Jump to content

PSLV-C2

From Wikipedia, the free encyclopedia

PSLV-C2
Model of thePSLVlaunch vehicle
NamesPolar Satellite Launch Vehicle
Mission typeDeployment of threesatellites
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, 06:22UTC
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-C2was the second operational launch and overall fifth mission of thePolar Satellite Launch Vehicle(PSLV) program. This launch was also the forty-third launch byIndian Space Research Organisation(ISRO) since its first mission on 1 January 1962. The vehicle carried three satellites which were deployed in theSun-synchronouslow Earth orbit.[1][2][3][4][5]The vehicle carriedIndia's first remote sensingsatelliteOceansat-1(IRS-P4) as the main payload. It also carriedSouth KoreansatelliteKITSAT-3and German satelliteDLR-Tubsatas auxiliary payloads.[1]PSLV-C2 was the first IndianExpendable launch vehicleto 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

[edit]
  • 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:SolidHTPB based(138.0 + 54 tonnes)
    • Second stage:LiquidUDMH+N2O4(4.06 tonnes)
    • Third stage:SolidHTPB based(7.2 tonnes)
    • Fourth stage:LiquidMMH+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 6kN
    • Second stage:725kN
    • Third stage:340kN
    • Fourth stage:7.2 x 2kN
  • 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

[edit]

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
IndiaIndia Oceansat-1 1 1050 kg Indian Remote Sensing Satellite Remote sensing
South KoreaSouth Korea KITSAT-3 1 107 kg Microsatellite Test and demonstrate new satellite bus & its payloads
GermanyGermany DLR-Tubsat 1 45 kg Microsatellite Test newly developed attitude control system

Launch and planned flight profile

[edit]
Heat shieldof PSLV displayed atHALheritage center.

PSLV-C2 was launched at 06:22UTCon 26 May 1999 fromSatish Dhawan Space Centre(then called "Sriharikota Launching Range" ). The mission was planned with pre-flight prediction ofperigeeandapogeeof 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 shieldseparation
T+167.7 126.60 2,260 Closed-loopguidanceinitiation
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 byAtal Bihari Vajpayee(thenPrime Minister of India),Murli Manohar Joshi,Vasundhara RajeandN. Chandrababu Naidu.[6]

See also

[edit]

References

[edit]
  1. ^abcde"PSLV-C2".Indian Space Research Organisation.Retrieved9 July2016.
  2. ^ab"Space Launch Report: PSLV".Space Launch Report. Archived from the original on 4 January 2013.Retrieved9 July2016.{{cite news}}:CS1 maint: unfit URL (link)
  3. ^ab"ISRO timeline since 1960s".Indian Space Research Organisation.Retrieved9 July2016.
  4. ^ab"PSLV-C2 mission".iisc.ernet.in.Retrieved9 July2016.
  5. ^abc"The science and commerce of PSLV".Frontline (magazine).Retrieved9 July2016.
  6. ^ab"PSLV Successfully Launches Three Satellites".Press Information Bureau.Retrieved9 July2016.
  7. ^ab"PSLV-C2 brochure"(PDF).Indian Space Research Organisation.Retrieved9 July2016.
  8. ^"Korea Institute of Technology Satellite-3".eoportal.org.Retrieved9 July2016.
  9. ^"TUBSAT (Technical University of Berlin Satellite) Program".eoportal.org.Retrieved9 July2016.
Retrieved from "https://en.wikipedia.org/w/index.php?title=PSLV-C2&oldid=1197845709"