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PSLV-C2

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PSLV-C2
Model of the PSLV rocket
Mission typeDeployment of three satellites.
OperatorISRO
WebsiteISRO website
Mission duration1117.5 seconds
Apogee735.1 kilometres (457 mi)
Spacecraft properties
SpacecraftPolar Satellite Launch Vehicle
Spacecraft typeExpendable launch vehicle
ManufacturerISRO
Launch mass294,000 kilograms (648,000 lb)
Payload mass1,202 kilograms (2,650 lb)
Start of mission
Launch date11:52:00, May 26, 1999 (IST) (1999-05-26T11:52:00IST) (IST)
RocketPolar Satellite Launch Vehicle
Launch siteSriharikota Launching Range
ContractorISRO
End of mission
DisposalPlaced in graveyard orbit
Deactivated26 May 1999
Orbital parameters
Reference systemSun-synchronous
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 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.[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 $1.0 million (equivalent to $1.83 million in 2023) to ISRO for launching their satellites.[5][6]

Mission parameters

  • Mass:
    • Total liftoff weight: 294,000 kilograms (648,000 lb)
    • Payload weight: 1,202 kilograms (2,650 lb)
  • Overall height: 44.4 metres (145.7 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 kilometres (457 mi)
  • Maximum velocity: 7,490 metres per second (24,573 ft/s) (recorded at time of fourth stage ignition)
  • Duration: 1117.5 seconds

[1][7]

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.[1][8][9]

Country Name Nos Mass Type Objective
India India Oceansat-1 1 1,050 kg Indian Remote Sensing Satellite Remote sensing
South Korea South Korea Kitsat-3 1 107 kg Microsatellite Test & demonstrate new satellite bus & its payloads
Germany Germany DLR-Tubsat 1 45 kg Microsatellite Test newly developed attitude control system

Launch & planned flight profile

Heat shield of PSLV displayed at HAL heritage center.

PSLV-C2 was launched at 11:52 a.m. IST 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 (±35 km). 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

References

  1. ^ a b c d e "PSLV-C2". Indian Space Research Organisation. Retrieved 9 Jul 2016.
  2. ^ a b "Space Launch Report: PSLV". spacelaunchreport.com. Retrieved 9 Jul 2016.
  3. ^ a b "ISRO timeline since 1960s". Indian Space Research Organisation. Retrieved 9 Jul 2016.
  4. ^ a b "PSLV-C2 mission". iisc.ernet.in. Retrieved 9 Jul 2016.
  5. ^ a b c "The science and commerce of PSLV". Frontline. Retrieved 9 Jul 2016.
  6. ^ a b "PSLV Successfully Launches Three Satellites". Press Information Bureau. Retrieved 9 Jul 2016.
  7. ^ a b "PSLV-C2 brochure" (PDF). Indian Space Research Organisation. Retrieved 9 Jul 2016.
  8. ^ "Korea Institute of Technology Satellite-3". eoportal.org. Retrieved 9 Jul 2016.
  9. ^ "TUBSAT (Technical University of Berlin Satellite) Program". eoportal.org. Retrieved 9 Jul 2016.
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