Satellite Launching 1

8/8/2019 Satellite Launching 1

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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

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