Apr 15, 2010
GSLV-D3 / GSAT-4
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.
|