Encyclopedia Astronautica
PSLV



pslv.jpg
PSLV
PSLV - Polar Standard Launch Vehicle
Credit: ISRC
Indian third-generation launch vehicle, large enough to carry polar-orbiting earth resources satellites.

LEO Payload: 3,700 kg (8,100 lb) to a 200 km orbit at 49.50 degrees. Payload: 800 kg (1,760 lb) to a GTO, 18 deg. Failures: 1. Success Rate: 92.86%. First Fail Date: 1993-09-20. Last Fail Date: 1993-09-20. Launch data is: continuing. Launch Price $: 30.000 million in 1985 dollars. Flyaway Unit Cost $: 17.500 million in 1999 dollars.

Stage Data - PSLV

  • Stage 0. 6 x PSLV-0. Gross Mass: 10,930 kg (24,090 lb). Empty Mass: 2,010 kg (4,430 lb). Thrust (vac): 502.600 kN (112,989 lbf). Isp: 262 sec. Burn time: 44 sec. Isp(sl): 229 sec. Diameter: 1.00 m (3.20 ft). Span: 1.00 m (3.20 ft). Length: 9.99 m (32.77 ft). Propellants: Solid. No Engines: 1. Engine: SLV-1. Other designations: Polar Satellite Launch Vehicle. Status: In Production.
  • Stage 1. 1 x PSLV-1. Gross Mass: 168,200 kg (370,800 lb). Empty Mass: 30,200 kg (66,500 lb). Thrust (vac): 4,860.070 kN (1,092,587 lbf). Isp: 269 sec. Burn time: 105 sec. Isp(sl): 237 sec. Diameter: 2.80 m (9.10 ft). Span: 2.80 m (9.10 ft). Length: 20.34 m (66.73 ft). Propellants: Solid. No Engines: 1. Engine: PSLV-1. Other designations: Polar Satellite Launch Vehicle. Status: In Production.
  • Stage 2. 1 x PSLV-2. Gross Mass: 45,800 kg (100,900 lb). Empty Mass: 5,300 kg (11,600 lb). Thrust (vac): 725.015 kN (162,990 lbf). Isp: 293 sec. Burn time: 158 sec. Diameter: 2.80 m (9.10 ft). Span: 2.80 m (9.10 ft). Length: 12.50 m (41.00 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: Viking 4. Other designations: Polar Satellite Launch Vehicle. Status: In Production.
  • Stage 3. 1 x PSLV-3. Gross Mass: 8,400 kg (18,500 lb). Empty Mass: 1,100 kg (2,400 lb). Thrust (vac): 328.709 kN (73,897 lbf). Isp: 294 sec. Burn time: 83 sec. Diameter: 1.99 m (6.52 ft). Span: 2.02 m (6.62 ft). Length: 3.54 m (11.61 ft). Propellants: Solid. No Engines: 1. Engine: PSLV-3. Other designations: Polar Satellite Launch Vehicle. Status: In Production.
  • Stage 4. 1 x PSLV-4. Gross Mass: 2,920 kg (6,430 lb). Empty Mass: 920 kg (2,020 lb). Thrust (vac): 14.003 kN (3,148 lbf). Isp: 308 sec. Burn time: 425 sec. Isp(sl): 0.0000 sec. Diameter: 1.34 m (4.39 ft). Span: 2.02 m (6.62 ft). Length: 2.60 m (8.50 ft). Propellants: N2O4/MMH. No Engines: 2. Engine: PSLV-4. Other designations: Polar Satellite Launch Vehicle. Status: In Production.

AKA: Polar Satellite Launch Vehicle.
Status: Active.
Gross mass: 294,000 kg (648,000 lb).
Payload: 3,700 kg (8,100 lb).
Height: 44.40 m (145.60 ft).
Diameter: 2.80 m (9.10 ft).
Thrust: 5,300.00 kN (1,191,400 lbf).
Apogee: 200 km (120 mi).
First Launch: 1993.09.20.
Last Launch: 2011.04.20.
Number: 16 .

More... - Chronology...


Associated Countries
Associated Spacecraft
  • Oscar International series of amateur radio communications satellites. Operational, first launch 1961.12.12. Launched in a variety of configurations and by many nations. More...
  • IRS Indian Remote Sensing Satellite. Operational, first launch 1988.03.17. Remote sensing of the Earth for natural resources management applications. More...
  • Tubsat German communications technology satellite. 7 launches, 1991.07.17 (Tubsat-A) to 2007.01.10 (Maroc-Tubsat). Germany's Technical University of Berlin (TUB) built a successful series of 40 kg 'Tubsat' experimental technology satellites. More...
  • Kitsat South Korean technology satellite. 2 launches, 1993.09.26 (Oscar 23) to 1999.05.26 (Kitsat-3). South Korean indigenous 50-kg-class small satellite series, developed originally with technology transfer from Surrey Satellite Technology Ltd. More...
  • Rubin German technology microsatellite. 8 launches, the first on 2000.07.15 (Rubin). Rubin was developed by OHB and students of the Hochschule Bremen. More...
  • PROBA European earth land resources satellite. One launch, 2001.10.22. Proba (PRoject for On-Board Autonomy, 1) was a European Space Agency technology development minisatellite with a mass of 94 kg. More...
  • TES Indian military surveillance satellite. One launch, 2001.10.22. TES was an imaging satellite equipped with cameras and instruments to test military reconnaissance satellite technology. More...
  • BIRD German earth land resources satellite. One launch, 2001.10.22. More...
  • METSAT Indian earth weather satellite. One launch, 2002.09.12. METSAT was an Indian (ISRO) meteorological, geostationary satellite designed to simultaneously obtain atmospheric cloud cover, water vapor, and temperature data. More...
  • Cute Japanese technology satellite. 2 launches, 2006.02.21 (Cute 1.7) and 2008.04.28 (Cute-1.7-APD-II). Student subsatellites. More...
  • Pehuensat Argentinan technology satellite. One launch, 2007.01.10. Experimental satellite developed by the Universidad Nacional del Comahue and AMSAT-LU. The satellte remained attached to the PSLV's Dual Launch Adapter. More...
  • SRE Indian re-entry vehicle technology satellite. One launch, 2007.01.10. Indian experimental subscale Discoverer-type re-entry capsule. A testbed for a projected $ 3 billion Indian project to orbit a manned spacecraft by 2014. More...
  • AGILE Italian gamma ray astronomy satellite. One launch, 2007.04.23. The Italian gamma-ray observatory satellite (Astrorivelatore Gamma ad Imagini Leggero) carried the GRID 0. More...
  • Tecsar Israeli military surveillance radar satellite. First launch 2008.01.21. Israeli military radar/optical surveillance satellite using synthetic aperture x-band radar, with estimated 10 cm radar and 1 m optical ground resolution. More...
  • IMS Indian military surveillance radar satellite. One launch, 2008.04.28. Indian Mini Satellite, a small imaging satellite. More...
  • AAUSat Danish gamma ray astronomy satellite. One launch, 2008.04.28. University of Aalborg nanosat; carried a gamma ray burst detector for the Danish National Space Center. More...
  • Delfi Dutch technology satellite. One launch, 2008.04.28. Technical University of Delft nanosat. More...
  • Compass German technology satellite. One launch, 2008.04.28. Fachhochschule Aachen nanosat. More...
  • SEEDS Japanese technology satellite. One launch, 2008.04.28. Nihon University at Tokyo nanosat. More...
  • Can X Canadian technology satellite. 2 launched, 2008.04.28 (Can X-6 ) and (Can X-2 ). More...
  • Chandraayan Indian lunar orbiter. One launch, 2008.10.22. First Indian lunar orbiter. It released the MIP impactor. More...
  • MIP Indian lunar impact probe. One launch, 2008.10.22. Moon Impact Probe, released from Chandraayan-1 in lunar orbit. The MIP fired its own deorbit motor and impacted the moon near the Shackleton Crater at the south pole. More...

Associated Engines
  • PSLV-4 ISRO N2O4/MMH rocket engine. 7 kN. Isp=308s. Used on PSLV launch vehicle. First flight 1993. More...
  • PSLV-1 ISRO solid rocket engine. 4860 kN. Isp=264s. Used on GSLV, PSLV. First flight 1993. More...
  • PSLV-3 ISRO solid rocket engine. 328.7 kN. Isp=291s. Used on PSLV launch vehicle. First flight 1993. More...
  • SLV-1 ISRO solid rocket engine. 502.6 kN. Isp=253s. Used on ASLV, PSLV, SLV. First flight 1979. More...
  • Viking 4 SEP N2O4/UDMH rocket engine. 721 kN. Isp=296s. Used on Ariane 1, GSLV, PSLV. First flight 1979. More...

See also
  • PSLV Indian third-generation launch vehicle, large enough to carry polar-orbiting earth resources satellites. More...

Associated Manufacturers and Agencies
  • ISRO Indian manufacturer of rockets, spacecraft, and rocket engines. Indian Space Research Organization, India. More...

Bibliography
  • McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: here.
  • JPL Mission and Spacecraft Library, Jet Propulsion Laboratory, 1997. Web Address when accessed: here.
  • Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition).
  • Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al.
  • McDowell, Jonathan, Launch Log, October 1998. Web Address when accessed: here.
  • National Space Science Center Planetary Page, As of 19 February 1999.. Web Address when accessed: here.
  • Isakowitz, Steven J, Hopkins, Joshua B, and Hopkins, Joseph P, International Reference to Space Launch Systems, AIAA, Washington DC, 2004.
  • NASA/GSFC Orbital Information Group Website, Web Address when accessed: here.
  • Space-Launcher.com, Orbital Report News Agency. Web Address when accessed: here.

Associated Launch Sites
  • Sriharikota India's primary space launch center, located on the east coast of the peninsula with a firing sector over the Bay of Bengal. In use from 1971 to present. More...

Associated Stages
  • PSLV-3 Solid propellant rocket stage. Loaded/empty mass 8,400/1,100 kg. Thrust 328.71 kN. Vacuum specific impulse 294 seconds. More...
  • PSLV-4 N2O4/MMH propellant rocket stage. Loaded/empty mass 2,920/920 kg. Thrust 14.00 kN. Vacuum specific impulse 308 seconds. More...
  • PSLV-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 45,800/5,300 kg. Thrust 725.02 kN. Vacuum specific impulse 293 seconds. More...
  • PSLV-1 Solid propellant rocket stage. Loaded/empty mass 168,200/30,200 kg. Thrust 4,860.07 kN. Vacuum specific impulse 269 seconds. More...
  • PSLV-0 Solid propellant rocket stage. Loaded/empty mass 10,930/2,010 kg. Thrust 502.60 kN. Vacuum specific impulse 262 seconds. More...

PSLV Chronology


1993 September 20 - . 05:12 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota PSLV. LV Family: PSLV. Launch Vehicle: PSLV. LV Configuration: PSLV-D1. FAILURE: Software error caused vehicle to go off course.. Failed Stage: G.
  • IRS-1E - . Payload: IRS-1E. Nation: India. Agency: ISRO. Class: Earth. Type: Earth resources satellite. Spacecraft: IRS. COSPAR: F930920A.

1994 October 15 - . 05:05 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota PSLV. LV Family: PSLV. Launch Vehicle: PSLV. LV Configuration: PSLV-D2.
  • IRS-P2 - . Mass: 870 kg (1,910 lb). Nation: India. Agency: ISRO. Class: Earth. Type: Earth resources satellite. Spacecraft: IRS. USAF Sat Cat: 23323 . COSPAR: 1994-068A. Apogee: 820 km (500 mi). Perigee: 818 km (508 mi). Inclination: 98.6700 deg. Period: 101.29 min. Summary: Remote sensing; sun-synch orbit..

1996 March 21 - . 04:53 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota PSLV. LV Family: PSLV. Launch Vehicle: PSLV. LV Configuration: PSLV-D3.
  • IRS-P3 - . Mass: 930 kg (2,050 lb). Nation: India. Agency: ISRO. Class: Earth. Type: Earth resources satellite. Spacecraft: IRS. USAF Sat Cat: 23827 . COSPAR: 1996-017A. Apogee: 820 km (500 mi). Perigee: 819 km (508 mi). Inclination: 98.5000 deg. Period: 101.30 min. Summary: LEO .

1997 September 29 - . 04:47 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota PSLV. LV Family: PSLV. Launch Vehicle: PSLV. LV Configuration: PSLV-C1.
  • IRS-1D - . Payload: IRS-P3. Nation: India. Agency: ISRO. Class: Earth. Type: Earth resources satellite. Spacecraft: IRS. USAF Sat Cat: 24971 . COSPAR: 1997-057A. Apogee: 823 km (511 mi). Perigee: 742 km (461 mi). Inclination: 98.5000 deg. Period: 100.50 min.

1999 May 26 - . 06:22 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota PSLV. LV Family: PSLV. Launch Vehicle: PSLV. LV Configuration: PSLV-C2.
  • Kitsat-3 - . Nation: Korea South. Agency: ISRO. Manufacturer: KAIST. Class: Earth. Type: Seismology satellite. Spacecraft: Kitsat. USAF Sat Cat: 25756 . COSPAR: 1999-029A. Apogee: 727 km (451 mi). Perigee: 707 km (439 mi). Inclination: 98.6000 deg. Period: 99.10 min.
  • DLR-Tubsat - . Mass: 45 kg (99 lb). Nation: Germany. Agency: DLR. Class: Earth. Type: Seismology satellite. Spacecraft: Tubsat. USAF Sat Cat: 25757 . COSPAR: 1999-029B. Apogee: 733 km (455 mi). Perigee: 712 km (442 mi). Inclination: 98.6000 deg. Period: 99.20 min. DLR-Tubsat carried on the experimental work of Tubsat-A and -B. The satellite measured 32x32x32 cm and had a mass of 44.8 kg. The dechnology demonstrator conducted earth observation with 6 m resolution and conducted attitude control experiments. It was still in operation as of 2003.
  • OceanSat 1 (IRS-P4) - . Payload: IRS-P4. Mass: 1,036 kg (2,283 lb). Nation: India. Agency: ISRO. Class: Earth. Type: Sea satellite. Spacecraft: IRS. USAF Sat Cat: 25758 . COSPAR: 1999-029C. Apogee: 724 km (449 mi). Perigee: 721 km (448 mi). Inclination: 98.3000 deg. Period: 99.30 min. Summary: Remote sensing satellite with Ocean Colour Monitor (OCM) and a Multi-frequency Scanning Microwave Radiometer (MSMR).

2001 October 22 - . 04:53 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota PSLV. LV Family: PSLV. Launch Vehicle: PSLV. LV Configuration: PSLV-C3.
  • TES - . Mass: 1,108 kg (2,442 lb). Nation: India. Agency: ISRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: TES. USAF Sat Cat: 26957 . COSPAR: 2001-049A. Apogee: 592 km (367 mi). Perigee: 533 km (331 mi). Inclination: 97.6000 deg. Period: 95.90 min. Launch delayed from July 20. The PS4 upper stage deployed the 1108 kg Indian TES (Technology Experiment Satellite) into a sun-synchronous orbit at 05:09:10 GMT. TES was an imaging satellite equipped with cameras and instruments to test military reconnaissance satellite technology. It was probably based on the IRS remote sensing satellite and carried a one-meter resolution panchromatic camera. India decided to develop an independent indigenous reconnaissance satellite capability after the 1999 incursion of Pakistani troops into disputed territory in Kashmir caught it by surprise. TES was developed by ISRO, the Indian Space Research Organization.
  • BIRD - . Mass: 1,108 kg (2,442 lb). Nation: Germany. Agency: ISRO. Class: Earth. Type: Earth resources satellite. Spacecraft: BIRD. USAF Sat Cat: 26959 . COSPAR: 2001-049C. Apogee: 529 km (328 mi). Perigee: 509 km (316 mi). Inclination: 97.9000 deg. Period: 95.00 min. BIRD (Bispectral IR Detector) was a 94 kg German research minisatellite testing a new sensor for Earth imaging studies, detecting forest fires and other hot spots and studying vegetation changes. BIRD was released by the PS4 upper stage 40 seconds after the primary TES satellite payload had been deployed. The technology demonstrator was to help in the design a major remote sensing array of infrared detectors.
  • PROBA - . Mass: 1,108 kg (2,442 lb). Nation: Europe. Agency: ISRO. Class: Earth. Type: Earth resources satellite. Spacecraft: PROBA. USAF Sat Cat: 26958 . COSPAR: 2001-049B. Apogee: 677 km (420 mi). Perigee: 553 km (343 mi). Inclination: 97.9000 deg. Proba (PRoject for On-Board Autonomy, 1) was a European Space Agency technology development minisatellite with a mass of 94 kg. It carried a radiation detector, an IR spectrometer, debris impact detectors, Earth imaging cameras, and an experimental spacecraft processor for spacecraft autonomy experiments. The satellite was built by Verheart in Belgium using the MiniSIL bus developed by SI of England, and was controlled from Belgium. After release of the TES and BIRD satellites, the PS4's upper stage small RCS engines raised the orbit to 553 x 676 km, and PROBA was ejected at 0520 GMT.

2002 September 12 - . 10:25 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota PSLV. LV Family: PSLV. Launch Vehicle: PSLV. LV Configuration: PSLV-C4.
  • METSAT - . Payload: Metsat 1. Mass: 1,000 kg (2,200 lb). Nation: Europe. Agency: ISRO. Class: Earth. Type: Weather satellite. Spacecraft: Metsat. USAF Sat Cat: 27525 . COSPAR: 2002-043A. Apogee: 35,809 km (22,250 mi). Perigee: 35,764 km (22,222 mi). Inclination: 0.3000 deg. Period: 1,436.10 min. METSAT 1 was an Indian (ISRO) meteorological, geostationary satellite that was launched by an upgraded, four-stage PSLV-C4 rocket. The satellite was manoeuvred from the transfer orbit to a geostationary postion at 37 E longitude on September 16, and then was parked at 74 E longitude on September 24. As of 2007 Mar 11 located at 74.00E drifting at 0.007W degrees per day.

2003 October 17 - . 04:54 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota PSLV. LV Family: PSLV. Launch Vehicle: PSLV. LV Configuration: PSLV-C5.
  • ResourceSat 1 (IRS-P6) - . Mass: 1,360 kg (2,990 lb). Nation: India. Agency: ISRO. Program: IRS. Class: Earth. Type: Earth resources satellite. Spacecraft: IRS. USAF Sat Cat: 28051 . COSPAR: 2003-046A. Apogee: 836 km (519 mi). Perigee: 813 km (505 mi). Inclination: 98.8000 deg. Period: 101.40 min. Summary: The satellite was to replace IRS-1C and IRS-1D, and carried three cameras for remote sensing, the highest resolution one being the 6-meter LISS-4 imager. The sensors were designed for agricultural remote sensing applications..

2005 May 5 - . 04:44 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLP. LV Family: PSLV. Launch Vehicle: PSLV. LV Configuration: PSLV-C6.
  • CartoSat 1 - . Payload: IRS-P5. Mass: 1,560 kg (3,430 lb). Nation: India. Agency: ISRO. Spacecraft: IRS. USAF Sat Cat: 28649 . COSPAR: 2005-017A. Apogee: 623 km (387 mi). Perigee: 620 km (380 mi). Inclination: 97.9000 deg. Period: 97.10 min. First launch from new second PSLV pad at Sriharikota. Eleventh satellite in the Indian Remote Sensing satellite series, Cartosat-1 carried two panchromatic cameras, one fore-mounted with a tilt of +26 deg and the other aft-mounted with a tilt of -5 deg from the yaw axis. Together they provided black-and-white stereoscopic pictures in the visible region ( 0.50-0.85 micron) of the electromagnetic spectrum with a spatial resolution of 2.5 metre. The cameras covered a swath of 30 km and a solid state memory recorded up to 120 GB of images for downloading when the satellite passed over the Spacecraft Control Centre at Bangalore or ISTRAC stations at Lucknow, Mauritius, Bears Lake in Russia and Biak in Indonesia. Cartosat 1's sun-synchronous orbit crossed the equator at a local time of 10:30. The spacecraft was 3-axis stabilised using reaction wheels, magnetic torquers and hydrazine thrusters. 1100 W of eectrical power was provided by a 5 sq m solar array and two 24 Ah Ni-Cd batteries. Mission life was 5 years. Launch delayed from February, late April. The multispectral satellite had a 2.5-meter resolution camera.
  • VUSat - . Payload: IHamsat. Mass: 42 kg (92 lb). Nation: India. Agency: AmSat. Class: Communications. Type: Amateur radio communications satellite. Spacecraft: Oscar. USAF Sat Cat: 28650 . COSPAR: 2005-017B. Apogee: 646 km (401 mi). Perigee: 607 km (377 mi). Inclination: 97.9000 deg. Period: 97.20 min. Microsatellite providing satellite-based Amateur Radio services to the international community of Amateur Radio Operators (HAMs). Primarily intended for HAM operators in South Asia. One of the transponders was developed by Indian amateurs with the assistance of ISRO, and the second by a student at the Higher Technical Institute, Venlo, Netherlands. Hamsat was a 630 mm x 630 mm x 550 mm cube of aluminium-honeycomb structure. Power was provided by body-mounted gallium arsenide solar panels and a lithium ion battery. The satellite was spin-stabilised at 4 rpm. Uplink/downlink frequencies were 435.25 MHz / 145.9 MHz.

2007 January 10 - . 04:16 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota PSLV. LV Family: PSLV. Launch Vehicle: PSLV. LV Configuration: PSLV-C7.
  • SRE-1 - . Mass: 550 kg (1,210 lb). Nation: India. Agency: ISRO. Class: Technology. Type: Re-entry vehicle technology satellite. Spacecraft: SRE. Decay Date: 2007-01-22 . USAF Sat Cat: 29711 . COSPAR: 2007-001C. Apogee: 643 km (399 mi). Perigee: 620 km (380 mi). Inclination: 97.9000 deg. Period: 97.40 min. India's Space Recovery Experiment-1 India's SRE-1 first lowered to its orbit to 485 km x 643 km on January 20. A 10-minute deorbit burn began at 03:30 GMT on January 22, with re-entry beginning at 04:07 and a successful splashdown at 04:16 GMT in the Bay of Bengal near 13.3 N / 81.4E. The capsule was successfully recovered by the Indian Navy. The capsule returned two microgravity payloads as well as proving basic technologies for any eventual Indian manned space program. It was also announced that the capsule could be used to orbit further microgravity payloads at low cost to customers.
  • LAPAN Tubsat - . Mass: 56 kg (123 lb). Nation: Indonesia. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft: Tubsat. USAF Sat Cat: 29709 . COSPAR: 2007-001A. Apogee: 638 km (396 mi). Perigee: 620 km (380 mi). Inclination: 97.9000 deg. Period: 97.30 min. Summary: Experimental satellite developed with assistance from TUB (Berlin Technical University. It carried a 5-meter-resolution surveillance camera..
  • Cartosat-2 - . Mass: 680 kg (1,490 lb). Nation: India. Agency: ISRO. Class: Surveillance. Type: Civilian surveillance satellite. Spacecraft: IRS. USAF Sat Cat: 29710 . COSPAR: 2007-001B. Apogee: 644 km (400 mi). Perigee: 629 km (390 mi). Inclination: 98.0000 deg. Period: 97.40 min. The satellite was the twelfth in the Indian Remote Sensing satellite series and was capable of providing scene-specific spot imagery. The panchromatic camera provided imagery with a spatial resolution of better than one metre and a swath of 9.6 km. Data from the satellite was to be used for detailed mapping.
  • Pehuensat - . Mass: 6.00 kg (13.20 lb). Nation: Argentina. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft: Pehuensat. USAF Sat Cat: 29712 . COSPAR: 2007-001D. Apogee: 641 km (398 mi). Perigee: 621 km (385 mi). Inclination: 97.9000 deg. Period: 97.30 min. Summary: Experimental satellite developed by the Universidad Nacional del Comahue and AMSAT-LU. The satellte remained attached to the PSLV's Dual Launch Adapter..

2007 April 23 - . 10:00 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLP. LV Family: PSLV. Launch Vehicle: PSLV. LV Configuration: PSLV-CA PSLV-C8.
  • AGILE - . Mass: 352 kg (776 lb). Nation: Italy. Agency: ASI. Manufacturer: Carlo Gavazzi. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: AGILE. USAF Sat Cat: 31135 . COSPAR: 2007-013A. Apogee: 553 km (343 mi). Perigee: 523 km (324 mi). Inclination: 2.5000 deg. Period: 95.40 min. The PSLV-C8 launch vehicle flew for the first time in a light configuration with no strap-on motors and a Dual Launch Adapter. The Italian gamma-ray observatory satellite (Astrorivelatore Gamma ad Imagini Leggero) carried the GRID 0.3-200 MeV wide-field gamma ray camera and the Super-AGILE 15-45 keV detector hard X-ray detector.
  • AAM - . Mass: 185 kg (407 lb). Nation: India. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. USAF Sat Cat: 31136 . COSPAR: 2007-013B. Apogee: 549 km (341 mi). Perigee: 531 km (329 mi). Inclination: 2.5000 deg. Period: 95.50 min. Summary: The Dual Launch Adapter housed the secondary payload, an Advanced Avionics Module for future use on Indian launch vehicles. The AAM remained attached to the PSLV fourth stage..

2008 April 28 - . 03:53 GMT - . Launch Site: Sriharikota. LV Family: PSLV. Launch Vehicle: PSLV. LV Configuration: PSLV s/n C9.
  • Cartosat 2A - . Mass: 768 kg (1,693 lb). Nation: India. Agency: ISRO. Class: Surveillance. Type: Military surveillance radar satellite. Spacecraft: IRS. USAF Sat Cat: 32783 . COSPAR: 2008-021A. Apogee: 645 km (400 mi). Perigee: 623 km (387 mi). Inclination: 98.0000 deg. Period: 97.40 min. Summary: Primary payload, an imaging satellite with a spatial resolution of better than one metre and a swath of 9.6 km. Data from the satellite was to be used for detailed mapping..
  • Can X-6 - . Nation: Canada. Agency: ISRO. Class: Communications. Type: Military communications satellite. Spacecraft: Can X. USAF Sat Cat: 32784 . COSPAR: 2008-021B. Apogee: 638 km (396 mi). Perigee: 615 km (382 mi). Inclination: 98.0000 deg. Period: 97.20 min. Summary: Nanosat built by University of Toronto Institiute of Aerospace Studies and Com Dev International; carried a payload for relaying identification beacon data from shipping..
  • Cute-1.7-APD-II - . Mass: 4.00 kg (8.80 lb). Nation: Japan. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 32785 . COSPAR: 2008-021C. Apogee: 635 km (394 mi). Perigee: 615 km (382 mi). Inclination: 98.0000 deg. Period: 97.20 min. Summary: Tokyo Institute of Technology nanosat..
  • IMS 1 - . Mass: 60 kg (132 lb). Nation: India. Agency: ISRO. Class: Surveillance. Type: Military surveillance radar satellite. Spacecraft: IMS. USAF Sat Cat: 32786 . COSPAR: 2008-021D. Apogee: 638 km (396 mi). Perigee: 620 km (380 mi). Inclination: 98.0000 deg. Period: 97.30 min. Summary: Indian Mini Satellite, a small imaging satellite..
  • Compass 1 - . Nation: Germany. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 32787 . COSPAR: 2008-021E. Apogee: 636 km (395 mi). Perigee: 614 km (381 mi). Inclination: 98.0000 deg. Period: 97.20 min. Summary: Fachhochschule Aachen nanosat..
  • AAUSat-II - . Nation: Denmark. Agency: ISRO. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: Cubesat. USAF Sat Cat: 32788 . COSPAR: 2008-021F. Apogee: 636 km (395 mi). Perigee: 614 km (381 mi). Inclination: 98.0000 deg. Period: 97.20 min. Summary: University of Aalborg nanosat; carried a gamma ray burst detector for the Danish National Space Center..
  • Delfi-C3 - . Nation: Netherlands. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 32789 . COSPAR: 2008-021G. Apogee: 636 km (395 mi). Perigee: 614 km (381 mi). Inclination: 98.0000 deg. Period: 97.20 min. Summary: Technical University of Delft nanosat..
  • Can X-2 - . Nation: Canada. Agency: ISRO. Class: Communications. Type: Military communications satellite. Spacecraft: Cubesat. USAF Sat Cat: 32790 . COSPAR: 2008-021H. Apogee: 635 km (394 mi). Perigee: 615 km (382 mi). Inclination: 98.0000 deg. Period: 97.20 min.
  • SEEDS 2 - . Nation: Japan. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 32791 . COSPAR: 2008-021J. Apogee: 637 km (395 mi). Perigee: 614 km (381 mi). Inclination: 98.0000 deg. Period: 97.20 min. Summary: Nihon University at Tokyo nanosat..
  • Rubin-8-AIS - . Nation: India. Agency: ISRO. Class: Communications. Type: Civilian communications satellite. Spacecraft: Rubin. USAF Sat Cat: 32792 . COSPAR: 2008-021K. Apogee: 662 km (411 mi). Perigee: 619 km (384 mi). Inclination: 97.9000 deg. Period: 97.50 min. Summary: Remained attached to PSLV final stage; carried a payload for relaying identification beacon data from shipping..

2008 October 22 - . 00:52 GMT - . Launch Site: Sriharikota. LV Family: PSLV. Launch Vehicle: PSLV. LV Configuration: PSLV s/n C11.
  • Chandraayan-1 - . Mass: 1,380 kg (3,040 lb). Nation: India. Agency: ISRO. Class: Moon. Type: Lunar probe. Spacecraft: Chandraayan. USAF Sat Cat: 33405 . COSPAR: 2008-052A. Apogee: 22,817 km (14,177 mi). Perigee: 225 km (139 mi). Inclination: 17.8000 deg. Period: 403.00 min. India's first lunar probe. Placed by the PSLV into indicated orbit. It then used its own engines for translunar injection. It entered an initial lunar orbit of 504 km x 7502 km x 90.0 deg on November 8, maneuvering to the planned 100 x 100 km orbit by November 12.
  • MIP - . Nation: India. Agency: ISRO. Class: Moon. Type: Lunar probe. Spacecraft: MIP. USAF Sat Cat: 33406 . COSPAR: 2008-052B. Apogee: 23,095 km (14,350 mi). Perigee: 277 km (172 mi). Inclination: 17.8000 deg. Period: 402.70 min. Moon Impact Probe, released from Chandraayan-1 in lunar orbit on November 14 at 14:36 GMT. The MIP fired its own deorbit motor and impacted the moon at 15:01 GMT, near the Shackleton Crater at the south pole. The impact plume was scanned by the Chandraayan-1 orbiter and ground-based telescopes for evidence of lunar polar ice.

2011 April 20 - . 04:42 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota PSLV. LV Family: PSLV. Launch Vehicle: PSLV.
  • Resourcesat 2 - . Mass: 1,200 kg (2,600 lb). Nation: India. Program: IRS. Class: Surveillance. Type: Surveillance satellite. Spacecraft: IRS. USAF Sat Cat: 37387 . COSPAR: 2011-015A. Apogee: 825 km (512 mi). Perigee: 820 km (500 mi). Inclination: 98.8000 deg. Period: 101.30 min. Surveillance satellite. Carried the LISS-4 camera, a 6-meter-resolution imager, which was to be used for both military reconnaissance and civilian remote sensing. It also carried the lower resolution LISS-3 (23 m resolution) and AWIFS (56 m resolution), and an AIS Automatic Identification System payload for Comdev of Canada for tracking ships at sea.
  • Youthsat - . Nation: India. Class: Science. Type: Science satellite. USAF Sat Cat: 37388 . COSPAR: 2011-015B. Apogee: 823 km (511 mi). Perigee: 803 km (498 mi). Inclination: 98.8000 deg. Period: 101.20 min. Summary: Carried experiments to study solar-terrestrial relationships..
  • X-Sat - . Nation: India. Class: Surveillance. Type: Surveillance satellite. USAF Sat Cat: 37389 . COSPAR: 2011-015C. Apogee: 822 km (510 mi). Perigee: 803 km (498 mi). Inclination: 98.8000 deg. Period: 101.10 min. Summary: Nanyang Technological University Singapore satellite; carried a 10-meter-resolution multispectral imager..

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