PSLV-C3
PSLV-C3 was the third operational launch and overall sixth mission of the PSLV program. This launch was also the forty-sixth launch by Indian Space Research Organisation since its first mission on 1 January 1962. The vehicle carried three satellites which were deployed in the Sun-synchronous Low Earth orbit. The vehicle carried Technology Experiment Satellite, BIRD and PROBA. This was India's and ISRO's second commercial spaceflight. PSLV-C3 was launched at 10:23 a.m. IST on 22 October 2001 from Satish Dhawan Space Centre .
Mission highlights
- Third operational launch of the PSLV program.
- Overall sixth mission of the PSLV program.
- Second commercial launch by ISRO.
- Three satellites injected in Sun-synchronous low Earth orbit.
Mission parameters
- Mass:
- * Total liftoff weight:
- * Payload weight:
- Overall height:
- Propellant:
- * First stage: Solid HTPB based
- * Second stage: Liquid UDMH +
- * Third stage: Solid HTPB based
- * Fourth stage: Liquid MMH + MON
- Engine:
- * First stage: S139
- * Second stage: Vikas
- * Third stage:
- * Fourth stage: 2 x PS-4
- Thrust:
- * First stage: 4,430 + 677 x 6 kN
- * Second stage: 724 kN
- * Third stage: 324 kN
- * Fourth stage: 7.4 x 2 kN
- Altitude:
- Maximum velocity:
- Duration: 1,658 seconds
Payload
| Country | Name | Nos | Mass | Type | Objective |
 India | TES | 1 | 1,108 kg | Satellite | Experimental Earth observation satellite |
 Belgium | BIRD | 1 | 94 kg | Microsatellite | Remote sensing technology demonstration |
 Germany | PROBA | 1 | 92 kg | Microsatellite | Earth observation technology demonstration |
Launch & planned flight profile
PSLV-C3 was launched at 10:23 a.m. IST on 22 October 2001 from Satish Dhawan Space Centre . The mission was planned with pre-flight prediction of covering overall distance of. Following was the planned flight profile.| Stage | Time | Altitude | Velocity | Event | Remarks |
| First stage | T+0 | 0.02 | 452 | First stage ignition | Lift-off |
| First stage | T+1.24 | 0.02 | 452 | Ignition of 4 ground-lit strap-on motors | |
| First stage | T+25.04 | 2.515 | 551 | Ignition of 2 air-lit strap-on motors | |
| First stage | T+68.04 | 23.472 | 1,155 | Separation of 4 ground-lit strap-on motors | |
| First stage | T+90.04 | 40.061 | 1,644 | Separation of 2 air-lit strap-on motors | |
| First stage | T+112.73 | 67.601 | 2,028 | First stage separation | |
| Second stage | T+112.93 | 67.828 | 2,027 | Second stage ignition | |
| Second stage | T+156.73 | 115.604 | 2,284 | Heat shield separation | |
| Second stage | T+278.81 | 236.272 | 4,099 | Second stage separation | |
| Third stage | T+280.01 | 237.433 | 4,097 | Third stage ignition | |
| Third stage | T+498.33 | 455.487 | 6,086 | Third stage separation | |
| Fourth stage | T+520.60 | 460.818 | 6,065 | Fourth stage ignition | |
| Fourth stage | T+914.92 | 571.247 | 7,575 | Fourth stage thrust cut-off | |
| Fourth stage | T+971.92 | 572.080 | 7,575 | TES separation | |
| Fourth stage | T+1,011.92 | 572.709 | 7,575 | BIRD separation | |
| Fourth stage | T+1,091.92 | 574.064 | 7,575 | PROBA orbit rise start | |
| Fourth stage | T+1,552.50 | 585.018 | 7,593 | PROBA orbit rise stop | |
| Fourth stage | T+1,602.50 | 586.688 | 7,592 | PROBA orbit separation | Mission over |