PSLV-C2
{{Short description|1999 Indian space launch mission}}
{{Use British English|date=October 2021}}
{{Use dmy dates|date=October 2021}}
{{Infobox spaceflight
| name = PSLV-C2
| names_list = Polar Satellite Launch Vehicle
| image = PSLV.svg
| image_caption = Model of the PSLV launch vehicle
| image_size = 90px
| mission_type = Deployment of three satellites
| operator = ISRO
| COSPAR_ID =
| SATCAT =
| website = [http://www.isro.gov.in/ ISRO website]
| mission_duration = 1117.5 seconds
| spacecraft = Polar Satellite Launch Vehicle
| spacecraft_type = Expendable launch vehicle
| spacecraft_bus =
| manufacturer = Indian Space Research Organisation
| launch_mass = {{cvt|294000|kg}}
| payload_mass = {{cvt|1202|kg}}
| dimensions =
| power =
| launch_date = 26 May 1999, 06:22 UTC
| launch_rocket = Polar Satellite Launch Vehicle
| launch_site = Sriharikota Launching Range
| launch_contractor = ISRO
| orbit_reference = Sun-synchronous orbit
| orbit_regime = Low Earth orbit
| orbit_periapsis =
| orbit_apoapsis =
| orbit_inclination =
| orbit_period =
| apsis = gee
| payload_items = 25px Oceansat-1
25px KITSAT-3
25px DLR-Tubsat
| insignia =
| insignia_caption =
| insignia_size = 200px
| programme = Polar Satellite Launch Vehicle missions
| previous_mission = PSLV-C1
| next_mission = PSLV-C3
}}
PSLV-C2 was the second operational launch and overall fifth mission of the Polar Satellite Launch Vehicle (PSLV) program. This launch was also the forty-third launch by Indian Space Research Organisation (ISRO) since its first mission on 1 January 1962. The vehicle carried three satellites which were deployed in the Sun-synchronous low Earth orbit.{{cite news|title=PSLV-C2|publisher=Indian Space Research Organisation|access-date=9 July 2016|url=http://www.isro.gov.in/launcher/pslv-c2}}{{cite news|title=Space Launch Report: PSLV |publisher=Space Launch Report|access-date=9 July 2016|url=http://www.spacelaunchreport.com/pslv.html|archive-url=https://archive.today/20130104225437/http://www.spacelaunchreport.com/pslv.html|url-status=usurped|archive-date=4 January 2013}}{{cite news|title=ISRO timeline since 1960s|publisher=Indian Space Research Organisation|access-date=9 July 2016|url=http://www.isro.gov.in/about-isro/isros-timeline-1960s-to-today#43}}{{cite news |title=PSLV-C2 mission|website=iisc.ernet.in|access-date=9 July 2016|url=http://www.iisc.ernet.in/currsci/oct25/articles18.htm}}{{cite news|title=The science and commerce of PSLV|publisher=Frontline (magazine)|access-date=9 July 2016|url=http://www.frontline.in/static/html/fl1612/16120370.htm}} The vehicle carried India's first remote sensing satellite Oceansat-1 (IRS-P4) 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 US$1.0 million (equivalent to ${{Inflation|US|1|1999|r=2}} million in {{Inflation-year|US}}) to ISRO for launching their satellites.{{cite news|url=http://pib.nic.in/focus/fomay99/fo2605992.html|title=PSLV Successfully Launches Three Satellites|publisher=Press Information Bureau |access-date=9 Jul 2016}}
Mission parameters
- Mass:
- Total liftoff weight: {{cvt|294000|kg}}
- Payload weight: {{cvt|1202|kg}}
- Overall height: {{cvt|44.4|m}}
- Propellant:
- First stage: Solid HTPB based (138.0 + 54 tonnes)
- Second stage: Liquid UDMH + {{N2O4}} (4.06 tonnes)
- Third stage: Solid HTPB based (7.2 tonnes)
- Fourth stage: Liquid MMH + {{N2O4}} (2.0 tonnes)
- 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: {{cvt|735.1|km}}
- Maximum velocity: {{cvt|7490|m/s}} (recorded at time of fourth stage ignition)
- Duration: 1117.5 seconds {{cite news|url=http://www.isro.gov.in/sites/default/files/pdf/pslv-brochures/PSLVC2.pdf|title=PSLV-C2 brochure |publisher=Indian Space Research Organisation|access-date=9 July 2016}}
Payload
PSLV-C2 carried and deployed total three satellites. Oceansat-1 (IRS-P4) was the main payload and KITSAT-3 and DLR-Tubsat were two auxiliary payloads that were mounted on PSLV-C2 equipment bay diametrically opposite to each other. Oceansat-1, was mounted on top of the equipment bay. In the flight sequence, IRS-P4 was injected first, followed by KITSAT-3 and then DLR-Tubsat.{{cite news|url=https://directory.eoportal.org/web/eoportal/satellite-missions/k/kitsat-3|title=Korea Institute of Technology Satellite-3 |publisher=eoportal.org|access-date=9 July 2016}}{{cite news|title=TUBSAT (Technical University of Berlin Satellite) Program |publisher=eoportal.org|access-date=9 July 2016|url=https://directory.eoportal.org/web/eoportal/satellite-missions/t/tubsat}}
| class="wikitable sortable" | |||||
| Country | Name | No. | Mass | Type | Objective |
|---|---|---|---|---|---|
| {{Flagicon|India}} India | Oceansat-1 | 1 | 1050 kg | Indian Remote Sensing Satellite | Remote sensing |
| {{Flagicon|South Korea}} South Korea | KITSAT-3 | 1 | 107 kg | Microsatellite | Test and demonstrate new satellite bus & its payloads |
| {{Flagicon|Germany}} Germany | DLR-Tubsat | 1 | 45 kg | Microsatellite | Test newly developed attitude control system |
Launch and planned flight profile
File:Full size heat shield of PSLV 7850.JPG of PSLV displayed at HAL heritage center.]]
PSLV-C2 was launched at 06:22 UTC on 26 May 1999 from Satish Dhawan Space Centre (then called "Sriharikota Launching Range"). The mission was planned with pre-flight prediction of perigee and apogee of {{cvt|727|km}}. The actual perigee was 723.1 km, apogee was 735.1 km. Following was the planned flight profile.
| class="wikitable" | |||||
| Stage | Time (seconds) | Altitude (kilometer) | Velocity (meter/sec) | Event | Remarks |
|---|---|---|---|---|---|
| rowspan="6" | First stage | T+0 | 0.02 | 450 | First stage ignition | Lift-off |
| T+1.2 | 0.02 | 450 | Ignition of 4 ground-lit strap-on motors | ||
| T+25.1 | 2.43 | 540 | Ignition of 2 air-lit strap-on motors | ||
| T+68.1 | 23.10 | 1,100 | Separation of 4 ground-lit strap-on motors | ||
| T+90.1 | 40.21 | 1,520 | Separation of 2 air-lit strap-on motors | ||
| T+117.7 | 72.08 | 1,970 | First stage separation | ||
| rowspan="4" | Second stage | T+117.9 | 72.38 | 1,970 | Second stage ignition | |
| T+162.7 | 120.71 | 2,210 | Heat shield separation | ||
| T+167.7 | 126.60 | 2,260 | Closed-loop guidance initiation | ||
| T+284.5 | 254.03 | 4,070 | Second stage separation | ||
| rowspan="2" | Third stage | T+285.7 | 255.46 | 4,060 | Third stage ignition | |
| T+506.4 | 533.57 | 5,970 | Third stage separation | ||
| rowspan="5" | Fourth stage | T+584.4 | 605.44 | 5,870 | Fourth stage ignition | |
| T+991.7 | 728.25 | 7,490 | Fourth stage thrust cut-off | ||
| T+1017.5 | 728.66 | 7,490 | Oceansat-1 (IRS-P4) separation | ||
| T+1067.5 | 729.51 | 7,490 | KITSAT-3 separation | ||
| T+1117.5 | 730.41 | 7,490 | DLR-Tubsat separation |
The launch was witnessed by Atal Bihari Vajpayee (then Prime Minister of India), Murli Manohar Joshi, Vasundhara Raje and N. Chandrababu Naidu.
See also
References
{{Reflist|30em}}
{{Portal bar|India|Science|Space|Spaceflight}}
{{PSLV}}
{{Indian space programme}}
{{Expendable launch systems}}