LVM3(Geosynchronous Satellite Launch Vehicle Mk III)
LVM3 will be
capable of placing the 4 tonne class
satellites of the GSAT series into
Geosynchronous Transfer Orbits.
The powerful cryogenic
stage of LVM3 enables it to place
heavy payloads into Low Earth Orbits of 600
The C25 is powered by
CE-20, India's largest cryogenic engine,
designed and developed by the Liquid
Propulsion Systems Centre.
LVM3 uses two
S200 solid rocket boosters to provide the
huge amount of thrust required for lift off.
The S200 was developed at Vikram Sarabhai
The L110 liquid stage
is powered by two Vikas engines designed and
developed at the Liquid Propulsion Systems
LVM3 is configured as a three stage vehicle with two
strap-on motors (S200), one liquid core stage (L110) and a high thrust cryogenic
stage (C25). The S200 solid motor is among the largest solid boosters in the
204 tonnes of solid propellant. The liquid L110 stage uses a twin liquid engine
with 115 tonnes of liquid propellant, while the C25 Cryogenic upper stage is
the fully indigenous high thrust cryogenic engine (CE20) with a propellant
loading of 28 tons.
The overall length of the vehicle is 43.5 m with a gross lift-off weight of 640
tonnes and a 5m-diameter payload fairing. .
LVM3 is the new heavy lift launch vehicle of
ISRO for achieving a 4000 kg spacecraft launching
capability to GTO (Geosynchronous Transfer Orbit) in a cost effective manner.
LVM3 is a three stage launch vehicle consisting of two solid propellant S200
and core stages comprising of L110 liquid stage, C25 cryogenic stage, the
equipment bay (EB) and the Encapsulated assembly (EA).
EA comprises of the spacecraft, Payload Adaptor (PLA) and the Payload fairing
(PF). With a lift-off mass of 640 tons, this 43.5 m
tall three-stage launch vehicle gives ISRO full self-reliance in launching
heavier communication satellites that weigh up to 4000 kg in GTO.
The vehicle takes off with the simultaneous ignition of the two S200 boosters.
The core stage (L110) is ignited at about 113s through the flight,
during the firing of the S200 stages. Both S200 motors burn for about 134s and
the separation occur at 137s. The payload fairing is separated at an altitude
of 115 km and at about 217s during L110 firing. The L110 burnout and separation
and C25 ignition occur at 313s.
The spacecraft is injected into a GTO (Geosynchronous Transfer Orbit) orbit of
180x36000 km at a nominal time of 974s.