Geosynchronous Satellite Launch Vehicle Mark II
There are two variant of payload
for GSLV vehicle:
1. Diameter of 3.4 m metallic PLF &
2. Diameter of 4 m ogive PLF.
The payload fairing of GSLV is wider than the
rest of the launcher. The fairing provides
aerodynamic efficiency and shields the payload from
mechanical damage during the atmospheric phase of
The cryogenic upper stage of GSLV
imparts a high velocity to the payload and detaches
at the periapsis. This high velocity is
characteristic of the Geosynchronous Transfer Orbit.
Once the spacecraft reaches the apoapsis of this
high eccentricity orbit,
it performs a burn using its Spacecraft propulsion
to circularise its orbit.
The high thrust hypergolic liquid
propellant Vikas engine's newer improved version
with a higher chamber pressure is used here. It is
activated 150 seconds into flight.
The first stage of GSLV is ignited
at Lift off(To) after the ignition of the four
strap-ons occurring at (To-4.8 sec), ensuring their
full functionality. This is required in order to
extract maximum thrust out of the initial stages.
The solid core of the first stage burns for 100
seconds while the strap-ons continue to provide
thrust for another 40 seconds
The GSLV uses 4 liquid strap-on
motors. The strap-ons are powered by one Vikas
engine each and along with the solid rocket motor
core of the first stage, provide an enormous thrust
to the launcher.
GSLV's primary payloads are INSAT
class of communication satellites that operate from
Geostationary orbits and hence are placed in
Geosynchronous Transfer Orbits by GSLV.
Further, GSLV's capability of placing
up to 6 tonnes in Low Earth Orbits broadens the scope of
payloads from heavy satellites to multiple smaller
Developed under the Cryogenic Upper
Stage Project (CUSP), the CE-7.5 is India's first
cryogenic engine, developed by the Liquid Propulsion
Systems Centre. CE-7.5 has a staged combustion operating
One Vikas engine is used in the
second stage of GSLV. The stage was derived from the PS2
of PSLV where the Vikas engine has proved its
The first stage of GSLV was also
derived from the PSLV's PS1. The 138 tonne solid rocket
motor is augmented by 4 liquid strap-ons.
Geosynchronous Satellite Launch Vehicle Mark II (GSLV Mk II)
the launch vehicle developed by India, to launch communication satellites in geo
transfer orbit using
cryogenic third stage. Initially Russian GK supplied cryogenic stages were used.
Later cryogenic stage was indigenously developed and
inducted in Jan 2014 from GSLV D5 onwards. This operational fourth generation
launch vehicle is a three stage vehicle with four liquid strap-ons.
The flight proven indigenously developed Cryogenic Upper Stage (CUS), forms the
third stage of GSLV Mk II. From January 2014,
the vehicle has achieved six consecutive successes