Geosynchronous Satellite Launch Vehicle is an expendable launch system operated by the
Indian Space Research Organisation. It was developed to enable India to launch its satellites
without dependence on foreign rockets and providers. GSLV has attempted eight launches
to date, since its first launch in 2001 through its most recent launch in 2014.
History The Geosynchronous Satellite Launch Vehicle
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. GSLV uses major components that are already
proven in the Polar Satellite Launch Vehicle launchers in the form of the S125/S139 solid
booster and the liquid-fueled Vikas engine. The third stage was procured from Russian
company Glavcosmos based on an agreement signed in 1991. Russia backed out of the deal after
US sanctions were imposed in May 1992. ISRO started the Cryogenic Upper Stage Project
in April 1994 and began developing its own cryogenic stage. Russia agreed to sell 7 cryogenic
stages and 1 ground mock-up stage instead of 5 cryogenic stages and the technology to
build the stages. The first development flight of GSLV Mk.I
was launched on 18 April 2001. The flight carrying GSAT-1 failed to reach the correct
orbit. Attempts to save GSAT-1 by using its own propulsion system to manoeuvre it into
the correct orbit were unsuccessful as it ran out of fuel several thousand kilometres
below geosynchronous orbit. The GSLV became operational after a second
development flight, which successfully placed GSAT-2 in 2003. In its first operational flight
in September 2004, GSLV launched EDUSAT - India's first dedicated satellite for educational
services. However, the second operational flight, GSlV-F02, conducted on July 10, 2006
did not succeed in placing the satellite INSAT-4C into orbit.
GSLV-F04 is the fifth flight of India's Geosynchronous Satellite Launch Vehicle, launched INSAT-4CR
satellite, into a Geosynchronous Transfer Orbit of 170 km perigee and 35,975 km apogee
with an orbital inclination of 21.7° with respect to the equator on September 2, 2007.
Subsequently, the satellite was manoeuvred into geostationary orbit using its own propulsion
system. Two launches in 2010 failed; the first, in
April 2010, was the first flight of the GSLV Mk.II, with an Indian-developed third stage
engine replacing the Russian engine used on earlier flights. The third stage failed to
ignite. The next launch, in December 2010, used the Russian engine, however the vehicle
went out of control during first stage flight and was destroyed by range safety.
GSLV-D5, launched on January 5, 2014, was the first successful flight of the GSLV Mark.II
using the indigenously developed cryogenic engine, the CE-7.5.
Vehicle description The 49 metres tall GSLV, with a lift-off mass
of 415 tonnes, is a three-stage vehicle with solid, liquid and cryogenic stages respectively.
The payload fairing, which is 7.8 metres long and 3.4 metres in diameter, protects the vehicle
electronics and the spacecraft during its ascent through the atmosphere. It is discarded
when the vehicle reaches an altitude of about 115 km.
GSLV employs S-band telemetry and C-band transponders for enabling vehicle performance monitoring,
tracking, range safety / flight safety and preliminary orbit determination. The Redundant
Strap Down Inertial Navigation System/Inertial Guidance System of GSLV housed in its equipment
bay guides the vehicle from lift-off to spacecraft injection. The digital auto-pilot and closed
loop guidance scheme ensure the required attitude manoeuvre and guide injection of the spacecraft
to the specified orbit. The GSLV can place approximately 5,000 kg
into an easterly low Earth orbit. With the GSLV Mk.I, using the Russian 12KRB upper stage,
with KVD-1 cryogenic rocket engine, GSLV can place 2,200 kg into an 18° geostationary
transfer orbit. The GSLV Mk.II uses an indigenous cryogenic engine, the CE-7.5 in the third
stage instead of the Russian cryogenic engine. Liquid boosters
The first GSLV flight, GSLV-D1 used the L40 engine. Subsequent flights of the GSLV used
high pressure engines in the strap-on boosters called the L40H. The GSLV uses four L40H liquid
strap-on boosters derived from the L37.5 second stage, which are loaded with 40 tons of hypergolic
propellants. The propellants are stored in tandem in two independent tanks 2.1 m diameter.
The engine is pump-fed and generates 680 kN of thrust, with a burn time of 149 seconds.
First stage GSLV-D1 used the S125 stage which contained
125 tonnes of solid propellant and had a burn time of 100 seconds. All subsequent launches
have used enhanced propellant loaded S139 stage. The S139 stage is 2.8 m in diameter
and has a nominal burn time of 109 seconds. The stage generates a maximum thrust of 4700 kN.
. Second stage
The GS2 stage is powered by the Vikas engine. It has 2.8 m diameter.
Third stage
The third stage of the GSLV Mk.II is propelled by the CE-7.5, an indigenous cryogenic rocket
engine, 2.8 m in diameter and uses liquid hydrogen and liquid oxygen The indigenous
cryogenic engine was built at the Liquid Propulsion Systems Centre in Mahendragiri, Tamil Nadu.
Variants All GSLV launches have been conducted from
the Satish Dhawan Space Centre in Sriharikota. The GSLV using the Russian Cryogenic Stage
are designated as the GSLV Mk-I and the GSLV using the indigenous Cryogenic Upper Stage
are designated the GSLV Mk-II. GSLV Mk I
This variant had a 125 t first stage and was capable of launching 1500 kg into geostationary
transfer orbit. This variant is retired. GSLV Mk I
This variant had 139 t first stage and improved fuel in the strap-on boosters & second stage.
This variant can launch 1900 kg into geostationary transfer orbit.
GSLV Mk I This variant has a 15 tonne propellant loading
in the third stage, called the C-15. GSLV-F06 is the only attempted launch of the Mark I(c)
version to date. GSLV Mk II
This variant uses an Indian cryogenic engine, the CE-7.5, and is capable of launching 2500 kg
into geostationary transfer orbit. Previous GSLV vehicles have used Russian cryogenic
engines. GSLV Mk-III
The Geosynchronous Satellite Launch Vehicle Mark III or the GSLV Mk-III is a three stage
launch vehicle under development. The GSLV Mk-III is a three stage vehicle with a first
stage consisting of two identical large solid boosters strapped onto the second liquid stage.
The third stage is a cryogenic stage. Launch history
See also Comparison of orbital launchers families
Comparison of orbital launch systems Geosynchronous Satellite Launch Vehicle Mk
III ISRO Orbital Vehicle
References
External links ISRO GSLV Page
INDIA in Space - GSLV Page 12KRB Upper Stage at Khrunichev Space Center