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PSLV-C2

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PSLV-C2
Model of the PSLV launch vehicle
NamesPolar Satellite Launch Vehicle
Mission typeDeployment of three satellites
OperatorISRO
WebsiteISRO website
Mission duration1117.5 seconds
Spacecraft properties
SpacecraftPolar Satellite Launch Vehicle
Spacecraft typeExpendable launch vehicle
ManufacturerIndian Space Research Organisation
Launch mass294,000 kg (648,000 lb)
Payload mass1,202 kg (2,650 lb)
Start of mission
Launch date26 May 1999, 06:22 UTC
RocketPolar Satellite Launch Vehicle
Launch siteSriharikota Launching Range
ContractorISRO
Orbital parameters
Reference systemSun-synchronous orbit
RegimeLow Earth orbit
Payload
Oceansat-1
KITSAT-3
DLR-Tubsat
← PSLV-C1
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.[1][2][3][4][5] 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.[1] 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 $1.83 million in 2023) to ISRO for launching their satellites.[5][6]

Mission parameters

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  • Mass:
    • Total liftoff weight: 294,000 kg (648,000 lb)
    • Payload weight: 1,202 kg (2,650 lb)
  • Overall height: 44.4 m (146 ft)
  • 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: 735.1 km (456.8 mi)
  • Maximum velocity: 7,490 m/s (24,600 ft/s) (recorded at time of fourth stage ignition)
  • Duration: 1117.5 seconds [1][7]

Payload

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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.[1][8][9]

Country Name No. Mass Type Objective
India India Oceansat-1 1 1050 kg Indian Remote Sensing Satellite Remote sensing
South Korea South Korea KITSAT-3 1 107 kg Microsatellite Test and demonstrate new satellite bus & its payloads
Germany Germany DLR-Tubsat 1 45 kg Microsatellite Test newly developed attitude control system

Launch and planned flight profile

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Heat shield 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 727 km (452 mi). The actual perigee was 723.1 km, apogee was 735.1 km. Following was the planned flight profile.[1][2][3][4][5][7]

Stage Time
(seconds)		 Altitude
(kilometer)		 Velocity
(meter/sec)		 Event Remarks
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
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
Third stage T+285.7 255.46 4,060 Third stage ignition
T+506.4 533.57 5,970 Third stage separation
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.[6]

See also

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References

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  1. ^ a b c d e "PSLV-C2". Indian Space Research Organisation. Retrieved 9 July 2016.
  2. ^ a b "Space Launch Report: PSLV". Space Launch Report. Archived from the original on 4 January 2013. Retrieved 9 July 2016.{{cite news}}: CS1 maint: unfit URL (link)
  3. ^ a b "ISRO timeline since 1960s". Indian Space Research Organisation. Retrieved 9 July 2016.
  4. ^ a b "PSLV-C2 mission". iisc.ernet.in. Retrieved 9 July 2016.
  5. ^ a b c "The science and commerce of PSLV". Frontline (magazine). Retrieved 9 July 2016.
  6. ^ a b "PSLV Successfully Launches Three Satellites". Press Information Bureau. Retrieved 9 July 2016.
  7. ^ a b "PSLV-C2 brochure" (PDF). Indian Space Research Organisation. Retrieved 9 July 2016.
  8. ^ "Korea Institute of Technology Satellite-3". eoportal.org. Retrieved 9 July 2016.
  9. ^ "TUBSAT (Technical University of Berlin Satellite) Program". eoportal.org. Retrieved 9 July 2016.
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