The document discusses missile launching systems and control systems concepts. It begins with an overview of missiles and their components like guidance systems and propulsion. It then describes the key parts of a missile launching system, including the loader, assembler, and launching system control. Finally, it covers concepts like impulse response and bounded-input bounded-output (BIBO) stability, noting that a system is BIBO stable if the impulse response is absolutely integrable and poles have negative real parts. The document provides examples and diagrams to illustrate missile systems and stability analyses.

1. RAGHU ENGINEERING COLLEGE
(AUTONOMOUS)
DEPARTMENT OF EEE
Academic year: 2018-2019
II year II-semester
Control Systems
CASE STUDY
ON
MISSILE LAUNCHING SYSTEM .
BATCH-2
A.Snehitha-18985A0206
A.S.S.R.Murthy-18985A0207
A.Sai Sampath-18985A0208
B.Naga Venkatesh-18985A0209
B.Chaitanya-18985A0210
FACULTY:
K.Sulochana
Assistant Professor.
19-04-2019 Control Systems 1

2. Missile
In modern language, a missile, also known as a guided missile, is a guided self-
propelled system, as opposed to an unguided self-propelled munition, referred to
as a rocket (although these too can also be guided).
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3. More About Missiles
 The word missile is derived form Latin verb which means ‘to send.’
 They are basically rockets but used for only destructive purposes, the only
difference is that missiles have a guidance system which rockets doesn’t.
 Aside from explosives other possible types of missile payloads are various forms
of chemical and biological agents, nuclear warheads or some kinetic energy.
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Fig A: Astra MK-1 Missile
Astra is an all weather beyond-visual-range air-to-air missile developed by
the DRDO, India.

4. Missile Components
Guided missiles are made of series of subassemblies. The major
sections are carefully connected together. The major components of a
missile are as follows:
1. War head.
2. Fusing
3. Guidance system.
4. Propulsion system.
5. Fins.
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Fig B: Showing basic structural parts of a guided missile

5. Principle Of Working
 The working of a missile can be explained using newton’s third law,
the propulsion of the missile can be achieved with the help of rocket
engine which produces thrust by ejecting hot gaseous matter called
as propellant.
 This propellant is exhausted via nozzle at a high speed which causes
the missile to move in opposite direction.
 To target the missile using of a guidance system such as GPS, INS,
TERCOM or can be done by a human operator.
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6. Missile Launching System
 Its purpose is to deliver a missile, ready for firing, from the missile
magazine to the launcher guide arm.
 The launching system includes the feeder system, the launcher, and
the launching system control.
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FIG C: Mark13 Missile launcher.
Fig D: Missile launching
system MK10

7. Launcher
 The main purpose of a launcher is to provide a launching platform or
pad for missiles.
 They have secondary purposes too i.e., to support, aim and launch a
missile.
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Fig E: Multiple missile launcher
from L&T.

8. Modern Missile Launchers
 Its ability to position itself in train and elevation.
 A structure that can support missiles singly or in pairs.
 Devices that provide a method of inserting information into the
missile before it is fired.
 Devices that fire the missile.
 Systems that provide for the safety of the ship, missile, and
personnel.
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9. Missile Launching
System- MK12
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Fig G: Structural view of MK12Fig F: Picture of MK12

10. Loader
It is sometimes called as rammer,
It picks up the missile after it has
been brought up from the
magazine, moves it to the assembly
area, where the wings and fins are
attached.
Then the missile is moved to
launcher, there is no need of
lengthy transfer as the launcher is
located next to rammer.
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Fig H: Loader of MK12 missile launcher.

11. Assembler
 The assembly area is in the missile
house, near the launcher.
 The wings and fins that are to be
attached to the missiles are stored in
racks in this area.
Men are stationed here and they
attach a wing or fin to the missile as it
rests on the loader.
It must be done very quickly to
maintain the timing sequence of the
launcher, and the men must have had
precision- timed training before they
are assigned to the task
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Fig I: Assembler Perspective view.

12. Launching System Control
 The control panels for components are located as close to the
component as possible.
 The large control panel offers automatic control, but local control is
necessary for testing, checking, repairing, or replacing individual units
of components.
The launcher is controlled by the following five methods: remote
control, local control, dud jettison control, load-order control, and
test control. These are also called modes of operation.
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13. Conclusion
Not only the above mentioned parts, there are many elevation
systems and train systems to perform the missile launch process.
We are concluding that this modern missile launching system
comprises many open loop and closed loop control system in various
assemblies.
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14. RAGHU ENGINEERING COLLEGE
(AUTONOMOUS)
DEPARTMENT OF EEE
Academic year: 2018-2019
II year II-semester
Control Systems
CASE STUDY
ON
SIGNIFICANCE OF IMPULSE RESPONSE AND DETREMINATION OF BIBO STABILITY .
BATCH-2
A.Snehitha-18985A0206
A.S.S.R.Murthy-18985A0207
A.Sai Sampath-18985A0208
B.Naga Venkatesh-18985A0209
B.Chaitanya-18985A0210
FACULTY:
K.Sulochana
Associate Professor.
19-04-2019 Control Systems 14

15. Impulse Response.
 An impulse response means the output/behavior of a system when
we provide it with an impulse signal. An impulse signal is a
momentary signal of infinite magnitude (ideally).
 The Laplace transform of an impulse function is 1, so the impulse
response is equivalent to the inverse Laplace transform of the
system's transfer function, for an LTI system.
 In other words, for an unknown system, its impulse response can help
us understand the system as for any input to a system, the output can
be calculated.
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16. Significance of Impulse Response.
 The Fourier transform of the impulse response is the transfer
function of the system, i.e. a function that outlines the behavior of
the system at all frequencies.
 Any input signal can be constructed from delayed and scaled
impulses, so it is easy to work out what your system response will be
to more complicated input signals.
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17. Let,
T(s) be the closed loop transfer function of the system.
c(s) be response of the system in s domain.
r(s) be the input in s domain.
m(s) be the impulse response of the system.
m(s) = c(s)/r(s);
m(s).r(s) = c(s) ………(1)
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Impulse Response of a system.

18. r(s) = 1 ; r(t) = δt ; where L{r(t)} = 1 = r(s).
from equation…..(1),
c(s) = m(s).1
c(s) = m(s) ………(2)
applying inverse Laplace,
c(t) = m(t).r(t)
Where convolution operation can be mathematically defined as,
Where, τ is a dummy variable used for integration.
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c(t) = −∞
∞
𝑚(τ).r(t-τ)dτ

19. BIBO Stability.
 In signal processing, specifically control theory, bounded-input,
bounded-output (BIBO) stability is a form of stability for linear signals
and systems that take inputs. If a system is BIBO stable, then the
output will be bounded for every input to the system that is bounded.
 A continuous-time linear time-invariant system is BIBO stable if and
only if all the poles of the system have real parts less than 0.
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20. BIBO Stability in detail.
 A bounded signal is any signal such that there exists a value such that
the absolute value of the signal is never greater than some value.
 Since this value is arbitrary, what we mean is that at no point can the
signal tend to infinity, including the end behavior.
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Fig A : picture showing a bounded
signal.

21. Time Domain conditions for BIBO Stability.
 We must turn our attention to the condition a system must possess
in order to guarantee that if any bounded signal is passed through the
system, a bounded signal will arise on the output. It turns out that a
continuous-time LTI system with impulse response h(n) is BIBO stable
if and only if it is absolutely summable.
 Discrete- time condition for BIBO stability:
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−∞
∞
ℎ 𝑛 < ∞

22. BIBO Stability In Terms of Impulse Response.
Consider a linear relaxed system i.e., with no initial conditions.
Where,
m(t) is impulse response of the system,
r(t) is input of the system in time domain,
c(t) is response of the system in time domain,
We know that,
c(t) = −∞
∞
𝑚(τ).r(t-τ)dτ;
r(t) = A1 < ∞; r(t-τ) = A1 < ∞
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23. |c(t)| = | 0
∞
𝑚(τ).r(t-τ)dτ|
|c(t)| = 0
∞
|m(τ).r(t−τ)dτ| …………(3)
|c(t)| = A1
0
∞
|𝑚 τ 𝑑τ|
|c(t)| < A2 < ∞
A2 = A1
0
∞
|𝑚 τ 𝑑τ| ………….(4)
From equation…(4),
0
∞
|𝑚 τ 𝑑τ| < A3 < ∞
Therefore, the condition for BIBO stability comes as
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0
∞
|𝑚 τ 𝑑τ| < A3 < ∞

24. Location of Poles on s-
Plane for Stability.
 The closed loop transfer
function m(s) can be
represented as ratio of two
polynomials:
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25.  The impulse response is given by
inverse Laplace of m(s).
 The inverse Laplace of each term
depends on the location of roots on s-
plane.
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Conclusion
 By observing the above cases we
came to conclude that, for a system to
be stable the area under the impulse
response should be absolutely
integrable.