GS2 Vikas
Model of the Vikas engine
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| Country of origin | India |
|---|---|
| Designer | ISRO |
| Manufacturer | Godrej & Boyce |
| Status | Active |
| Liquid-fuel engine | |
| Propellant | N2O4 / UDMH |
| Cycle | Gas generator |
| Performance | |
| Thrust | 800 kN |
| Chamber pressure | 5.86 MPa,(58.5 bar) |
| Isp (vac.) | 290 seconds (2.8 km/s) |
| Dimensions | |
| Length | 3.70 m (12.1 ft)(Vikas-4B) |
| Used in | |
| 2nd stage of PSLV and GSLV Main stage L110 of GSLV Mk.III |
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The Vikas (an acronym for VIKram Ambalal Sarabhai) is a family of liquid fuelled rocket engines conceptualized and designed by the Liquid Propulsion Systems Centre in the 1970s. It is used in the Polar Satellite Launch Vehicle (PSLV) and the Geosynchronous Satellite Launch Vehicle (GSLV) series of expendable launch vehicles for space launch use.
The engine is used as the second stage of both the PSLV and the GSLV launch vehicles, with four strap-on boosters. The engine is also capable of gimballing. The GSLV MK-3 rocket uses two Vikas engines in its L110 core stage. The propellant loading for GSLV Mk-3 vikas engines is 55 tons compared to 40 tons for regular GSLV Mk-2 and PSLV rockets.
The engine uses up about 40 metric tons of UDMH as fuel and Nitrogen tetroxide (N2O4) as oxidizer with a maximum thrust of 725 kN. An up-graded version of the engine has a chamber pressure of 58.5 bar as compared to 52.5 bar in the older version and produces a thrust of 800 kN.
The rocket benefited from technological cooperation from the Viking 4A engine built by CNES/SEP of France. The primary difference being that the Vikas is rated for a longer burn time.
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