PSLV-C2
PSLV-C2 was the second operational launch and overall fifth mission of the PSLV program. This launch was also the forty-third 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 India's first remote sensing satellite Oceansat-1 as the main payload. It also carried South Korean satellite Kitsat-3 and German satellite DLR-Tubsat as auxiliary payloads. PSLV-C2 was the first Indian Expendable launch vehicle to carry and deploy more than one satellite in a mission. This was also India's and ISRO's first commercial spaceflight where South Korea and Germany each paid $1.0 million to ISRO for launching their satellites.
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 +
- Engine:
- * First stage: S139
- * Second stage: Vikas
- * Third stage:
- * Fourth stage: 2 x PS-4
- Thrust:
- * First stage: 4628 + 662 x 6 kN
- * Second stage: 725 kN
- * Third stage: 340 kN
- * Fourth stage: 7.2 x 2 kN
- Altitude:
- Maximum velocity:
- Duration: 1117.5 seconds
Payload
| Country | Name | Nos | Mass | Type | Objective |
 India | Oceansat-1 | 1 | 1,050 kg | Indian Remote Sensing Satellite | Remote sensing |
 South Korea | Kitsat-3 | 1 | 107 kg | Microsatellite | Test & demonstrate new satellite bus & its payloads |
 Germany | DLR-Tubsat | 1 | 45 kg | Microsatellite | Test newly developed attitude control system |
Launch & planned flight profile
PSLV-C2 was launched at 11:52 a.m. IST on 26 May 1999 from Satish Dhawan Space Centre . The mission was planned with pre-flight prediction of perigee and apogee of 727 km. The actual perigee was 723.1 km, apogee was 735.1 km. Following was the planned flight profile.| Stage | Time | Altitude | Velocity | Event | Remarks |
| First stage | T+0 | 0.02 | 450 | First stage ignition | Lift-off |
| First stage | T+1.2 | 0.02 | 450 | Ignition of 4 ground-lit strap-on motors | |
| First stage | T+25.1 | 2.43 | 540 | Ignition of 2 air-lit strap-on motors | |
| First stage | T+68.1 | 23.10 | 1,100 | Separation of 4 ground-lit strap-on motors | |
| First stage | T+90.1 | 40.21 | 1,520 | Separation of 2 air-lit strap-on motors | |
| First stage | T+117.7 | 72.08 | 1,970 | First stage separation | |
| Second stage | T+117.9 | 72.38 | 1,970 | Second stage ignition | |
| Second stage | T+162.7 | 120.71 | 2,210 | Heat shield separation | |
| Second stage | T+167.7 | 126.60 | 2,260 | Closed-loop guidance initiation | |
| Second stage | T+284.5 | 254.03 | 4,070 | Second stage separation | |
| Third stage | T+285.7 | 255.46 | 4,060 | Third stage ignition | |
| Third stage | T+506.4 | 533.57 | 5,970 | Third stage separation | |
| Fourth stage | T+584.4 | 605.44 | 5,870 | Fourth stage ignition | |
| Fourth stage | T+991.7 | 728.25 | 7,490 | Fourth stage thrust cut-off | |
| Fourth stage | T+1017.5 | 728.66 | 7,490 | Oceansat-1 separation | |
| Fourth stage | T+1067.5 | 729.51 | 7,490 | Kitsat-3 separation | |
| Fourth stage | T+1117.5 | 730.41 | 7,490 | DLR-Tubsat separation |
The launch was witnessed by Atal Bihari Vajpayee, Murli Manohar Joshi, Vasundhara Raje and N. Chandrababu Naidu.