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The GSLV-D3 was the sixth flight of ISRO's Geosynchronous Satellite Launch Vehicle (GSLV) as well as its third developmental flight. In this flight, GSLV was to launch 2220 kg GSAT-4, an experimental advanced technology communication satellite. GSLV-D3 was the maiden flight of GSLV in which the indigenous Cryogenic Upper Stage (CUS) was used.

GSLV-D3 was launched from the Second Launch Pad (SLP) at Satish Dhawan Space Centre SHAR, Sriharikota on April 15, 2010. Flight testing of the Indigenous Cryogenic Stage was unsuccessful.


GSLV –D3 Stages at a glance
Parameter
GS1 (First Stage)
GS2 (Second Stage)
(L37.5H)
GS3 (Third Stage) (CUS12)
S139 Booster
L40H Strap-on
Length (m)
20.13
19.7
11.56
8.7
Dia (m)
2.8
2.1
2.8
2.8
Propellant mass (t)
138.25
42.67
39.42
12.85
Case / Tank material
Maraging steel
Aluminium Alloy
Aluminium Alloy
Aluminium Alloy
Propellant
HTPB
UH25 and N2O4
UH25 and N2O4
LH2 and LOX
Burn Time (s)
109.8(action time)
149.3
(steady state time)
136
(steady state time)
714.4
(from ignition to shut off)
Max. Vac. Thrust (kN)

4707

763
799
73.5 (Normal)
82.0 (uprated)
Control System
 
Engine gimballing -Single Plane
Engine Gimalling – two place for pitch and yaw control, hot gas Reaction Control System (RCS) for roll control
2 Vernier engines for thrust phase control and cold gas RCS for cost phase control.

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