1. NAME-RAJIB KUMAR BEHERA REGD. NO.-0801221084 SEMESTER,BRANCH:-- 7 TH SEM,MECHANICAL ENGG.

2. PLAN OF PRESENTATION 1.OBJECTIVE OF TOPIC 2.INTRODUCTION 3.TECHNICAL HISTORY 4.WORKING PRINCIPLE 5.ADVANTAGES6.DISADVANTAGES7.CONCLUSION8.BIBLIOGRAPHY

3. OBJECTIVE OF TOPIC  By Geo Satellite Launch Vehicle we can research that how a satellite is placed in space station.  To study the behavior of earth and space property.  To develop the future research programs of space.  To take part in space research competition with other country.

4. INTRODUCTION  A Geo Satellite Launch Vehicle is a vehicle by which we can place a satellite in space station.  Geo Satellite Launch Vehicle (GSLV) operates mainly in three stages, namely first stage, second stage & third stage (upper stage).  We employ these three stages in GSLV because here we have to work against earth gravity to place a satellite in space station, which is 22,300Miles from the earth surface.  The above three stages work one by one, when previous one will be complicated.  Generally GSLV used to place any type of satellite in space station.

5. TECHNICAL HISTORY  The Geosynchronous Satellite Launch Vehicle (GSLV) project was initiated in 1990 with the objective of acquiring launch capability for geo satellites. Until then, India depended on the former Soviet Union for the launch of heavy satellites.  Flight D1, launched on 18 th April, 2001 from first launch pad of pay load GSAT 1 of mass 1540kg, which is successful.  Flight F02, lunched on 10 th July,2006 from second lunched pad of pay load INSAT 4C of mass 2168kg, which failed &the rocket and satellite had to be destroyed on Bay Of Bengal.

7. First stage:-  The first stage is relatively simple. Besides the engine, the fuel, and the oxidizer tanks, a center body section lies between the fuel and the liquid oxygen tank. This center body section houses electronic equipment to implement commands from the second stage where the rocket's brains reside.  Once the spacecraft launches off the pad, the first stage engine needs more and more fuel to keep accelerating. A turbine-turbo pump pushes fuel and oxygen into the combustion chamber. Liquid oxygen is also used to keep the main engine and its nozzle from getting too hot and overheating

8. Contd…..  Two small precision engines provide roll control during main engine burn and attitude control after main engine cutoff before the second stage separation. If the rocket sensors detect that the rocket is starting to spin or roll, the engines will fire to stop the rotation.  In order to make adjustments to the flight path, the engine is moved back and forth from the bottom of the rocket on large, straight gimbals by a fluid under pressure

9. Second stage:-  The second stage of the GSLV is powered by an Aerojet AJ10-118K engine, which burns a combination of Aerozine 50 (a 50/50 mix of hydrazine and dimethyl-hydrazine) and nitrogen tetroxide (N2O4) oxidizer. These fuels burn automatically when mixed, without a need for any lighters or igniters.  Stage II is restart able, and fires twice. The first burn occurs during the final portion of the boost phase and is used to insert the second and third stage spacecraft stack into a low Earth orbit. The second stage is programmed to shut itself off once the rocket and spacecraft are in orbit around Earth.

10. Contd……  The rocket and spacecraft orbit Earth until it arrives at just the right spot that line up on the correct path to depart for Mars. Once the spacecraft is at the right angle, the second stage engine re-fires. This short re-firing of the second stage engine provides the final alignment and velocity for the third stage.  To keep the spacecraft in the right position, the second stage engine, like the first stage engine, slides back and forth on large, straight gimbals through hydraulic pressure.

11. Third stage:-  The upper stage of the launch vehicle is connected to the satellite itself, which is enclosed in a metal shield, called a “fairing.”  The fairing protects the satellite while it is being launched and makes it easier for the launch vehicle to travel through the resistance of the Earth's atmosphere.  The fairing splits apart once the satellite is above the Earth's atmosphere and burns up in the Earth's atmosphere.  The rockets of the upper stage fire after the satellite is in space and put the satellite in the exact spot where it is needed.

12. Contd…..  Third stage motor uses approximately 2,020 kilograms (4,453 pounds) of solid propellant that is composed primarily of ammonium perchlorate and aluminum.  This propellant produces an average of 66,000 Newton's thrust.

13. ADVANTAGES  GSLV helps in placing any satellite in space station easily.  At the time of launching, if GSLV fail to place the satellite in space station & destroyed then it does not affect to people or buildings.  GSLV helps us for future space research programming.

14. DISADVANTAGES  It has high cost project.  If after lunching any problem will occur in GSLV, then it can’t be repaired.  This project takes long time.  The used parts are dropped into sea, so there is a chance of water pollution.  For this project specific places are required.

15. CONCLUSION  Recent researches are going on to minimize the high cost & to increase the % of success in launching.  Through GSLV project we can got some extra knowledge about property &behavior of earth. And also it can help us to study the property & behavior of space.

16. BIBLIOGRAPHY  Solid Rocket Booster Instrumentation Program and Components List, Report No. 16A00103,  Marshall Space Flight Center, AL, March 15, 1983.  SSME Flight Measurement Location Document, Revision D, Rockwell International,  Rocket dyne Division, Canoga Park, CA, May 1991.  Critical Design Review of Eaton SSME Pressure Transducer, Rockwell Aerospace, January31, 1995.  Space Station Furnace Facility Metrology Plan, NASA/MSFC Astrionics Laboratory, November 1996.  ISRO.