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Satellite Launching
Made By- Presented By-
Chiranjeeve Bansal Richa Agarwal
Shivangi Tyagi
Nidhi Pandey
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What is a Satellite?
According to Wikipedia, In the context ofspaceflight, a Satellite is an object which has beenplaced into orbit by human endeavor. Such
objects are referred as artificial satellites todistinguish them from natural satellites.
Technically, Satellites are usually semi-independent computer controlled systems.
Satellite sub systems attend many tasks, such aspower generation, thermal control, telemetry,attitude control and telemetry.
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BRIEF HISTORY
History changed on October 4, 1957, when the Soviet Union successfully
launched Sputnik I. The world's first artificial satellite was about the size of a
basketball, weighed only 183 pounds, and took about 98 minutes to orbit the
Earth on its elliptical path.
The Sputnik launch also led directly to the creation of National Aeronauticsand Space Administration (NASA). In July 1958, Congress passed
the National Aeronautics and Space Act(commonly called the "Space Act"),
which created NASA as of October 1, 1958 from the National Advisory
Committee for Aeronautics (NACA) and other government agencies.
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SATELLITE LAUNCHING
If you threw a baseball from the
mountain top, it would fall to the
ground in a curving path. Two
motions act on it: trying to go in a
straight line and falling towardEarth. The faster you throw the
ball, the farther it will go before it
hits the ground.
If you could throw the ball at a
speed of 17,000 mph, it would
never reach the ground. It would
circle the Earth in a curved path,
otherwise known as orbit. (It would
be traveling at 5 miles per second
and take about ten minutes to
cross the United States.) This is the
speed needed to put satellites into
orbit, which is why the Space
Shuttle and other satellites havesuch powerful boosters.
To place a satellite into a stable
orbit, 2 parameters need to be
perfectly coupled together-1. Velocity Vector
2. Orbital Height
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STAGES OF SATELLITE
LAUNCHING
Lift-Off
Roll/1st Stage Separation/ 2nd Stage Ignition
Payload Fairing Jettison 2nd Stage Separation/ 3rd Stage Ignition
3rd Stage Separation
4th Stage Roll/ Align
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LIFT-OFF STAGE Liftoffis the first moment of flight of a plane,
a rocket or other space launch vehicle, when itleaves the ground.
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1STSTAGE SEPARATION
After 21 seconds of launch Roll of satellite
takes place.
After 2 Mins and 7 seconds, the 1st
stageseparation takes place in which the lower part
gets separated from the satellite.
The Figure in next slide shows the 1st stage
separation of Apollo 11 Saturn 5.
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PAYLOAD FAIRING JETTISON
The standard payload fairing is typically a cone-cylinder
combination, due to aerodynamic considerations, however
specialized fairing are in use as well. The type of fairing which
upon jettisoning separates into two halves is called a clamshell
fairing by way of analogy to the bifurcating shell of a clam.
In some cases the fairing may enclose both the payload and the
upper stage of the rocket.
If the payload is attached both to the booster's core structures
and to the fairing, the payload may still be affected by fairing'sbending loads, as well as inertia loads due to vibrations caused
by gusts and buffeting.
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FAILURES CAUSED BY PAYLOAD
FAIRING The Augmented Target Docking Adapter was placed into orbit by an Atlas
SLV-3 in June 1966. When the Gemini 9Aspacecraft rendezvoused with it
in an attempt to dock, the crew discovered that the payload fairing was still
attached to the spacecraft, covering its docking port.
In 1999, the launch of the IKONOS-1 Earth observation satellite failed afterthe payload fairing of the Athena II rocket did not open properly.
The same happened to the Naro-1, South Korea's first carrier rocket,
launched on 25 August 2009. During the launch half of the payload's fairing
failed to separate, and as a result the rocket was thrown off course. The
satellite did not reach a stable orbit.
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STAGING AT A GLIMPSE
In serial or tandem staging schemes, the first stage is at the bottomand is usually the largest, the second stage and subsequent upperstages are above it, usually decreasing in size. In parallel stagingschemes solid or liquid rocket boosters are used to assist with lift-off.These are sometimes referred to as 'stage 0'. In the typical case, the
first stage and booster engines fire to propel the entire rocketupwards. When the boosters run out of fuel, they are detached fromthe rest of the rocket (usually with some kind ofsmall explosive charge) and fall away. The first stage then burns tocompletion and falls off. This leaves a smaller rocket, with the secondstage on the bottom, which then fires. Known in rocketry circles
as staging, this process is repeated until the final stage's motor burnsto completion.
In some cases with serial staging, the upper stage ignites before theseparation- the interstage ring is designed with this in mind, and thethrust is used to help positively separate the two vehicles.
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ADVANTAGES OF STAGES
The main reason for multi-stage rockets and boosters is that once the fuel is
burned, the space and structure which contained it and the motors
themselves are useless and only add weight to the vehicle which slows down
its future acceleration. By dropping the stages which are no longer useful, the
rocket lightens itself. A further advantage is that each stage can use a different type of rocket
motor each tuned for its particular operating conditions. Thus the lower
stage motors are designed for use at atmospheric pressure, while the upper
stages can use motors suited to near vacuum conditions.
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DISADVANTAGES
Staging requires the vehicle to lift motors which are not
being used until later, as well as making the entire
rocket more complex and harder to build. In addition,
each staging event is a significant point of failure duringa launch, with the possibility of separation failure,
ignition failure, and stage collision. Nevertheless the
savings are so great that every rocket ever used to
deliver a payload into orbit had staging of some sort.
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POLAR SATELLITE LAUNCH
VEHICLE
The Polar Satellite Launch Vehicle, commonly known by its
abbreviation PSLV, is an expendable launch system developed
and operated by the Indian Space Research
Organization (ISRO).
It was developed to allow India to launch its Indian Remote
Sensing (IRS) satellites into sun synchronous orbits, a service
that was, until the advent of the PSLV, commercially viable only
from Russia. PSLV can also launch small size satellites
into geostationary transfer orbit (GTO).
The PSLV has launched 41 satellites (19 Indian and 22 from
other countries) into a variety of orbits till date.
PSLV costs 17 million USD flyaway cost for each launch.
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PSLV-C8 (CA Variant) carrying the AGILE x-ray
and -ray astronomical satellite of the ASI lifting
off from Sriharikota
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VEHICLE DESCRIPTION
The PSLV has four stages using solid and liquid propulsion systems
alternately. The first stage is one of the largest solid-fuel rocket boosters in
the world and carries 138 tonnes ofHydroxyl-terminated
polybutadiene (HTPB) bound propellant with a diameter of 2.8 m.
The second stage employs the Vikas engine and carries 41.5 tonnes (40tonnes till C-5 mission) of liquid propellant Unsymmetrical Di-Methyl
Hydrazine (UDMH) as fuel and Nitrogen tetroxide (N2O4) as oxidizer.
The third stage uses 7 tonnes ofHTPB-based solid propellant and produces
a maximum thrust of 324 kN. It has a Kevlar-polyamide fiber case and a
submerged nozzle equipped with a flex-bearing-seal gimbaled nozzle (2)
thrust-vector engine for pitch & yaw control.
The fourth and the terminal stage of PSLV has a twin engine configuration
using liquid propellant.
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DEVELOPMENT
PSLV is designed and developed at Vikram Sarabhai Space
Centre (VSSC), Thiruvananthapuram, Kerala. The inertial systems are
developed by ISRO Inertial Systems Unit (IISU) at Thiruvananthapuram.
The liquid propulsion stages for the second and fourth stages of PSLV as
well as the reaction control systems are developed by the Liquid PropulsionSystems Centre (LPSC), also at Thiruvananthapuram. The solid propellant
motors are processed by Satish Dhawan Space Centre SHAR, which also
carries out launch operations.
After some delays, the PSLV had its first launch on 20 September 1993.
Although all main engines performed as expected, an altitude control
problem was reported in the second and third stages. After this initial
setback, ISRO met complete success with the third developmental launch in
1996.
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VARIANTS OF PSLV
Variants launches Successes Failures Partial Failures Remarks
PSLV(Standard) 10 8 1 1
PSLV-CA(Core
Alone)
6 6 0 0 Launched 10
Satellites in 1 go.
PSLV(Extended) 1 1 0 0 Launched
Chandrayaan-1
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REFERENCES
2.5 Launches & Launch Vehicle, Satellite
Communications 2nd Edition, Pratt, Bostian,
Allnutt
Slide Show by Mr. Manoj, Faculty, VCE.
Wikipedia.org
Octopus.gma.org Online Journal of Space Communication