. VALUE OF M R B M..............................................................................................12

4. IMPLEMENTATION..............................................................................................16

4.1 M R B M Location.............................................................................................16

4.2 How does a M R B M Gather Information.........................................................17

4.3 Limiting Outbound Attacks................................................................................18

4.4 Putting the Honey into the Pot...........................................................................18

5. MERITS AND DEMERITS....................................................................................19

6. LEGAL ISSUES......................................................................................................21

7. FUTURE OF MRBM...............................................................................................23

8. CONCLUSION........................................................................................................24

REFERENCES.............................................................................................................25

iii

LIST OF FIGURES

Figure 3.1 Working of Honeyd......................................................................................8

Figure 3.2 A honeynet..................................................................................................10

iv

M R B M

1. INTRODUCTION

 What's the difference between a missile and a rocket?

Missiles and rockets are the same. It's their usage that varies. A ballistic

missile is a rocket that flies to a high altitude by firing its engines until all fuel

is expended and then lets gravity drop its warhead payload onto a pre-

planned target. It is a ground-to-ground weapon.

A similar rocket, if powerful enough, can be used to blast a satellite up to such

a high altitude above the atmosphere that it will be in orbit around Earth. The

satellite payload will stay up there for a period of time and then fall back down

into the atmosphere and burn up. 

The PGM-19 Jupiter was the first medium-range ballistic missile (MRBM) of

the United States Air Force (USAF). It was a liquid-fueled rocket using RP-

1 fuel and LOX oxidizer, with a single Rocketdyne LR70-NA (model S-3D)

rocket engine producing 667 kN of thrust. The prime contractor was

the Chrysler Corporation.The MRBM PGM-19 Jupiter initially was intended to

be guided by radio, but Later the Department of Defense assigned all land-

based long-range missiles to the USAF, with the Army retaining control of

battlefield missiles with a range of 200 miles (320 km) or less. The Jupiter

MRBM program was transferred to the Air Force, which had developed

the PGM-17 Thor MRBM independently.

In india the Medium range ballistic missiles developed by DRDO .The initial

Technology demonstrator version had a range of 1500 km but were based on

a solid and a liquid stage making for long preparation before firing .Learning

from these production variants of are solid fuel based to allow for swift

retaliation against adversaries Variants make use of either liquid or both liquid

and solid fuels .Developed as a battlefield missile, it could carry a nuclear

warhead in its role as a tactical nuclear weapon

0

M R B M

3. What is a Ballistic Missile

A ballistic missile is a missile that follows a sub-orbital ballistic flight path

with the objective of delivering one or more warheads to a predetermined

target. The missile is only guided during the relatively brief initial powered

phase of flight and its course is subsequently governed by the laws of orbital

mechanics and ballistics. To date, ballistic missiles have been propelled

during powered flight by chemical rocket engines of various types.

A ballistic missile trajectory consists of three parts: the powered flight portion,

the free-flight portion which constitutes most of the flight time, and the re-entry

phase where the missile re-enters the Earth's atmosphere. Ballistic missiles

can be launched from fixed sites or mobile launchers, including vehicles

(transporter erector launchers, TELs), aircraft, ships and submarines. The

powered flight portion can last from a few tens of seconds to several minutes

and can consist of multiple rocket stages.

When in space and no more thrust is provided, the missile enters free-flight. In

order to cover large distances, ballistic missiles are usually launched into a

high sub-orbital spaceflight; for intercontinental missiles the highest altitude

(apogee) reached during free-flight is about 1200 km.The re-entry stage

begins at an altitude where atmospheric drag plays a significant part in missile

trajectory, and lasts until missile impact.

The rocket-nozzle control system allows the missile to change its trajectory

several times during re-entry and even terminal phase, effectively preventing

pre-calculated intercept points of radar systems - which is a method nearly

all ABM systems use these days. As a high-speed ballistic missile and pre-

mission fueling capability, the accuracy of the missile is largely speculative

and cannot be confidently predicted for wartime situations being used for

precision attacks against high value targets such as command, control and

communications centres.

1

M R B M

3. TYPES OF MISSILE

Rockets used as military missiles are categorized by their ranges. Here

are the types

BSRBM is a battlefield short range missile capable of a very short flight of less than 100 miles. 

SRBM is a short range ballistic missile that travels from 100-500 miles. An example is the Russian SCUD missile, which has been exported to more countries than any other type of guided ballistic missile. Iraq fired 93 SCUDs during the Persian Gulf War in 1991. North Korea produced a version of the SCUD it called Hwasong. 

MRBM is a medium range ballistic missile that travels from 500-

1500 miles. Iran's Shahab-3 missile has a range of 800 miles, which

makes it an MRBM. It was derived from North Korea's No-dong missile

as was Pakistan's Ghauri missile. 

IRBM is an intermediate range ballistic missile that can hit a target

1,500-3,400 miles away. IRBMs frequently have been turned into

launchers for small satellites. This is accomplished by adding upper

stages to the rocket so it is more powerful. For example, during the

early days of space launches in in the United States, the Thor,

Redstone and Jupiter missiles were turned into space rockets. A

modified Jupiter known as Jupiter-C launched America's first satellite,

Explorer 1. Other examples of IRBMs turned into space launchers

include Israel's Shavit and North Korea's Taep'o-dong. 

MRBM is an intercontinental ballistic missile that can strike a target

3,400 to 9,200 miles away. That makes it a global weapon. An MRBM

has two or more rocket stages and flies up as high as 700 miles before

dropping its warhead payload on a target. The United States, Russia,

and China have operational MRBM warfare systems. Other nations,

including India, Pakistan, Iran, Israel and North Korea, may have

MRBMs, but not organized systems. Some examples of American

MRBMs include Atlas, Titan, Minuteman and Peacekeeper. Recently,

2

M R B M

American Titan and Minuteman MRBMs, and Russian SS-9 Cyclone

MRBMs, have been converted into space rockets. 

SLBM is a submarine launched ballistic missile that can deliver a

nuclear weapon payload. An example of an SLBM is the United States'

Trident intercontinental ballistic missile, which is armed with nuclear

warheads and launched from submarines. Russia's Shitl space rocket

was derived from the SS-N-23 SLBM. 

Type Range Examples

MRBM 700 – 1,200 km Agni-I, CSS-5,No-dong

IRBM 2,000 – 2,500 km Agni-II, CSS-2

IRBM 3,000 – 5,000 km Agni-III,

IRBM 3,200 – 3,700  km Agni-IV

MRBM 5,000-6,000 km (under development). Agni-V,  SS-5

MRBM6,000-10,000 km (speculated to be under development)

Agni-VI ,NKSL-X-2

3

M R B M

3. FUEL TECHNOLOGY

SOLID FUEL TECHNOLOGY AND LIQUID FUEL TECHNOLOGY:

The single-stage , liquid-fueled, road mobile, nuclear-capable ballistic missile.

It could carry a 1,000 kg payload 1,300 km. while a single-stage, liquid-

fueled, submarine-launched ballistic missile with a range of 2,400 to 3,000 km

and the ability to carry a nuclear warhead.

The liquid-fueled rocket with a diameter of about 1.25 meters, which is

sufficient to accommodate a nuclear warhead can exploit low-thrust rocket

motors to build a two-stage rocket, and qualified engineers who are able to

make good use of the technology that is available to them.serve as a testbed

for long-range ballistic missile technologies.The Safir could be modified with a

different upper rocket stage so that it could carry a warhead weighing roughly

1,000 kg to a range of about 2,000 km.

Fig 1.1 First stage nozzle.

The solid fuel propellant weighs ~4,200 kg . 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. The solid fuel second stage does not

require retro motors for proper stage separation. The solid fuels consist of

AP-Al-PBAN HTPB (hydroxyl-terminated polybutadiene),carbon and silica-

phenolic lining is used in the fore end and aft end of the divergent. The

propellant used in Agni-I consists of HTPB (hydroxyl-terminated

polybutadiene) solid propellant.

4

M R B M

First Stage: The booster motor is one meter in diameter and ten meters in

length. It has approximately 9 tons solid propellant. The stage features three

segments of propellant grain, with an internal star configuration 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 MRBM consists of the AP-Al-

PBAN composite propellant. All later Agni variants use HTPB (hydroxyl-

terminated polybutadiene). The propellant is of star configuration 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. 

Second Stage: which has two small engines. fuel of  TG-02/AK-20 (Xylidiene

+ Triethylamine/IRFNA+ NTO),It has 1.1 meter long vented interstage is light-

weight and ensures better vehicle control and reliable second stage

separation. The second stage mass is about 12 tonnes and length of 3.9

meters (including 0.8 m payload adapter). The stage currently employs

maraging steel case that could be later upgraded to composites to maximize

fuel mass fraction that is critical to realize long range, especially with lighter

payload. The second stag also employs flex nozzles to provide necessary in-

flight trajectory control.. The case material of the second stage is aluminium

alloy. The high energy solid fuel of the stage burns slowly for about 105

seconds using high expansion ratio nozzle making it a very efficient engine.

FIG 1.2 The second stage of missile with 3.57 tons of propellant.

5

M R B M

3.FLIGHT PHASES OF MRBM

The flight of a ballistic missile can be divided into three phases: boost phase,

cruise phase, and descent (terminal) phase. Boost phase begins with

the ignition of the missile's booster rocket. The booster lofts the missile at a

steep angle, imparting a high speed to the payload before burning out. The

payload and booster then separate, beginning the cruise phase. The spent

booster falls back to Earth while the payload, starting to lose speed, continues

to gain altitude. If the missile is sufficiently long-range, its payload rises above

the Earth's atmosphere during cruise phase, where it jettisons

its aerodynamic protective shroud and arcs under the influence of gravity. The

payload may be a single cone-shaped warhead or a flat "bus" with several

warheads attached to it like upside-down icecream cones arranged circularly

on a plate.

Boot phase :The booster rockets of early ballistic missiles were

powered by liquid fuels. A liquid-fuel rocket carries fuel (hydrazine,

liquid hydrogen, or other) and liquid oxygen in tanks. Pressurized

streams of fuel and oxygen are mixed and ignited at the top of a bell-

shaped chamber: hot, expanding gases rush out of the open end of the

bell, imparting momentum to the rocket in the opposite direction. Liquid

fuels are unwieldy, as they must be maintained at low temperatures

and may leak fuel or oxygen from tanks, pipes, valves, or pumps. 

(shorter for a solid rocket than for a liquid-propellant rocket); altitude at

the end of this phase is typically 150 to 400 km depending on the

trajectory chosen, typical burnout speed is 7 km/s.

Cruise phase: approx. 25 minutes—sub-orbital spaceflight in an elliptic

flightpath; the flight path is part of an ellipse with a vertical major axis;

the apogee (halfway through the midcourse phase) is at an altitude of

approximately 1,200 km; the semi-major axis is between 3,186 km and

6,372 km; the projection of the flightpath on the Earth's surface is close

to a great circle, slightly displaced due to earth rotation during the time

of flight; the missile may release several independent warheads,

6

M R B M

and penetration aids such as metallic-coated balloons, aluminum chaff,

and full-scale warhead decoys.

Descent (terminal) phase: (starting at an altitude of 100 km) 2

minutes—impact is at a speed of up to 4 km/s (for early MRBMs less

than 1 km/s)

Figure 1.3

7

M R B M

3.ACCURACY

The MRBM 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. By using navigation sensors and flight control

through its space program. The placement accuracy in GTO (involving

powered flight of 1,000 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 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:

1. Small velocity correction thruster package and/or

2. 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

8

M R B M

LOS (line of sight) well beyond apogee. The overall accuracy is the cumulated

sum of:

1. Accuracy of determining geographic coordinate of target and launcher.

2. 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.

9

M R B M

4.How MRBM’s are tracked

The National Missile Defence (NFD) has setup five parts to the working of this

missile launch and target delivery system.They are being classified as:

Upgraded Early-warning Radar (UEWR)

X-band/Ground-based Radar(XBR)

Space-based Infrared System(SBIRS)

Battle Management, Command, Control and

Communications (BMC3)

Ground-based Interceptors (GBIs)

The first part of NMD will involve detecting the launch of enemy missiles and

tracking them. Data gathered by a system of radar and satellites will be sent

back to personnel at the BMC3, who then will take appropriate action. Let's

take a look at the three components that make up the detection and tracking

system of NMD.

Upgraded Early-warning Radar (UEWR) :

This is a  phased-array surveillance radar that can detect and track ballistic

missiles. NMD will use upgraded versions of existing, ultra-high frequency

early-warning radar. Hardware modifications, including the replacement of

existing computers, graphic displays, communications equipment and the

radar receiver/exciter, will also be made to the EWR. UEWRs will be used to

detect and track missiles and other projectiles during their midcourse phase,

before cueing the more precise X-Band Radar.

10

M R B M

X-band/Ground-based Radar (XBR) :

This consists of a multi-function phased array radar that uses high

frequency and advanced radar-signal processing technology. The XBR will

track missiles as they fly closer to the United States and assess which

missiles are decoys and which are armed with warheads. It is equipped with

high-resolution radar that allows it to accurately discriminate between closely

spaced objects. XBR radar has a 50-degree field of view and can rotate 360

degrees to track targets. It will transmit a radiation pattern in a narrow beam

made up of electromagnetic pulses. The radar site consists of the X-band

radar mounted on a pedestal, a control and maintenance facility, a power

generation facility and a 492-foot (150-m) protected area. The XBR site will

cover 17.46 acres.

Figure 1.3

11

M R B M

Space-based Infrared System (SBIRS) :

Under development by the Air Force, the SBIRS satellites are on a 10-year

development plan and are expected to be added to the system three to four

years after NMD becomes operational. These satellites will replace the

current Defense Support Program (DSP) satellites. There are three kinds of

SBIRS satellites, including four geostationary earth orbit (GEO) satellites,

twohighly elliptical orbit (HEO) satellites and an unspecified number of low

earth orbit (LEO) satellites. Eventually, there will be a 24-satellite

constellation that will start tracking enemy missiles earlier than radar, allowing

for quicker response.

Figure 1.5

12

M R B M

Technical Specifications of Indian MRBM

Weight 12,000 kg (Agni-I)

16,000 kg (Agni-II)

48,000 kg (Agni-III)

49,000 kg (Agni-V)

Length 15 m (Agni-I)

21 m (Agni-II)

17 m (Agni-III)

17.5 m (Agni-V)

Diameter 1.0 m (Agni-I, Agni-II)

2.0 m (Agni-III)

Warhead Strategic nuclear (15 KT to 250 KT), conventional HE-unitary, penetration, sub-munitions, incendiary, or

fuel air explosives

Engine Single stage (Agni-I)

Two-and-half-stage (Agni-II)

Two stage (Agni-III) solid propellant engine

Operationalrange 700-1,200 km (Agni-I)

2,000-3,500 km (Agni-II)

3,500-5,000 km (Agni-III)

Over 5,500 km (Agni-V)

Flight altitude 300 km (Agni-I)

230 km (Agni-II)

350 km (Agni-III)

Speed 2.5 km/s (Agni-I)

3.5 km/s (Agni-II)

Guidancesystem Ring laser gyro-INS (inertial navigation systemm), optionally augmented by GPS terminal guidancewith

possible radar scene correlation

13

M R B M

6.List of ICBM’s by Country

  Soviet Union   /     Russia Specific types of Soviet ICBMs include:

Active

R-36 SS-9 Scarp R-36M2 Voevoda / SS-18 Satan UR-100N 15A30 / SS-19 Stiletto RT-2PM Topol / 15Zh58 / SS-25 Sickle RT-2UTTKh Topol M / SS-27 / RS12M1 / RS12M2 / RT2PM2 RS-24: MIRV-equipped.

  United States

Active

Minuteman III (LGM-30G): launched from silo—as of May 2009, there are 450 Minuteman III missiles in active inventory

Trident (UGM-93A/B) SLBM: Trident II (D5) was first deployed in 1990 and is planned to be deployed past 2020 (11,300 kilometres (7,000 mi) range).

  India

Although, India is believed to have capped the Integrated Guided missile

development programme at a maximum range of 5,500 km, there are reports

claiming that DRDO is covertly working to develop multiple longer

range ICBMs to boost its nuclear deterrence against more distant countries.

India's former Air Chief Marshal P.V. NAIK contended, “India needs the

capability to match its sphere of influence” as the country's sphere of influence

grows.

Agni-V (5,000–6,000 km) Agni-VI (6,000-10,000 km) [Speculated; final decision about the

range is yet to be taken]

14

M R B M

Surya (10,000-16,000 km) [Speculated][5]

  People's Republic of China

DF (Dong Feng or East Wind) are land-based. JL (Ju Lang or Giant Wave) are submarine-

launched.

DF-4  (CSS-3): 1975, silo-based, 5,500 km

DF-4  improved (CSS-3): 1975, silo-based, 7,000 km

DF-5  (CSS-4): 1981, silo based, 13,000 km

DF-5A  (CSS-4): 1983, road-mobile, 15,000 km

15

M R B M

5.Modern MRBM’s

Modern MRBMs typically carry multiple independently targetable re-entry

vehicles (MIRVs), each of which carries a separate nuclear warhead, allowing

a single missile to hit multiple targets. MIRV was an outgrowth of the rapidly

shrinking size and weight of modern warheads and the Strategic Arms

Limitation Treaties which imposed limitations on the number of launch

vehicles (SALT I and SALT II). It has also proved to be an "easy answer" to

proposed deployments of ABM systems—it is far less expensive to add more

warheads to an existing missile system than to build an ABM system capable

of shooting down the additional warheads; hence, most ABM system

proposals have been judged to be impractical.

first operational ABM systems were deployed in the U.S. during

1970s. Safeguard ABM facility was located in North Dakota and was

operational from 1975–1976. The USSR deployed itsGalosh ABM system

around Moscow in the 1970s, which remains in service. Israel deployed a

national ABM system based on the Arrow missile in 1998,[13] but it is mainly

designed to intercept shorter-ranged theater ballistic missiles, not MRBMs.

The U.S. Alaska-based National missile defence system attained initial

operational capability in 2004.

first operational ABM systems were deployed in the U.S. during

1970s. Safeguard ABM facility was located in North Dakota and was

operational from 1975–1976. The USSR deployed itsGalosh ABM system

around Moscow in the 1970s, which remains in service.

Israel deployed a national ABM system based on the Arrow missile in

1998, but it is mainly designed to intercept shorter-ranged theater ballistic

missiles, not MRBMs.

16

M R B M

Figure 1.6

The U.S. Alaska-based National missile defence system attained initial

operational capability in 2004.

MRBMs can be deployed from TELs such as the RussianTopol.

MRBMs can be deployed from multiple platforms:

in missile silos, which offer some protection from military attack

(including, the designers hope, some protection from a nuclearfirst

17

M R B M

strike)

on submarines: submarine-launched ballistic missiles (SLBMs);

most or all SLBMs have the long range of MRBMs (as opposed to

IRBMs)

on heavy trucks; this applies to one version of the RT-2UTTH Topol

M which may be deployed from a self-propelled mobile launcher,

capable of moving through roadless terrain, and launching a missile

from any point along its route

mobile launchers on rails; this applies, for example, to РТ-23УТТХ

"Молодец" (RT-23UTTH "Molodets"—SS-24 "Sсаlреl")

The last three kinds are mobile and therefore hard to find.

During storage, one of the most important features of the missile is its

serviceability. One of the key features of the first computer-controlled MRBM,

the Minuteman missile, was that it could quickly and easily use its computer to

test itself.

In flight, a booster pushes the warhead and then falls away. Most modern

boosters are solid-fueled rocket motors, which can be stored easily for long

periods of time. Early missiles used liquid-fueled rocket motors. Many liquid-

fueled MRBMs could not be kept fuelled all the time as the cryogenic liquid

oxygen boiled off and caused ice formation, and therefore fueling the rocket

was necessary before launch. This procedure was a source of significant

operational delay, and might allow the missiles to be destroyed by enemy

counterparts before they could be used. To resolve this problem the British

invented the missile silo that protected the missile from a first strike and also

hid fuelling operations underground.

Once the booster falls away, the warhead continues on an unpowered ballistic

trajectory, much like an artillery shell or cannon ball. The warhead is encased

in a cone-shaped reentryvehicle and is difficult to detect in this phase of flight

as there is no rocket exhaust or other emissions to mark its position to

defenders. The high speeds of the warheads make them difficult to intercept

and allow for little warning striking targets many thousands of kilometers away

18

M R B M

from the launch site (and due to the possible locations of the submarines:

anywhere in the world) within approximately 30 minutes.

Land-based MRBMs

Only Russia, the United States and China are currently known to possess

land-based MRBMs.

The United States currently operates 450 MRBMs in three USAF bases. The

only model deployed is LGM-30G Minuteman-III.

All previous USAF Minuteman II missiles have been destroyed in accordance

with START, and their launch silos have been sealed or sold to the public. To

comply with the START II most U.S. multiple independently targetable re-

entry vehicles, or MIRVs, have been eliminated and replaced with single

warhead missiles. The powerful MIRV-capable Peacekeeper missiles were

phased out in 2005.

Recent Updation in MRBM’s

However, since the abandonment of the START II treaty, the U.S. is said to

be considering retaining 800 warheads on an existing 450 missilesChina has

developed several long range MRBMs.

India has recently inducted the Agni 3 which has a range of 5000km. It is said

that Agni 3 can go as much as 6000km with decreased payloads.

Israel is suspected of deploying the nuclear armed Jericho 3 MRBM.

19

M R B M

8. CONCLUSION

This report has given an in depth knowledge about MRBM’s and their

contributions to the nation’s security, its working principle and basic ideas

about a ballistic missile. Moreover an MRBM is a weapon used for mass

destruction during wars . However its usage and operation depends upon

the nation how it handles during wartime .

MRBM’s are in their infancy and new ideas and technologies will surface in

the upcoming years leading to better technologies and range of the target like

India’s Agni II and Agni III which is stepping its foot for a better operation in

future. At the same time as MRBM’s are getting more advanced, it should be

handled with utter care and it shouldn’t be misused lest will create a havoc.

Finally let’s hope that such a advancement in technology will be used to

restore the peace and prosperity of the world and not to give the world a

devastating end.

20

M R B M

REFERENCES

[1] Lance Spitzner, “M R B M Tracking Hackers”, 2003, Pearson Education, Inc

[2] Reto Baumann and Christian Plattner, “White Paper: M R B M”, 26 February 2002URL: http://en.wikipedia.org/wiki/Intercontinental_ballistic_missile#Flight_phases

[3] Lance Spitzner, “M R B M Definition and Value of M R B M”, 17 May, 2002, URL:http://www.enteract.com/~lspitz/M R B M.html

[4] Kurt Seifried, “M R B Mting with VMWARE – basics”, 15 February 2002, URL:http://www.seifried.org/security/ids/20020107-M R B M-vmware-basics.html

[5] Honeynet Project, “Know Your Enemy: Defining Virtual Honeynets, Different types of “Virtual Honeynets”, 18 August 2002, URL: http://www.honeynet.org/papers/virtual/

[6] Michael Clark, “Honeynets”, 7 November 2001, URL:http://online.securityfocus.com/infocus/1506/

21