- Historical Background
- The Indian Space Resarch Organisation (ISRO) initiated the development of the Polar Satellite Launch Vehicle (PSLV) in the 1980s, based on the technology developed with the previous SLV-3 and ASLV launchers. The PSLV was designed to loft ISRO’s Indian Remote Sensing (IRS) satellites on behalf of India’s policy for autonomous access to space.
- First launch failed on September 20, 1993, due to a software error at stage 2/3 separation. Second and third development flights were successful on October 15, 1994, and March 21, 1996.
- An improved PSLV is due to make its debut in 1997.
- A Geosynchronous Satellite Launch Vehicle (GSLV) derived from the PSLV is also planned to be introduced in 1998.
- Launch Sites
- Sriharikota Range (SHAR), Andhra Pradesh (13° 41′ N / 80° 14′ E)
- Launch Log
- Major References
- The Orbital Launcher Report
- – Vol. 1 – N°3
- – Vol. 1 – N°4
- – Vol. 2 – N°6
- – Vol. 3 – N°6
| Number of Stages | 4 + 6 boosters | |
| Total Length | 44.2 m | |
| Gross Lift Off Mass | 283,000 kg |
| Designation | PSOM (S9) | six units |
| Diameter | 1 m | |
| Length | 10 m | |
| Total Mass | 10,930 kg | each |
| Propellant | HTPB | |
| Propellant Mass | 8,920 kg | each |
| Burning Time | 49 sec. | |
| Specific Impulse | 262 sec. | vacuum |
| Average Thrust | 422 kN | sea level, each |
| Designation | PS1 (S125) | |
| Diameter | 2.8 m | |
| Length | 20.3 m | |
| Total Mass | 160,200 kg | |
| Propellant | HTPB | |
| Propellant Mass | 129,000 kg | |
| Burning Time | 97 sec. | |
| Specific Impulse | 264 sec. | vacuum |
| Average Thrust | 4,860 kN / 3,587 kN | vacuum / sea level |
| Designation | PS2 (L37.5) | |
| Diameter | 2.8 m | |
| Length | 11.5 m | |
| Total Mass | 43,000 kg | |
| Propellant | UDMH + N2O4 | |
| Propellant Mass | 37,500 kg | |
| Engine | Vikas | derived from Ariane’s Viking 4 |
| Burning Time | 150 sec. | |
| Specific Impulse | 293 sec. | vacuum |
| Average Thrust | 725 kN | vacuum |
| Designation | PS3 (S7) | |
| Diameter | 2 m | |
| Length | 3.5 m | |
| Total Mass | 8,300 kg | |
| Propellant | HTPB | |
| Propellant Mass | 7,200 kg | |
| Burning Time | 75.2 sec. | |
| Specific Impulse | 291 sec. | vacuum |
| Average Thrust | 328.7 kN | vacuum |
| Designation | PS4 (L2) | |
| Diameter | 1.34 m | |
| Length | 2.6 m | |
| Total Mass | 2,920 kg | |
| Propellant | MMH + N2O4 | |
| Propellant Mass | 2,000 kg | |
| Engines | 2 x LVS | |
| Burning Time | 420 sec. | |
| Specific Impulse | 307 sec. | vacuum |
| Average Thrust | 7.5 kN | vacuum, each |
| Diameter | 3.2 m | |
| Length | 8.3 m |
| 2,900 kg |
400 km, 43° |
| 1,000 kg |
900 km, 99° | limited by azimut constraints |
| 450 kg |
GTO, 18° | limited by azimut constraints |
| ISRO Vikhram Sarabhai Space Centre (VSSC) |
| ISRO Liquid Propulsion Systems Centre (LPSC) | Vikas |
| ISRO Solid Propellant Space Booster Plant (SPROB) | Solid propulsion |
| Hindustan Aeronautics Ltd | Fairing, interstage structures |
| Anup Engineering Pvt Ltd | Solid motor case |
| ISRO Inertial Systems Unit (IISU) | Inertial measurement unit |
| Siva Vasu Electronics Works | Electronics wiring |
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© Takyon International 1997.