ABOUT VIKAS
The Vikas engine is a liquid-fueled rocket engine developed by ISRO based on the French Viking engine technology. It burns UDMH and nitrogen tetroxide in a gas-generator cycle and powers the second stage and strap-on boosters of ISRO’s PSLV and GSLV rockets. The Vikas has been the backbone of India’s launch vehicle program for over three decades.
Image: ISRO
PERFORMANCE
| Thrust (Sea Level) | 680 kN (152,900 lbf) kN |
| Thrust (Vacuum) | 766 kN (172,200 lbf) kN |
| ISP (Sea Level) | 260 s s |
| ISP (Vacuum) | 293 s s |
| Chamber Pressure | 5.85 MPa (848 psi) bar |
| Mass | 900 kg |
| Thrust-to-Weight | 87 |
| Throttle Range | Not throttleable |
| Restart Capable | No |
THRUST CONVERSIONS (VACUUM)
| Kilonewtons | 766.0 kN |
| Pounds-force | 172,204 lbf |
ENGINE CYCLE
Gas Generator
A gas generator cycle taps off a small portion of propellants to drive turbopumps via a separate combustion chamber. The turbine exhaust is dumped overboard, making it less efficient but simpler and more reliable. Used by the Merlin, F-1, and RS-27.
PROPULSION
| Propellant | UDMH |
| Oxidizer | N₂O₄ (Nitrogen Tetroxide) |
| Engine Cycle | Gas Generator |
| Mixture Ratio | 1.7:1 |
| Flow Rate | ~266 kg/s kg/s |
PHYSICAL
| Dimensions | 0.9 m diameter × 2.8 m length |
| Combustion Chambers | 1 |
| Nozzle Expansion Ratio | 13.5:1:1 |
GENERAL
| Manufacturer | ISRO (Liquid Propulsion Systems Centre) |
| Country | India |
| Status | Active |
| First Flight | April 16, 1987 |
VARIANTS (4)
- Vikas 1
- Vikas 2
- Vikas 4
- Vikas High Thrust
VEHICLES USING VIKAS (3)
- PSLV
- GSLV Mk I
- GSLV Mk II
ENGINE LINEAGE
Viking (French)→Vikas→Vikas High Thrust
⚖ PROPELLANTS
