|Space Launch Report: GSLV|
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ISRO adapted stages from India'a Polar Satellite Launch Vehicle (PSLV) for GSLV. The first stage solid propellant motor and the liquid propellant second stage of PSLV, itself powered by engines used by Europe's Ariane 1, serve as the core first stage motor and the second stage of GSLV. The PSLV second stage was also used as the basis for the GSLV first stage liquid strap-on stages.
The first stage uses a 20.3 x 2.8 meter (m), 480 ton thrust
solid motor, augmented by four 19.7 x 2.1 m L40 liquid strap-on motors. The non-separating
L40s are powered by 70 ton thrust Viking 2 engines that burn UDMH/N2O4 for 160 seconds, 60
seconds longer than the core.
The vehicle is controlled by a strap-down inertial navigation/guidance system housed in a vehicle equipment bay that is mounted on a truss structure atop the third stage. A 7.8 meter tall, 3.4 meter diameter payload fairing protects the payload during ascent until it is jettisonned at an altitude of about 110 km during the second stage burn.
ISRO launched its first GSLV from Satish Dhawan Space
Centre, SHAR, Sriharikota on April 18, 2001. An early third stage cutoff denied the
49-meter tall rocket's total success in the inaugural D-1 mission. G-Sat 1, a 1,540 kg
test payload, fell about 4,000 km short of its planned 36,000 km geosynchronous transfer
orbit (GTO) apogee. G-Sat was unable to make up the difference with its apogee motor and
it ended up stranded in a 23-hour drift orbit. GSLV flew successfully in 2003 and 2004.
The failure began to make itself apparent almost
immediately after liftoff when one of four liquid-fueled strap-on boosters failed. This
created asymmetrical thrust that caused the vehicle to veer from its planned flight path.
The 49-metre-tall, 414 tonne, three-stage launcher broke up at relatively low
altitude and fell into the
On July 31, 2006 ISRO Chairman G Madhavan
Nair said that preliminary results of the investigation pointed toward a malfunction of
the thrust controller in the strap-on booster engine. Each booster is powered by a
single 70-tonne thrust Vikas engine fed by 42 tonnes of hypergolic liquid propellant.
Vikas are derived from Viking 2 engines originally used by
India Space Research Organization's GSLV-F06, a Mark 1 variant, suffered a control failure 47 seconds after liftoff from Sriharikota's Second Launch Pad on December 25, 2010. The three stage launch vehicle turned sideways at an altitude of 9-10 km and began to disintegrate, a process completed by the transmission of a range destruct command 63 seconds after liftoff. ISRO officials said that steering control commands had stopped reaching actuators on one or more of the four liquid strap on boosters. The precise cause of the failure is under investigation.
GSLV-F06 carried 2.31 tonne GSAT-5P, a communications satellite bound for geosynchronous transfer orbit. In order to lift GSAT-5P, GSLV-F06 was fitted with an enlarged 8.6 x 4 meter composite payload fairing and a stretched Russian powered third stage loaded with 15.2 tonnes of liquid hydrogen and liquid oxygen propellant.
It was the second failure of a GSLV in two 2010
attempts. GSLV-D3, a Mark 2 variant with India's first cryogenic upper stage, failed
on April 15, 2010 when the third stage engine failed at startup. Only two of the
seven GSLV launches performed since the rocket premiered in 2001 have flown as planned.
GSLV with India's Cryogenic Stage Succeeds
Indias Geosynchronous Satellite Launch Vehicle (GSLV) successfully boosted the GSAT 14 communications satellite into geosynchronous transfer orbit on January 5, 2013. It was the first success for the launch vehicle since 2004, and the first success for India's indigenously-developed, liquid hydrogen fueled Cryogenic Upper Stage (CUS).
The 415 tonne, 49 meter tall three-stage GSLV Mk 2 rocket, fitted with a 3.4 meter diameter payload fairing, lifted off at 10:48 UTC from the Second Launch Pad at the Satish Dhawan Space Center at Sriharikota to begin the GSLV-D5 development mission. It rose on 690.7 tonnes (1.52 million lbf) of liftoff thrust produced by a solid core motor augmented by four L40 liquid non-separating strap-on motors, each powered by a Vikas 2 engine that burned UDMH/N2O4 until cutoff 149 seconds after liftoff, about 60 seconds after the core burned out. The liquid second stage, powered by a single Vikas 4 UDMH/N2O4 engine, performed a 140.5 second burn to lift the vehicle to a 132 km altitude and a velocity of more than 4,900 m/sec.
The CUS LOX/LH2 third stage then fired its 7.5 tonne thrust CE-7.5 engine one time for more than 12 minutes to finish the mission. The 1.982 tonne satellite payload was accelerated toward a targeted 180 x 35,975 km x 19.3 deg orbit. ISRO's CE-7.5 is a staged combustion engine designed to operate at 454 seconds specific impulse - more efficient than the Aerojet-Rocketdyne RL10A-4-1 engine that powers the Atlas 5 Centaur stage. The fixed CE-7.5 engine is augmented by a pair of small steering engines.
An August, 2012 attempt to fly GLSV-D5 was thwarted by a second stage propellant leak during the early stages of the countdown. Damage caused by the leak forced ISRO to roll back and dismantle the rocket. Its core first stage and second stage were replaced entirely while its first stage liquid units were refurbished.
It was the third GSLV
success in eight flights since 2001.
DATE VEHICLE ID PAYLOAD MASS(t) SITE ORBIT ------------------------------------------------------------------------------------- 04/18/01 GSLV D01 GSAT 1 1.54 SR 1 [GTO-](1) 05/08/03 GSLV D02 GSAT 2 1.80 SR 1 GTO 09/20/04 GSLV F01 Edusat 2.00 SR 1 GTO 07/10/06 GSLV F02 INSAT 4C 2.17 SR 2 [FTO](2) 09/02/07 GSLV F04 INSAT 4CR 2.13 SR 2 [EEO](3) 04/15/10 GSLV Mk2 D03 GSAT 4 2.22 SR 2 [FTO](4) 12/25/10 GSLV F06 GSAT-5P 2.31 SR 2 [FTO](5) 01/05/14 GSLV Mk2 D05 GSAT 14 1.98 SR 2 GTO (6) 08/27/15 GLSV Mk2 D06 GSAT 6 2.117 SR 2 GTO 09/08/16 GSLV Mk2 F05 INSAT 3DR 2.211 SR 2 GTO 05/05/17 GSLV Mk2 F09 GSAT 9 2.23 SR 2 GTO ------------------------------------------------------------------------------------- (1) Upper stage shut down early. Left GSAT-1 4,000 km short of planned GTO apogee. (2) First stage liquid strap-on failed shortly after liftoff (3) Launch vehicle placed INSAT-4CR in 168 x 31,786 km x 15.8 deg orbit, well short of planned 170 x 35,975 km x 21.7 deg GTO. Guidance error. (4) 3rd Stg failed at or near startup. First Indian Cryo Stage (5) Control failed T+47 sec. RSO T+63 sec. (6) ISRO's first indeginous cryo upper stage success. ==================================================================================
Last Update: May 05, 2017