The document discusses ballistic missiles, including their objective to deliver warheads to targets, how they work according to Newton's third law of motion, and their different types ranging from short to intercontinental range. It describes the key phases of flight for ballistic missiles including powered flight, free flight, and re-entry, as well as the guidance systems and phases during boost, mid-course, and terminal. The document also covers characteristics of ballistic missiles such as their long range capabilities and high speeds, as well as types of propellants including liquid, solid, and hybrid varieties.

2. OBJECTIVE
• Understanding the mechanism behind working of
a ballistic missile.
• Studying types of ballistic missiles missiles
• Understanding concept of ballistics

3. Ballistic missile
• Rocket with a warhead
• Follows a ballistic trajectory
• Delivers one or more warhead to a predetermined target
• Both guided and unguided
• Guided during relatively brief periods of flight
• Most of the trajectory is unpowered and governed by gravity and air
resistance if in atmosphere

4. PRINCIPLE
• Works on Newton’s 3rd law of motion
• Continuous Ejection of Hot Gases in one direction
causes a steady motion of rocket in opposite
direction
• Operates on Brayton Cycle

5. Types of Ballistic
•Battlefield short range ballistic
missiles [ 150 km]
•Short range ballistic missiles
[250-800 km]
•Medium range [800-2400]
•Intercontinental range ballistic
missiles[5500 km]

6. Flight of icbm
• Three parts:powered flight portion,free flight
portion &re entry phase
• For srbm, two phases of icbm are employed
• Launched from TELs,aircraft ,shi Ps ubmarines,
• When in space and no more thrust is
required,missile enters free flight
• For icbm ,highest altitude reached during free
flight is about 1200km

7. GUIDANCE SYSTEM
• can be compared to the human pilot of an airplane
• consists of an :
• ATTITUDE CONTROL SYSTEM
• maintains the missile in the desired attitude
• controls the missile in pitch, roll
• damps out fluctuations that tend to deflect the missile from its ordered flight
path
• FLIGHT CONTROL SYSTEM
• generate the orders to the attitude control system to maintain that path.

8. PHASES OF GUIDANCE
• 3 phases – boost, midcourse, terminal

9. BOOST PHASE
• Missiles are boosted to flight speed by booster
component of propulsion system
• Lasts from the time missile is launched until
booster burns up its fuel
• Missiles aimed in specific direction on orders
from fire control computer
• This establishes line of fire along which missile
must fly during boosted period
• At the end of boost , missile must be at pre-
calculated point
• Essential that it provides stability to missile

10. • Not always present; but when present it is
the longest in time & distance
• Changes may be needed to bring missile
onto desired course & to keep it on course
• Puts missile near target, from where reentry
phase takes over control
MID-COURSE PHASE

11. Re-Entry vechile phase
• after propulsive phase ,Missile typically aligns , inertially
stabilizes release a reentry vehicle on a trajectory towards a pre
selected target
• the exterior of the rv is protected from aero thermodynamic
heating by a T.P.S
• The aerodynamic shape configuration determines duration and
flight path of rv
• This, in turn, affects the vehicle systems complexity and the
heating loads on the payload.

12. CHARACTERISTICS
• have much longer range than would be possible for cruise missiles for
same size.
• can travel extremely quick along there flight path
• An ICBM can strike a target within a 10000km range in about 30 to 35
minutes
• With speeds of over 5000m/s , these are much harder to intercept than
cruise.
• High cost of production and maintenance
• Follows ballistic path , hence attack detectable during boost phase

13. Types of propellant
LIQUID PROPELLANTS-
Two separately stored liquid propellant to produce thrust.
• Cyrogenic- USES VERY COLD AND LIQUIFIED GASES AS FUEL (lh2)AND
OXIDISER. (lox)
• Distressing tendency to return to gaseous form unless kept supercool
makes them difficult to store for long periods of time
• Not much used in military rockets
• Hypergolic - COMPOSED OF A FUEL AND OXIDISER THAT IGNITE
WHEN THEY COME IN CONTACT WITH EACH OTHER.
• corrosive so special containers and facilities required

14. HYBRID PROPELLANT
• advantages of both liquid and solid rocket engines.
• consists of a combustion chamber , packed with a solid chemical, .
• two chemicals are hypergolic
• liquid chemical is injected into the combustion chamber
• ignition occurs and thrust is produced.
solid propellant
•combustion chamber tubes packed with a propellant that contains both fuel and
oxidizer blended together uniformly
•relatively stable therefore it can be manufactured and stored for future use
•. Solid propellants have a high density and can burn very fast
•insensitive to shock, vibration and acceleration

15. FUTURE AND LATEST DEVELOPMENTS
AGNI V1:
 ICBM TYPE
 NUCLEAR WARHEAD
 FOUR STAGE SOLID FUELED
 CAPABILITY TO BE LAUNCHED FROM SUBMARINES AND FROM LAND
BASED LAUNCHERS
 OPERATIONAL RANGE –( 8000-12000).
AGNI V:
 3 STAGE SOLID FUELED
 RANGE 5500 to 5800KM

16. THANK YOU