GSLV satellites from 2001 to 2014

1. GSLV
(Geosynchronous Satellite Launch Vehicle)

2. 
Geosynchronous Satellite Launch
Vehicle (abbreviated as GSLV) is an expendable
launch system operated by the Indian Space
Research Organisation (ISRO)

It was developed to enable India to launch its
satellites indigenously without dependence on
foreign aid. GSLV has attempted eight launches to
date, since its first launch in 2001 through its most
recent launch in 2014

3. HISTORY



The Geosynchronous Satellite Launch Vehicle
(GSLV) project was initiated in 1990 with the
objective of acquiring an Indian government launch
capability for Geosynchronous satellites
India has depended on the United States and
Europe for the launch of INSAT class of satellites.[3]
GSLV uses major components that are already
proven in the Polar Satellite Launch Vehicle
(PSLV) launchers in the form of the S125/S139
solid booster and the liquid-fueled Vikas engine

4. MANAGING DIRECTOR (ISRO)

K.Radha krishnan

5. VEHICLE DESCRIPTION
The 49 metres (161 ft) tall GSLV, with a lift-off
mass of 415 tonnes (457 tons), is a threestage vehicle with solid, liquid and cryogenic
stages respectively
 The payload fairing, which is 7.8 metres
(26 ft) long and 3.4 metres (11 ft) in diameter,
protects the vehicle electronics and the
spacecraft during its ascent through the
atmosphere


6. LAUNCH HISTORY

All GSLV launches have been conducted
from the Satish Dhawan Space
Centre in Sriharikota.

7. GSLV-D1

8. GSLV-D1
 The
first developmental flight of Geosynchronous Satellite Launch
Vehicle, GSLV-D1, was successfully
carried out on April 18, 2001 from SHAR
Centre, Sriharikota
 Payload mass is 1,540 kg
 ISRO claims the launch to be
successful and claims GSLV-D1 as
failure

9. FEATURES OF GSLV D-1

The GSLV-D1 boasts of several unique
features. For the first time, a cryogenic
engine has been used on an ISRO vehicle.
Second, the 1,540-kg satellite (GSAT-1) is
the heaviest satellite to be carried by an
Indian-made satellite launch vehicle. The
GSLV-D 1 is to be followed by two more
developmental launches (GSLV-D2 and
GSLV-D3), which will progressively test with
increased payloads.

10. GSLV D-2

11. GSLV D-2
 GSLV-D2
is the second developmental
test flight of the vehicle. Successfully
launched on 8th May 2003 from SHAR
Centre, Sriharikota
 Payload mass is 1,825 kg
 ISRO claims GSLV D-2 as Successful
mission

12. FEATURES OF GSLV D-2

The GSLV-D2 features several improvements
over the GSLV-D1, which was sent up into
the space in April 2001. Importantly, the
rocket launched today carried a heavier
satellite-which weighed 1,800 kg, as
compared to the 1,540 kg of GSLV-D1. In
order to be able to carry a heavier
payload, the rocket carried more fuel and the
fuel was fired at a higher pressure. These
were the parameters that today's mission
wanted to put to test, and the result was a
complete success

13. GSLV-F01

14. GSLV-F01
GSLV-F01 is the third flight of ISRO’s
Geosynchronous Satellite Launch Vehicle
and this is the first operational flight launched
in 20th September 2004 from SHAR
Centre, Sriharikota.
 Payload mass is 1,950 kg
 ISRO claims GSLV-F01 as a Successful
mission


15. FEASTURES OF GSLV-F01

The Aluminum alloy GSLV payload fairing is 3.4
m in diameter and is 7.8 m long. GSLV employs
various separation systems such as Flexible
Linear Shaped Charge (FLSC) for the first
stage, pyro actuated collet release mechanism
for second stage and Merman band bolt cutter
separation mechanism for the third stage.
Spacecraft separation is by spring thrusters
mounted at the separation interface. The threeaxis attitude stabilisation of GSLV is achieved by
autonomous control systems provided in each
stage. Single plane Engine Gimbal Control
(EGC) of the four strap-ons of the first stage are
used for pitch, yaw and roll control.

16. GSLV-F02

17. GSLV-F02
GSLV-F02 launched INSAT-4C on July
10, 2006 from SHAR Centre, Sriharikota.
 Payload mass is 2,168 kg
 Both rocket and satellite had to be destroyed
over the Bay of Bengal after the rocket's
trajectory veered outside of permitted limits


18. GSLV-F02 CRASH

19. GSLV-F04

20. GSLV-F04
GSLV-F04 is the fifth flight of India's
Geosynchronous Satellite launch Vehicle
(GSLV) launched in 2nd September 2007 in
SHAR Centre, Sriharikota.
 Payload mass is 2,160 kg
 ISRO claims the mission to be Partially failure


21. FEATURES OF GSLV-FO4

The 49 m tall GSLV, with a lift-off mass of 415
tonne, is a three-stage vehicle with solid,
liquid and cryogenic stages. The first stage of
GSLV, one of the largest in the world, uses
Hydroxyl Terminated Polybutadiene (HTPB)
based propellant. The second stage and the
four strap-on motors surrounding the first
stage use liquid propellant 'Vikas' engine
burning UH25 and Nitrogen Tetraoxide. The
third stage is a cryogenic stage using liquid
Hydrogen as fuel and liquid Oxygen as
oxidiser.

22. GSLV-D3

23. GSLV-D3
The GSLV-D3 was the sixth flight of ISRO's
Geosynchronous Satellite Launch Vehicle
(GSLV) as well as its third developmental
flight. Launched in 15 April 2010 from SHAR
Centre, Sriharikota.
 Payload mass is 2,220 kg
 ISRO claims the mission to be unsuccessful


24. FEATURES OF GSLV-D3
 First
flight test of the ISRO designed
and built Cryogenic Upper Stage.
Failed to reach orbit due to
malfunction of Fuel Booster Turbo
Pump (FBTP) of the Cryogenic
Upper Stage

25. GSLV-F06

26. GSLV-F06
GSLV-F06 was the seventh mission of
Geosynchronous Satellite Launch Vehicle
(GSLV) launched in 25th December 2010
from SHAR Centre, Sriharikota.
 Payload mass is 2,130 kg
 Destroyed by range safety officer after loss
of control of liquid-fueled boosters


27. FEATURES OF GSLV-F06

The major changes incorporated in
compared to the previous flight include
loading of 15 tonnes of propellants in its third
stage and the uprating of the third stage
thrust by 26%. Besides, the overall length of
the vehicle was increased by about 1.3
metres.Hence the mission was unsuccessful.

28. GSLV-D5

29. GSLV-D5
GSLV-D5 is the eighth flight of India's
Geosynchronous Satellite Launch Vehicle
(GSLV). It is also the fourth developmental
flight of GSLV
 Payload mass is 1,980 kg
 This was the first successful flight of the
cryogenic stage which was developed
indigenously in India


30. FEATURES OF GSLV-D5
 Second
flight of GSLV with indigenous
cryogenic upper stage(CUS) developed
by ISRO’s Liquid Propulsion Systems
Centre (LPSC) was launched
successfully on 5 January 2014. It was a
launch with precision of 40 metres
(130 ft). All three stages of launch were
carried out successfully