Editing Polar Satellite Launch Vehicle

{{Short description|Indian expendable launch vehicle}}
{{Use Indian English|date=January 2018}}
{{Use dmy dates|date=November 2018}}
{{Infobox Rocket 
|name           = Polar Satellite Launch Vehicle
|image          = PSLV C-35 at the launch pad (cropped).jpg
|caption        = PSLV-C35 on the [[Satish Dhawan Space Centre#First Launch Pad|SDSC FLP]]

|function       = [[Medium-lift launch vehicle|Medium-lift launch system]]
|manufacturer   = ISRO
|country-origin = India
|cpl            = {{INRConvert|130|c|lk=on|year=2020}}<br/>-{{INRConvert|200|c|lk=on|year=2020}}<ref>{{cite web|title=SURPLUS MISSILE MOTORS: Sale Price Drives Potential Effects on DOD and Commercial Launch Providers|url=http://www.gao.gov/products/GAO-17-609|website=gao.gov|publisher=U.S. Government Accountability Office|date=16 August 2017|access-date=2 May 2018|archive-date=13 April 2018|archive-url=https://web.archive.org/web/20180413081425/https://www.gao.gov/products/GAO-17-609|url-status=live}} {{PD-notice}}</ref>
|height         = {{cvt|44|m}}
|diameter       = {{cvt|2.8|m}}
|mass           = '''PSLV-G:''' {{cvt|295000|kg}}<br/>'''PSLV-CA:''' {{cvt|230000|kg}}<br/>'''PSLV-XL:''' {{cvt|320000|kg}}<ref name="pslv">{{cite web|url=http://www.isro.gov.in/launchers/pslv|title=Polar Satellite Launch Vehicle|access-date=21 December 2014|archive-date=22 December 2016|archive-url=https://web.archive.org/web/20161222143633/http://www.isro.gov.in/launchers/pslv|url-status=live}}</ref>
|stages         = 4
|capacities     =

{{infobox rocket/Payload
|location       = [[Low Earth orbit|LEO]] (200 km @ 30° inclination)
|mass           = {{plainlist|
* '''G:''' {{cvt|3200|kg}}
* '''CA:''' {{cvt|2100|kg}}
* '''XL:''' {{cvt|3800|kg}}}}<ref name = "Access to Space">{{cite web|url=http://www.bsxindia.com/SomnathProjectDirector.pdf|title=Access to Space|year=2011|access-date=March 8, 2017|archive-url=https://web.archive.org/web/20101122032654/http://www.bsxindia.com/SomnathProjectDirector.pdf|archive-date=22 November 2010}}</ref><ref name="Thales_2009">{{cite web |title=Galileo Galilei (GG) Launcher Identification And Compatibility Analysis Report |url=http://eotvos.dm.unipi.it/temp/OLD/GG%20PRR%20DataPack/23%20-%20SD-TN-AI-1169_1%20Launcher%20Identification.pdf |access-date=27 February 2022 |archive-url=https://web.archive.org/web/20150410201701/http://eotvos.dm.unipi.it/temp/OLD/GG%20PRR%20DataPack/23%20-%20SD-TN-AI-1169_1%20Launcher%20Identification.pdf |archive-date=10 April 2015 |page=27 |date=8 June 2009}}</ref>}}

{{infobox rocket/Payload
|location       = [[Sun-synchronous orbit|SSO]] (620 km circular)
|mass           = {{plainlist|
* '''G:''' {{cvt|1600|kg}}
* '''CA:''' {{cvt|1100|kg}}
* '''XL:''' {{cvt|1750|kg}}}}<ref name = "Access to Space" /><ref name="pslv"/><ref name="VSSC_PSLV"/>}}

{{infobox rocket/Payload
|location       = [[Geostationary transfer orbit|Sub-GTO]] (284 × 20650 km)
|mass           = {{cvt|1425|kg}}<br/>
'''(PSLV-XL)'''<ref name="pslv"/><ref name="VSSC_PSLV"/>}}

{{infobox rocket/Payload
|location       = [[Geostationary transfer orbit|GTO]]
|mass           = {{plainlist|
* '''G:''' {{cvt|1150|kg}}
* '''XL:''' {{cvt|1300|kg}}}}<ref name = "Access to Space" /><ref>{{cite web |title=PSLV |url=http://www.spacelaunchreport.com/pslv.html |website=Space Launch Report |access-date=17 December 2020 |archive-date=28 July 2020 |archive-url=https://web.archive.org/web/20200728073632/http://www.spacelaunchreport.com/pslv.html |url-status=usurped }}</ref>}}

|status         = Active
|sites          = [[Satish Dhawan Space Centre]]
|launches       = [[List of PSLV launches#Launch history|63]]
|success        = 59
|fail           = 3
|partial        = 1
|first = {{plainlist|
* '''PSLV-G:''' 20 September 1993
* '''PSLV-CA:''' 23 April 2007
* '''PSLV-XL:''' 22 October 2008
* '''PSLV-DL:''' 24 January 2019
* '''PSLV-QL:''' 1 April 2019
}}
|last = {{plainlist|
* '''PSLV-G:''' 26 September 2016
* '''PSLV-CA:''' 30 December 2024
* '''PSLV-XL:''' 18 May 2025
* '''PSLV-DL:''' 1 January 2024
* '''PSLV-QL:''' 11 December 2019
}}
|payloads       = {{ubl|[[Chandrayaan-1]]|[[Mars Orbiter Mission]]|[[Astrosat]]|[[SRE-1]]|[[NAVIC]]|[[Aditya-L1]]|[[PROBA-3]]}}
|stagedata      = {{Infobox rocket/stage
|type           = booster
|diff           = PSLV-G
|name           = S9
|number         = 6 
|thrust         = {{cvt|510|kN}}
|SI             = {{cvt|262|isp}}
|burntime       = 44 s
|fuel           = [[Hydroxyl-terminated polybutadiene|HTPB]]
}}
{{Infobox rocket/stage
|type           = booster
|diff           = PSLV-XL/QL/DL
|name           = S12
|number         = 6 (XL)<br>4 (QL)<br/>2 (DL)
|length         = {{cvt|12|m}}<ref name=C37borchure>{{cite web|url=http://www.isro.gov.in/pslv-c37-cartosat-2-series-satellite/pslv-c37-brochure-0|title=PSLV-C37 Brochure|publisher=ISRO|access-date=5 June 2017|archive-date=8 April 2017|archive-url=https://web.archive.org/web/20170408124444/http://www.isro.gov.in/pslv-c37-cartosat-2-series-satellite/pslv-c37-brochure-0?page=1|url-status=dead}}</ref>
|diameter       = {{cvt|1|m}}
|engines        = off
|thrust         = {{cvt|703.5|kN}}<ref name="C41_Brochure">{{cite web|title=PSLV_C41_Brochure|url=https://www.isro.gov.in/sites/default/files/article-files/node/10157/for_web.pdf|access-date=9 April 2018 |archive-url=https://web.archive.org/web/20180409123338/https://www.isro.gov.in/sites/default/files/article-files/node/10157/for_web.pdf|archive-date=9 April 2018}}</ref>
|total          = {{cvt|4221|kN}} (XL)<br/>{{cvt|2814|kN}} (QL)<br/>{{cvt|1407|kN}} (DL)
|SI             = {{cvt|262|isp}}
|burntime       = 70 s
|fuel           = [[Hydroxyl-terminated polybutadiene|HTPB]]
|empty          = 
|gross          = 
|propmass       = {{cvt|12200|kg}} each
}}
{{Infobox rocket/stage
|type           = stage
|stageno        = First
|engines        = [[S139 Booster|S139]]
|length         = {{cvt|20|m}}<ref name=C37borchure/>
|diameter       = {{cvt|2.8|m}}
|solid          = yes
|thrust         = {{cvt|4846.9|kN}}<ref name="C41_Brochure"/>
|burntime       = 110 s
|SI             = {{cvt|237|isp}} ([[sea level]])<br/>{{cvt|269|isp}} ([[vacuum]])
|fuel           = [[Hydroxyl-terminated polybutadiene|HTPB]]
|empty          = 
|gross          = 
|propmass       = {{cvt|138200|kg}} each<ref name=C37borchure/><ref name="pslv"/>
}}
{{Infobox rocket/stage
|type           = stage
|stageno        = Second
|length         = {{cvt|12.8|m}}<ref name=C37borchure/>
|diameter       = {{cvt|2.8|m}}
|engines        = 1 [[Vikas engine|Vikas]]
|thrust         = {{cvt|803.7|kN}}<ref name="C41_Brochure"/>
|SI             = {{cvt|293|isp}}
|burntime       = 133 s
|fuel           = [[Dinitrogen tetroxide|N<sub>2</sub>O<sub>4</sub>]]/[[UDMH]]
|empty          = 
|gross          = 
|propmass       = {{cvt|42000|kg}} each<ref name=C37borchure/>
}}
{{Infobox rocket/stage
|type           = stage
|stageno        = Third
|length         = {{cvt|3.6|m}}<ref name=C37borchure/>
|diameter       = {{cvt|2|m}}
|engines        = S-7<ref name=sf101/>
|solid          = yes
|thrust         = {{cvt|250|kN}}
|SI             = {{cvt|295|isp}}
|burntime       = 113.5 s<ref name="CurrSci_V119_I6"/>
|fuel           = [[Hydroxyl-terminated polybutadiene|HTPB]]
|empty          = 
|gross          = 
|propmass       = {{cvt|7600|kg}} each<ref name=C37borchure/>
}}
{{Infobox rocket/stage
|type           = stage
|stageno        = Fourth
|length         = {{cvt|3|m}}<ref name=C37borchure/>
|diameter       = {{cvt|1.3|m}}
|engines        = 2 x L-2-5<ref name=sf101/>
|thrust         = {{cvt|14.66|kN}}<ref name="C41_Brochure"/>
|SI             = {{cvt|308|isp}}
|burntime       = 525 s
|fuel           = [[Monomethylhydrazine|MMH]]/[[Mixed Oxides of Nitrogen|MON]]
|empty          =  
|gross          =  
|propmass       = {{cvt|2500|kg}} each<ref name=C37borchure/>
}}
|comparable=[[Vega (rocket)|Vega]], [[Nuri (rocket)|Nuri]]}}

The '''Polar Satellite Launch Vehicle''' ('''PSLV''') is an [[expendable launch system|expendable]] [[medium-lift launch vehicle]] designed and operated by the [[ISRO|Indian Space Research Organisation]] (ISRO). It was developed to allow India to launch its [[Indian Remote Sensing Programme|Indian Remote Sensing]] (IRS) [[satellite]]s into [[Sun-synchronous orbit]]s, a service that was, until the advent of the PSLV in 1993, only commercially available from Russia. PSLV can also launch small size satellites into [[Geostationary transfer orbit|Geostationary Transfer Orbit]] (GTO).<ref name="ISRO Launch Vehiles">{{cite web|url=http://www.isro.org/Launchvehicles/launchvehicles.aspx|title=Welcome To ISRO :: Launch Vehicles|access-date=8 April 2014|archive-date=29 October 2014|archive-url=https://web.archive.org/web/20141029221429/http://www.isro.org/launchvehicles/launchvehicles.aspx|url-status=dead}}</ref>

Some notable payloads launched by PSLV include India's first [[Moon|lunar]] probe [[Chandrayaan-1]], India's first [[Interplanetary spaceflight|interplanetary mission]], [[Mars Orbiter Mission]] (Mangalyaan), India's first [[Space telescope|space observatory]], [[AstroSat|Astrosat]] and India's first [[Sun#Solar space missions|Solar mission]], [[Aditya-L1]].<ref name="pslv"/>

PSLV has gained credibility as a leading provider of [[Secondary payload|rideshare]] services for small satellites, owing to its numerous multi-satellite deployment campaigns with auxiliary payloads, usually ride-sharing along with an Indian primary payload.<ref>{{cite web|last1=Foust|first1=Jeff|title=Rideshare demand grows despite development of small launch vehicles|date=23 June 2017|url=https://spacenews.com/rideshare-demand-grows-despite-development-of-small-launch-vehicles/|publisher=Space News|access-date=2017-06-23}}</ref> As of June 2022, PSLV has launched [[List of foreign satellites launched by India|345 foreign satellites]] from 36 countries.<ref>{{cite web|url=https://timesofindia.indiatimes.com/india/pslv-c48-successfully-launches-risat-2bri-9-foreign-satellites/articleshow/72470119.cms|title=PSLV-C48 successfully launches RISAT-2BRI, 9 foreign satellites |last1=Tejonmayam|first1=U|work=The Times of India|date=11 December 2019|access-date=11 December 2019}}</ref> Most notable among these was the launch of [[PSLV-C37]] on 15 February 2017, successfully deploying 104 satellites in Sun-synchronous orbit, tripling the previous record held by Russia for the highest number of satellites sent to space on a single launch,<ref>{{cite news|url=https://www.nytimes.com/2017/02/15/world/asia/india-satellites-rocket.html|title=India Launches 104 Satellites From a Single Rocket, Ramping Up Space Race|last=Barry|first=Ellen|issn=0362-4331|date=2017-02-15|newspaper=The New York Times|access-date=15 February 2017|archive-date=5 April 2017|archive-url=https://web.archive.org/web/20170405215039/https://www.nytimes.com/2017/02/15/world/asia/india-satellites-rocket.html|url-status=live}}</ref><ref name="timesofindia.indiatimes.com">{{cite news|url=http://timesofindia.indiatimes.com/india/isros-record-satellites-launch-10-top-facts/articleshow/57159213.cms|title=ISRO's record satellites' launch: 10 top facts|work=The Times of India|access-date=15 February 2017|archive-date=16 February 2017|archive-url=https://web.archive.org/web/20170216070423/http://timesofindia.indiatimes.com/india/isros-record-satellites-launch-10-top-facts/articleshow/57159213.cms|url-status=live}}</ref> until 24 January 2021, when [[SpaceX]] launched the Transporter-1 mission on a [[Falcon 9]] rocket carrying 143 satellites into orbit.<ref>{{cite web |last1=Wattles |first1=Jackie |title=SpaceX launches 143 satellites on one rocket in record-setting mission |url=https://www.cnn.com/2021/01/24/tech/spacex-rideshare-transporter-mission-scn/index.html |website=CNN |date=24 January 2021 |access-date=24 January 2021 |archive-date=24 January 2021 |archive-url=https://web.archive.org/web/20210124154743/https://www.cnn.com/2021/01/24/tech/spacex-rideshare-transporter-mission-scn/index.html |url-status=live }}</ref>

Payloads can be integrated in tandem configuration employing a Dual Launch Adapter.<ref>{{cite web|url=https://www.isro.gov.in/sites/default/files/galleries/%E0%A4%AA%E0%A5%80%E0%A4%8F%E0%A4%B8%E0%A4%8F%E0%A4%B2%E0%A4%B5%E0%A5%80%20-%E0%A4%B8%E0%A5%8035%20/%E0%A4%B8%E0%A5%8D%E0%A4%95%E0%A5%88%E0%A4%9F%E0%A4%B8%E0%A5%88%E0%A4%9F-1%20%E0%A4%97%E0%A5%88%E0%A4%B2%E0%A4%B0%E0%A5%80/scatsatspacecraftintegratedwithpslv-c35withtwohalvesoftheheatshieldsseen.jpg|title=PSLV C35 / Scatsat-1 with Dual Launch Adapter|access-date=19 December 2017|archive-date=22 December 2017|archive-url=https://web.archive.org/web/20171222051331/https://www.isro.gov.in/sites/default/files/galleries/%E0%A4%AA%E0%A5%80%E0%A4%8F%E0%A4%B8%E0%A4%8F%E0%A4%B2%E0%A4%B5%E0%A5%80%20-%E0%A4%B8%E0%A5%8035%20/%E0%A4%B8%E0%A5%8D%E0%A4%95%E0%A5%88%E0%A4%9F%E0%A4%B8%E0%A5%88%E0%A4%9F-1%20%E0%A4%97%E0%A5%88%E0%A4%B2%E0%A4%B0%E0%A5%80/scatsatspacecraftintegratedwithpslv-c35withtwohalvesoftheheatshieldsseen.jpg|url-status=live}}</ref><ref>{{cite web|url=https://twitter.com/103ISC/status/684377754599477248|title=Here's the #103ISC Official Newsletter 2nd edition brought by Journalism students and researchers. 2/2 @PIB_Indiapic.twitter.com/mLq9CZnY5T|last=Cong|first=Indian Science|date=5 January 2016|website=@103ISC|access-date=2017-12-19|archive-date=11 January 2022|archive-url=https://web.archive.org/web/20220111190506/https://twitter.com/103ISC/status/684377754599477248|url-status=live}}</ref> Smaller payloads are also placed on equipment deck and customized payload adapters.<ref>{{cite journal|url=https://www.ijsr.net/archive/v7i11/ART20192415.pdf|title=Research on PSLV-C37 Launcher by ISRO|author=Aisha Nazeer|access-date=13 May 2023|journal=International Journal of Science and Research|volume=7 |number=11|date=November 2018}}</ref>

== Development ==
[[File:PSLV-C11 Strapon01.jpg|thumb|290px|left|PSLV-C11 strap-on]]

Studies by the PSLV Planning group under [[S. Srinivasan|S Srinivasan]] to develop a vehicle capable of delivering a 600&nbsp;kg payload to a 550&nbsp;km [[sun-synchronous orbit]] from [[Satish Dhawan Space Centre|SHAR]] began in 1978.<ref>{{Cite book|title=Ready to Fire: How India and I survived the ISRO Spy case|publisher=Bloomsbury Publishing|year=2018|pages=203}}</ref><ref>{{Cite book|title=From Fishing Hamlet to Red Planet|publisher=ISRO|pages=173}}</ref> Among 35 proposed configurations, four were picked; by November 1980, a vehicle configuration with two strap-ons on a core booster (S80) with 80 tonne solid propellant loading each, a liquid stage with 30 tonne propellant load (L30), and an upper stage called the Perigee-Apogee System (PAS) was being considered.<ref>{{cite news|url=https://books.google.com/books?id=IbbMj56ht8sC&pg=PA215|title=Indian ambitions in space go sky-high|date=22 January 1981|publisher=New Scientist|page=215|access-date=30 December 2018|archive-date=10 October 2022|archive-url=https://web.archive.org/web/20221010090941/https://books.google.com/books?id=IbbMj56ht8sC&pg=PA215|url-status=live}}</ref><ref name=":1">{{cite book|title=A brief history of rocketry in ISRO|last1=Rao|first1=P.V. Monoranjan|last2=Radhakrishnan|first2=Paramaswaran|publisher=Orient Blackswan|year=2012 |isbn=978-8173717642|pages=215}}</ref><ref name=":3">{{cite book|title=From fishing hamlet to red planet|publisher=Harpercollins|year=2015|isbn=978-9351776895|editor-last=Rao|editor-first=P.V. Manoranjan |chapter=2.6 PSLV: The workhorse of ISRO by N. Narayanamoorthy}}</ref><ref>{{cite book|title=Reach For the Stars: The Evolution of India's Rocket Programme|last=Raj|first=Gopal|publisher=Viking|year=2000 |isbn=978-0670899500|chapter=8. PSLV: Achieving Operational Launch Capability|quote=About a year later, an important change was made, with the solid fourth stage being substituted by a liquid stage. This change was considered necessary since the accuracy with which the IRS satellites had to be put into orbit — within 15 km in terms of orbital height and within 0.1° of the desired orbital inclination — could not be achieved with a solid stage.}}</ref>

By 1981, confidence grew in [[Remote sensing satellites|remote sensing spacecraft]] development with the launch of [[Bhaskara (satellite)|Bhaskara-1]], and the PSLV project objectives were upgraded to have the vehicle deliver a 1000&nbsp;kg payload into a 900&nbsp;km [[Sun-synchronous orbit|SSO]]. As technology transfer of [[Viking (rocket engine)|Viking]] rocket engine firmed up, a new lighter configuration with the inclusion of a liquid powered stage was selected.<ref>{{Cite book|title=Ready To Fire: How India and I Survived the ISRO Spy Case|publisher=Bloomsbury Publishing|year=2018|pages=207–208}}</ref> Funding was approved in July 1982 for the finalized design, employing a single large S125 solid core as first stage with six 9 tonne strap-ons (S9) derived from the [[Satellite Launch Vehicle|SLV-3]] first stage, liquid fueled second stage (L33), and two solid upper stages (S7 and S2.) This configuration needed further improvement to meet the orbital injection accuracy requirements of IRS satellites, and hence, the solid terminal stage (S2) was replaced with a pressure fed liquid fueled stage (L1.8 or LUS) powered by twin engines derived from roll control engines of the first stage. Apart from increasing precision, liquid upper stage also absorbed any deviation in performance of solid third stage. The final configuration of [[PSLV-D1]] to fly in 1993 was (6 × S9 + S125) + L37.5 + S7 + L2.<ref name=":1"/><ref name=":3"/>

The [[inertial navigation system]]s are developed by [[ISRO Inertial Systems Unit]] (IISU) at [[Thiruvananthapuram]]. The liquid propulsion for the second and fourth stages of the PSLV as well as the [[Reaction control system]]s (RCS) are developed by the [[Liquid Propulsion Systems Centre]] (LPSC) at [[Valiamala]] near [[Thiruvananthapuram]], [[kerala]]. The solid [[Solid-propellant rocket|propellant motor]]s are processed at [[Satish Dhawan Space Centre]] (SHAR) at [[Sriharikota]], [[Andhra Pradesh]], which also carries out launch operations. The aerodynamic characterization research was conducted at the [[National Aerospace Laboratories]]' 1.2m Trisonic Wind Tunnel Facility.<ref>{{Cite web |date=2022-06-06 |title=Bengaluru: 1.2m trisonic wind tunnel at National Aerospace Laboratories completes 55 years of service |url=https://www.aninews.in/news/national/general-news/bengaluru-12m-trisonic-wind-tunnel-at-national-aerospace-laboratories-completes-55-years-of-service20220606001500/ |access-date=2024-11-22 |website=ANI |language=en}}</ref>

The PSLV was first launched on 20 September 1993.<ref>{{Cite web |title=PSLV - ISRO |url=https://www.isro.gov.in/launchers/pslv |access-date=2022-03-09 |website=www.isro.gov.in |archive-date=9 February 2020 |archive-url=https://web.archive.org/web/20200209203227/https://www.isro.gov.in/launchers/pslv |url-status=live }}</ref><ref name=":4" /> The first and second stages performed as expected, but an [[Spacecraft attitude control|attitude control]] problem led to the collision of the second and third stages at separation, and the payload failed to reach orbit.<ref>{{cite web|title=India (Launchers)|url=http://claudelafleur.qc.ca/Indians-launchers.html|publisher=Spacecraft Encyclopedia|access-date=12 November 2014|archive-date=20 May 2016|archive-url=https://web.archive.org/web/20160520142430/http://claudelafleur.qc.ca/Indians-launchers.html|url-status=live}}</ref> After this initial setback, the PSLV successfully completed its second mission in 1994.<ref>{{cite web|title=PSLV (1)|url=http://space.skyrocket.de/doc_lau_det/pslv_1.htm|publisher=Gunter's Space Page|access-date=12 November 2014|archive-date=5 December 2020|archive-url=https://web.archive.org/web/20201205170455/https://space.skyrocket.de/doc_lau_det/pslv_1.htm|url-status=live}}</ref> The fourth launch of PSLV suffered a partial failure in 1997, leaving its payload in a lower than planned orbit. In November 2014, the PSLV had launched 34 times with no further failures.<ref>{{cite web|title=PSLV|url=http://space.skyrocket.de/doc_lau/pslv.htm|website=Gunter's Space Page|access-date=12 November 2014|archive-date=24 July 2011|archive-url=https://web.archive.org/web/20110724081813/http://space.skyrocket.de/doc_lau/pslv.htm|url-status=live}}</ref> (Although launch 41: August 2017 PSLV-C39 was unsuccessful.<ref name="pslv"/>)

PSLV continues to support Indian and foreign satellite launches especially for [[low Earth orbit]] (LEO) satellites. It has undergone several improvements with each subsequent version, especially those involving thrust, efficiency as well as weight. In November 2013, it was used to launch the [[Mars Orbiter Mission]], India's first interplanetary probe.<ref>{{Cite web|url=http://www.isro.org/satellites/mars-orbiter-spacecraft.aspx|title=ISRO - Mars Orbiter Mission|access-date=2014-04-08|archive-date=27 October 2014|archive-url=https://web.archive.org/web/20141027123201/http://www.isro.org/satellites/mars-orbiter-spacecraft.aspx|url-status=live}}</ref>

In June 2018, the Union Cabinet approved {{INRconvert|6131|c|lk=on|year=2020}} for 30 operational flights of the PSLV scheduled to take place between 2019 and 2024.<ref>{{cite web|title=Government approves Rs 10,000-crore continuation programmes for PSLV, GSLV|url=https://economictimes.indiatimes.com/news/science/government-approves-rs-10000-crore-continuation-programmes-for-pslv-gslv/articleshow/64483323.cms|publisher=The Economic Times|date=7 June 2018|access-date=8 June 2018|archive-date=8 June 2018|archive-url=https://web.archive.org/web/20180608035934/https://economictimes.indiatimes.com/news/science/government-approves-rs-10000-crore-continuation-programmes-for-pslv-gslv/articleshow/64483323.cms|url-status=live}}</ref>

ISRO is working towards handing over the production and operation of PSLV to private industry through a joint venture.<ref>{{Cite web |title=Press Release - NSIL signs Contract with HAL (lead member of HAL-L&T consortium) for production of 05 nos of PSLV-XL |url=https://www.nsilindia.co.in/sites/default/files/Press%20Release-%20Contract%20signed%20for%20production%20of%2005%20nos%20PSLV-XL.pdf |archive-url=https://web.archive.org/web/20220909125437/https://www.nsilindia.co.in/sites/default/files/Press%20Release-%20Contract%20signed%20for%20production%20of%2005%20nos%20PSLV-XL.pdf |archive-date=9 September 2022}}</ref> On 16 August 2019, [[NewSpace India Limited]] issued an [[invitation to tender]] for manufacturing PSLV entirely by private industries.<ref>{{Cite news |last=D.s |first=Madhumathi |date=2019-08-16 |title=ISRO's business arm begins search for PSLV makers |language=en-IN |work=The Hindu |url=https://www.thehindu.com/news/national/new-isro-arm-begins-search-for-pslv-makers/article29112870.ece |access-date=2022-09-09 |issn=0971-751X |archive-date=9 September 2022 |archive-url=https://web.archive.org/web/20220909133320/https://www.thehindu.com/news/national/new-isro-arm-begins-search-for-pslv-makers/article29112870.ece |url-status=live }}</ref><ref>{{Cite web |author=Chethan Kumar |date=Aug 27, 2021 |title=Adani, L&T among those in race for PSLV contract {{!}} India News - Times of India |url=https://timesofindia.indiatimes.com/india/adani-lt-in-race-for-deal-to-make-space-launch-vehicles/articleshow/85674630.cms |access-date=2022-09-09 |website=The Times of India |language=en |archive-date=9 September 2022 |archive-url=https://web.archive.org/web/20220909133322/https://timesofindia.indiatimes.com/india/adani-lt-in-race-for-deal-to-make-space-launch-vehicles/articleshow/85674630.cms |url-status=live }}</ref> On 5 September 2022, [[NewSpace India Limited]] signed a contract with [[Hindustan Aeronautics Limited]] and [[Larsen & Toubro]] led conglomerate for the production of five PSLV-XL launch vehicles after they won competitive bidding. Under this contract, they have to deliver their first PSLV-XL within 24 months and the remaining four vehicles every six months.<ref>{{Cite news |title=HAL-L&T to build five PSLV rockets, bags Rs 860 crore deal from NSIL for the project |work=The Economic Times |url=https://economictimes.indiatimes.com/industry/indl-goods/svs/engineering/hal-lt-to-build-five-pslv-rockets-bags-rs-860-crore-deal-from-nsil-for-the-project/articleshow/93980649.cms |access-date=2022-09-09 |archive-date=9 September 2022 |archive-url=https://web.archive.org/web/20220909133332/https://economictimes.indiatimes.com/industry/indl-goods/svs/engineering/hal-lt-to-build-five-pslv-rockets-bags-rs-860-crore-deal-from-nsil-for-the-project/articleshow/93980649.cms |url-status=live }}</ref><ref>{{Cite news|date=2017-10-26|title=ISRO looks at JV for PSLV manufacture; launch to be privatized by 2020|publisher=Geospatial World|url=https://www.geospatialworld.net/blogs/isro-looks-jv-pslv-manufacture-launch-privatized-2020/|access-date=2017-10-26|archive-date=16 November 2017|archive-url=https://web.archive.org/web/20171116011358/https://www.geospatialworld.net/blogs/isro-looks-jv-pslv-manufacture-launch-privatized-2020/|url-status=live}}</ref><ref>{{Cite web |author=Chethan Kumar |date=Apr 9, 2022 |title=Hal-l&t Wins Over 824-cr Contract For Making 5 Pslvs {{!}} India News - Times of India |url=https://timesofindia.indiatimes.com/india/hal-lt-wins-over-824-cr-contract-for-making-5-pslvs/articleshow/90736339.cms |access-date=2022-09-09 |website=The Times of India |language=en |archive-date=9 September 2022 |archive-url=https://web.archive.org/web/20220909133320/https://timesofindia.indiatimes.com/india/hal-lt-wins-over-824-cr-contract-for-making-5-pslvs/articleshow/90736339.cms |url-status=live }}</ref>

== Vehicle description ==
The PSLV has four stages, using solid and liquid propulsion systems alternately.

=== First stage (PS1) ===
[[File:PSLV-C44 Integrated upto First Stage inside Mobile Service Tower.jpg|thumb|left|375x375px|[[PSLV-C44]] first stage inside Mobile Service Tower]]

The first stage, one of the largest [[solid rocket boosters]] in the world, carries {{cvt|138|MT}} of [[hydroxyl-terminated polybutadiene]]-bound (HTPB) propellant and develops a maximum thrust of about {{cvt|4800|kN}}. The {{cvt|2.8|m}} diameter motor case is made of [[maraging steel]] and has an empty mass of {{cvt|30200|kg}}.<ref name="sf101">{{cite web|url=http://www.spaceflight101.com/pslv-launch-vehicle-information.html|title=PSLV Launch Vehicle Information|publisher=Spaceflight 101|access-date=February 20, 2015|archive-url=https://web.archive.org/web/20150924115759/http://www.spaceflight101.com/pslv-launch-vehicle-information.html|archive-date=24 September 2015|url-status=dead}}</ref>

[[Aircraft principal axes|Pitch]] and [[Yaw (rotation)|yaw]] control during first stage flight is provided by the Secondary Injection Thrust Vector Control (SITVC) System, which injects an [[aqueous solution]] of [[strontium perchlorate]] into the [[S139 Booster|S139]] exhaust divergent from a ring of 24 injection ports to produce asymmetric thrust. The solution is stored in two cylindrical [[aluminium]] tanks strapped to the core solid rocket motor and pressurised with [[nitrogen]]. Underneath these two SITVC tanks, [[Roll program|Roll]] Control Thruster (RCT) modules with small bi-propellant (MMH/MON) liquid engine are also attached.<ref name=":4">{{Cite web|date=10 October 1993|title=Current Science (Volume 65 - Issue 07) PSLV-D1|url=https://www.currentscience.ac.in/Downloads/article_id_065_07_0522_0528_0.pdf|url-status=live|archive-url=https://web.archive.org/web/20200806072408/https://www.currentscience.ac.in/Downloads/article_id_065_07_0522_0528_0.pdf|archive-date=6 August 2020|access-date=20 December 2019}}</ref>

On the PSLV-G and PSLV-XL, first stage thrust is augmented by six [[strap-on booster|strap-on solid boosters]]. Four boosters are ground-lit and the remaining two ignite 25 seconds after launch. The solid boosters carry {{cvt|9|MT}} or {{cvt|12|MT}} (for PSLV-XL configuration) propellant and produce {{cvt|510|kN}} and {{cvt|719|kN}} thrust respectively. Two strap-on boosters are equipped with SITVC for additional attitude control.<ref name="sf101"/> The PSLV-CA uses no strap-on boosters.

First stage separation is aided by four pairs of retro-rockets installed on inter-stage (1/2L). During staging, these eight rockets help push away the spent stage away from second stage.<ref name=":5">{{cite web|url=https://www.isro.gov.in/sites/default/files/flipping_book/PSLV-C1/files/assets/basic-html/page-3.html|title=PSLV-C1|website=isro.gov.in|access-date=22 February 2020|archive-date=6 August 2020|archive-url=https://web.archive.org/web/20200806063834/https://www.isro.gov.in/sites/default/files/flipping_book/PSLV-C1/files/assets/basic-html/page-3.html|url-status=live}}</ref>

=== Second stage (PS2) ===
[[File:PSLV C50 second stage with Vikas engine.jpg|left|thumb|250x250px|PSLV-C50 second stage with [[VIKAS engine|Vikas engine]]]]

The second stage is powered by a single [[Vikas (rocket engine)|Vikas engine]] and carries {{cvt|41.5|MT}} of [[Earth]] store-able liquid propellant{{spaced ndash}}[[unsymmetrical dimethylhydrazine]] (UDMH) as fuel and [[nitrogen tetroxide]] (N<sub>2</sub>O<sub>4</sub>) as oxidiser in two tanks separated by a common bulkhead.<ref name=":4"/> It generates a maximum thrust of {{cvt|800|kN}}. The engine is [[gimbal]]ed (±4°) in two planes to provide pitch and yaw control by two actuators, while roll control is provided by a Hot gas Reaction Control Motor (HRCM) that ejects hot gases diverted from gas generator of Vikas engine.<ref>{{cite web|url=https://www.isro.gov.in/sites/default/files/flipping_book/10-Space_India-1_1990/files/assets/basic-html/page-7.html|title=Space India 1/1990|website=isro.gov.in|access-date=22 February 2020|archive-date=6 August 2020|archive-url=https://web.archive.org/web/20200806054903/https://www.isro.gov.in/sites/default/files/flipping_book/10-Space_India-1_1990/files/assets/basic-html/page-7.html|url-status=live}}</ref>

On inter-stage (1/2U) of PS2, there are two pairs of ullage rockets to maintain positive acceleration during PS1/PS2 staging and also two pairs of retro-rockets to help push away spent stage during PS2/PS3 staging.<ref name=":5"/>

Second stage also carries some quantity of water in a [[toroid]]al tank at its bottom.<ref name=":6">{{cite web|url=https://www.isro.gov.in/sites/default/files/flipping_book/PSLV-C8/files/assets/common/downloads/publication.pdf|url-status=dead|title=PSLV C8 / AGILE brochure|access-date=23 February 2020|archive-date=23 February 2020|archive-url=https://web.archive.org/web/20200223011646/https://www.isro.gov.in/sites/default/files/flipping_book/PSLV-C8/files/assets/common/downloads/publication.pdf}}</ref> Water spray is used to cool hot gases from Vikas' gas generator to about 600&nbsp;°C before entering turbopump. Propellant and water tanks of second stage are pressurized by [[Helium]].<ref>{{Cite journal |title=Development & qualification of Titanium Alloy High-Pressure Gas Bottles for PSLV second Stage |url=http://adsabs.harvard.edu/full/1999ESASP.430..559T |url-status=live |access-date=2021-04-07 |journal=Cooperation in Space |bibcode=1999ESASP.430..559T |last1=Thomas |first1=George |last2=Pant |first2=Bhanu |last3=Ganesan |first3=R. |last4=Singh |first4=S. K. |last5=Sinha |first5=P. P. |year=1999 |volume=430 |page=559 |archive-date=11 November 2020 |archive-url=https://web.archive.org/web/20201111223537/http://adsabs.harvard.edu/full/1999ESASP.430..559T }}</ref><ref>{{cite book |title=Envisioning An Empowered nation|isbn=978-0070531543|page=40|last=Sivathanu Pillai|first=A.|year=2004|publisher=Tata McGraw-Hill Publishing Company }}</ref><ref>{{Cite web|date=April 1990|title=Space India Jan-Mar 1990|url=https://www.isro.gov.in/sites/default/files/flipping_book/10-Space_India-1_1990/files/assets/common/downloads/publication.pdf|url-status=live|archive-url=https://web.archive.org/web/20210407195425/https://www.isro.gov.in/sites/default/files/flipping_book/10-Space_India-1_1990/files/assets/common/downloads/publication.pdf|archive-date=7 April 2021|access-date=8 April 2021}}</ref>

=== Third stage (PS3) ===
[[File:PSLV C45 EMISAT campaign 09.jpg|left|thumb|375x375px|Third and fourth stages of [[PSLV-C45]]]]

The third stage uses {{cvt|7.6|MT}} of HTPB solid propellant and produces a maximum thrust of {{cvt|250|kN}}. Its burn duration is 113.5 seconds. It has a [[Kevlar]]-[[polyamide]] fibre case and a submerged nozzle equipped with a flex-bearing-seal gimbaled nozzle with ±2° [[Thrust-vectoring|thrust vector]] for pitch and yaw control. Roll control is provided by the fourth stage [[reaction control system]] (RCS) during thrust phase as well as during combined-coasting phase under which burnt-out PS3 remains attached to PS4.<ref name="sf101"/><ref name="CurrSci_V119_I6">{{Cite web |date=25 September 2015 |title=PSLV-C25: the vehicle that launched the Indian Mars Orbiter |url=https://www.currentscience.ac.in/Volumes/109/06/1055.pdf |archive-url=https://web.archive.org/web/20151224184646/http://www.currentscience.ac.in/Volumes/109/06/1055.pdf |archive-date=24 December 2015 |website=Current Science}}</ref>

=== Fourth stage (PS4) ===
The fourth stage is powered by regeneratively cooled twin engines,<ref>{{cite web|url=http://asaco.in/aerospace/sub-systems-for-aerospace/|title=ASACO sub-systems for space.|archive-url=https://web.archive.org/web/20171211095555/http://asaco.in/aerospace/sub-systems-for-aerospace/|archive-date=11 December 2017|url-status=live|access-date=16 October 2018}}</ref> burning [[monomethylhydrazine]] (MMH) and [[mixed oxides of nitrogen]] (MON). Each pressure fed engine generates {{cvt|7.4|kN}} thrust and is gimbaled (±3°) to provide pitch, yaw and roll control during powered flight. Coast phase attitude control is provided by six 50N RCS thrusters.<ref>{{cite journal|last1=Ramakrishnan|first1=S.|last2=Somanath|first2=S.|last3=Balakrishnan|first3=S. S.|date=2002-01-01|title=Multi-Orbit Mission by PSLV-C3 and Future Launch Opportunities|journal=Iaf Abstracts|pages=936|bibcode=2002iaf..confE.936R}}</ref> The stage is pressurized by [[helium]]<ref>{{Cite web|title=Latest Volume14-Issue21 News, Photos, Latest News Headlines about Volume14-Issue21|url=https://frontline.thehindu.com/magazine/issue/vol14-21/|access-date=2021-04-07|website=Frontline|language=en|archive-date=7 May 2021|archive-url=https://web.archive.org/web/20210507005441/https://frontline.thehindu.com/magazine/issue/vol14-21/|url-status=live}}</ref> and carries {{cvt|1600|kg}} to {{cvt|2500|kg}} of propellant depending on the mission requirements. PS4 has three variants L1.6, L2.0 and L2.5 based on propellant tank capacity.<ref name="sport"/><ref>{{Cite web |title=Signatures, Newsletter of the Indian Society of Remote Sensing – Ahmedabad Chapter. Volume: 24, No.2, April- June 2012 |url=https://www.sac.gov.in/SAC_Industry_Portal/publication/newsletter/Signatures_RISAT.pdf |archive-url=https://web.archive.org/web/20211221142837/https://www.sac.gov.in/SAC_Industry_Portal/publication/newsletter/Signatures_RISAT.pdf |archive-date=21 December 2021 |access-date=31 July 2023 |quote=The fourth stage has three variants designated as L1.6, L2.0 and L2.5 based on the propellant loading capacity of 1.6t, 2t and 2.5t respectively required for a particular mission.}}</ref>

On PSLV-C29/TeLEOS-1 mission, the fourth stage demonstrated re-ignition capability for the first time which was used in many subsequent flights to deploy payloads in multiple orbits on a single campaign.<ref name=":12">{{cite web|title=ISRO Successfully Tests Multiple Burn Fuel Engine During Launch of Six Singaporean Satellites|url=http://www.newindianexpress.com/states/andhra_pradesh/ISRO-Successfully-Tests-Multiple-Burn-Fuel-Engine-During-Launch-of-Six-Singaporean-Satellites/2015/12/16/article3180961.ece|access-date=16 December 2015|archive-date=3 May 2016|archive-url=https://web.archive.org/web/20160503044453/http://www.newindianexpress.com/states/andhra_pradesh/ISRO-Successfully-Tests-Multiple-Burn-Fuel-Engine-During-Launch-of-Six-Singaporean-Satellites/2015/12/16/article3180961.ece|url-status=dead}}</ref>

As a [[space debris]] mitigation measure, PSLV fourth stage gets [[Passivation (spacecraft)|passivated]] by venting pressurant and propellant vapour after achieving main mission objectives. Such passivation prevents any unintentional fragmentation or explosion due to stored internal energy.<ref>{{Cite journal|last1=Adimurthy|first1=V.|last2=Ganeshan|first2=A.S.|date=February 2006|title=Space debris mitigation measures in India|url=https://linkinghub.elsevier.com/retrieve/pii/S0094576505002961|journal=Acta Astronautica|language=en|volume=58|issue=3|pages=168–174|doi=10.1016/j.actaastro.2005.09.002|bibcode=2006AcAau..58..168A|access-date=26 December 2021|archive-date=12 April 2022|archive-url=https://web.archive.org/web/20220412004038/https://linkinghub.elsevier.com/retrieve/pii/S0094576505002961|url-status=live}}</ref><ref>{{Cite journal|last=Bonnal|first=C|date=2007-06-01|title=Design and operational practices for the passivation of spacecraft and launchers at the end of life|url=http://journals.sagepub.com/doi/10.1243/09544100JAERO231|journal=Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering|language=en|volume=221|issue=6|pages=925–931|doi=10.1243/09544100JAERO231|s2cid=110656798|issn=0954-4100}}</ref><ref>{{Cite web|title=Indian Presentation to the 47th Session of Scientific and Technical Subcommittee of United Nations Committee on the Peaceful Uses of Outer Space Agenda 8 'Space Debris Activities in India'|url=https://www.unoosa.org/pdf/pres/stsc2010/tech-33.pdf |archive-url=https://ghostarchive.org/archive/20221009/https://www.unoosa.org/pdf/pres/stsc2010/tech-33.pdf |archive-date=2022-10-09|url-status=live}}</ref>

The [[niobium alloy]] nozzle used on twin engines of fourth stage is expected to be replaced by lighter, [[silicon carbide]] coated [[Reinforced carbon–carbon|carbon–carbon]] nozzle divergent. The new nozzle was hot tested at facilities of [[ISRO Propulsion Complex|IPRC, Mahendragiri]] in March and April 2024. This substitution should increase payload capacity of PSLV by {{Convert|15|kg|lb}}.<ref>{{Cite web |title=ISRO Develops Lightweight Carbon-Carbon Nozzle for Rocket Engines, Enhancing Payload Capacity |url=https://www.isro.gov.in/ISRO_Develops_Lightweight_Carbon_Carbon_Nozzle_for_Rocket_Engines.html |archive-url=https://web.archive.org/web/20240419183918/https://www.isro.gov.in/ISRO_Develops_Lightweight_Carbon_Carbon_Nozzle_for_Rocket_Engines.html |archive-date=19 April 2024 |access-date=2024-04-21 |website=www.isro.gov.in}}</ref> ISRO also replaced imported [[Niobium|Columbium]] materials in the engine nozzle divergent  with [[Stellite]], which resulted in cost savings of 90%. The newly modified engines were tested at IPRC in April 2025.<ref>{{Cite web |title=ISRO Successfully qualifies fourth stage engine of PSLV with Satellite Nozzle Divergent |url=https://www.isro.gov.in/ISRO_Successfully_qualifies_fourth_stage_engine_of_PSLV_with_Satellite_Nozzle_Divergent.html |archive-url=http://web.archive.org/web/20250418060419/https://www.isro.gov.in/ISRO_Successfully_qualifies_fourth_stage_engine_of_PSLV_with_Satellite_Nozzle_Divergent.html |archive-date=2025-04-18 |access-date=2025-04-18 |website=www.isro.gov.in |language=en}}</ref>

ISRO successfully completed 665-second hot test of [[3D printed]] PS4 engine, produced by Wipro 3D through [[selective laser melting]]. A total of 19 weld joints were eliminated through this process while engine's 14 components were reduced to one piece. It saved 60% of the production time and drastically decreased the amount of raw materials used per engine, from 565&nbsp;kg to 13.7&nbsp;kg of metal powder.<ref>{{Cite news |date=2024-05-11 |title=With 3D-printed rocket engine, Isro adds another feather to cap |url=https://timesofindia.indiatimes.com/india/with-3d-printed-rocket-engine-isro-adds-another-feather-to-cap/articleshow/110019883.cms |access-date=2024-05-13 |work=The Times of India |issn=0971-8257}}</ref>

==== PS4 stage as orbital platform ====
{{Main|PSLV Orbital Experiment Module}}
PS4 has carried hosted payloads like AAM on PSLV-C8,<ref name=":6"/> [[Luxspace|Rubin 9.1]]/[[Rubin 9.2]] on PSLV-C14<ref>{{cite web|url=https://www.isro.gov.in/sites/default/files/flipping_book/PSLV-C14/files/assets/common/downloads/publication.pdf|url-status=dead|title=PSLV C14/Oceansat-2 brochure|access-date=23 February 2020|archive-date=6 August 2020|archive-url=https://web.archive.org/web/20200806094152/https://www.isro.gov.in/sites/default/files/flipping_book/PSLV-C14/files/assets/common/downloads/publication.pdf}}</ref> and mRESINS on PSLV-C21.<ref>{{cite web |url=https://www.dos.gov.in/sites/default/files/flipping_book/Space%20India%20July%2012-Aug%2013/files/assets/common/downloads/Space%20India%20July%2012-Aug%2013.pdf |url-status=dead |title=Space-India July 2012 to August 2013 |access-date=23 February 2020 |archive-date=6 August 2020 |archive-url=https://web.archive.org/web/20200806152719/https://www.dos.gov.in/sites/default/files/flipping_book/Space%20India%20July%2012-Aug%2013/files/assets/common/downloads/Space%20India%20July%2012-Aug%2013.pdf }}</ref> But now, PS4 is being augmented to serve as a long duration orbital platform after completion of primary mission. PS4 Orbital Platform (PS4-OP) will have its own power supply, telemetry package, data storage and attitude control for hosted payloads.<ref>{{cite web|url=http://www.unoosa.org/documents/pdf/copuos/stsc/2019/tech-55E.pdf |archive-url=https://ghostarchive.org/archive/20221009/http://www.unoosa.org/documents/pdf/copuos/stsc/2019/tech-55E.pdf |archive-date=2022-10-09 |url-status=live|title=Opportunities for science experiments in the fourth stage of India's PSLV|date=21 February 2019}}</ref><ref>{{cite web|url=https://www.isro.gov.in/sites/default/files/orbital_platform-_ao.pdf|url-status=dead|title=Announcement of Opportunity (AO) for Orbital platform: an avenue for in-orbit scientific experiments|date=15 June 2019|access-date=23 February 2020|archive-date=6 August 2020|archive-url=https://web.archive.org/web/20200806072033/https://www.isro.gov.in/sites/default/files/orbital_platform-_ao.pdf}}</ref><ref>{{cite news|url=https://timesofindia.indiatimes.com/india/2-days-after-space-station-news-isro-calls-for-docking-experiments-on-pslv-stage-4/articleshow/69800354.cms|title=2 days after Space Station news, Isro calls for "docking experiments" on PSLV stage-4|first=Chethan|last=Kumar|work=The Times of India|date=15 June 2019 |access-date=23 February 2020|archive-date=24 August 2019|archive-url=https://web.archive.org/web/20190824073052/https://timesofindia.indiatimes.com/india/2-days-after-space-station-news-isro-calls-for-docking-experiments-on-pslv-stage-4/articleshow/69800354.cms|url-status=live}}</ref>

On [[PSLV-C37]] and [[PSLV-C38]] campaigns,<ref>{{Cite web |title=In-situ observations of rocket burn induced modulations of the top side ionosphere using the IDEA payload on-board the unique orbiting experimental platform (PS4) of the Indian Polar Orbiting Satellite Launch Vehicle mission - ISRO |url=https://www.isro.gov.in/situ-observations-of-rocket-burn-induced-modulations-of-top-side-ionosphere-using-idea-payload-board |access-date=2022-06-27 |website=www.isro.gov.in |language=en |archive-date=21 September 2022 |archive-url=https://web.archive.org/web/20220921000216/https://www.isro.gov.in/situ-observations-of-rocket-burn-induced-modulations-of-top-side-ionosphere-using-idea-payload-board |url-status=live }}</ref> as a demonstration PS4 was kept operational and monitored for over ten orbits after delivering spacecraft.<ref>{{cite web |url=https://www.isro.gov.in/sites/default/files/article-files/node/9805/annualreport2017-18.pdf|title=Department of Space Annual Report 2017-18|url-status=live|archive-url=https://web.archive.org/web/20180213093132/https://www.isro.gov.in/sites/default/files/article-files/node/9805/annualreport2017-18.pdf|archive-date=13 February 2018}}</ref><ref>{{cite web|url=https://timesofindia.indiatimes.com/india/in-a-first-isro-will-make-dead-rocket-stage-alive-in-space-for-experiments/articleshow/67067817.cms|title=In a first, ISRO will make dead rocket stage "alive" in space for experiments|first=Surendra|last=Singh|work=The Times of India|date=16 December 2018|access-date=23 February 2020|archive-date=8 November 2020|archive-url=https://web.archive.org/web/20201108132514/https://timesofindia.indiatimes.com/india/in-a-first-isro-will-make-dead-rocket-stage-alive-in-space-for-experiments/articleshow/67067817.cms|url-status=live}}</ref><ref>{{cite web|url=https://www.deccanchronicle.com/science/science/200617/isro-to-lower-rockets-altitude.html|title=Isro to lower rocket's altitude|last=rajasekhar|first=pathri|publisher=Deccan Chronicle|date=2017-06-20|access-date=23 February 2020|archive-date=6 August 2020|archive-url=https://web.archive.org/web/20200806095054/https://www.deccanchronicle.com/science/science/200617/isro-to-lower-rockets-altitude.html|url-status=live}}</ref>

[[PSLV-C44]] was the first campaign where PS4 functioned as independent orbital platform for short duration as there was no on-board power generation capacity.<ref>{{cite news|last=Rajwi|first=Tiki|url=https://www.thehindu.com/news/national/kerala/pslv-lift-off-with-added-features/article25981654.ece|title=PSLV lift-off with added features|date=2019-01-12|newspaper=The Hindu|issn=0971-751X|access-date=23 February 2020|archive-date=6 August 2020|archive-url=https://web.archive.org/web/20200806161530/https://www.thehindu.com/news/national/kerala/pslv-lift-off-with-added-features/article25981654.ece|url-status=live}}</ref> It carried KalamSAT-V2 as a fixed payload, a 1U CubeSat by Space Kidz India based on [[Interorbital Systems]] kit.<ref>{{cite web|title=PSLV-C44 - ISRO|url=https://www.isro.gov.in/launcher/pslv-c44|access-date=26 June 2020|website=isro.gov.in|archive-date=17 January 2019|archive-url=https://web.archive.org/web/20190117013408/https://www.isro.gov.in/launcher/pslv-c44|url-status=dead}}</ref><ref>{{cite tweet|number=1088526772109422592|user=interorbital|title=Congratulations to ISRO and SpaceKidzIndia on getting their CubeSat into orbit! The students modified their IOS CubeSat kit, complete w/ their own experiments!|author=Interorbital Systems|date=25 January 2019}}</ref>

On [[PSLV-C45]] campaign, the fourth stage had its own power generation capability as it was augmented with an array of fixed [[solar cell]]s around PS4 propellant tank.<ref>{{cite web|url=https://spaceflightnow.com/2019/04/01/indian-military-satellite-20-more-planet-imaging-cubesats-aboard-successful-pslv-launch/|title=Indian military satellite, 20 more Planet imaging CubeSats launched by PSLV|last=Clark|first=Stephen|publisher=Spaceflight Now|access-date=2020-02-23|archive-date=6 April 2019|archive-url=https://web.archive.org/web/20190406042135/https://spaceflightnow.com/2019/04/01/indian-military-satellite-20-more-planet-imaging-cubesats-aboard-successful-pslv-launch/|url-status=live}}</ref> The three payloads hosted on PS4-OP were the Advanced Retarding Potential Analyzer for Ionospheric Studies (ARIS 101F) by [[IIST]],<ref>{{cite web|url=https://www.iist.ac.in/avionics/sudharshan.kaarthik|title=Department of Avionics, R. Sudharshan Kaarthik, Ph.D (Assistant Professor)|access-date=23 February 2020|archive-date=13 February 2020|archive-url=https://web.archive.org/web/20200213005932/https://www.iist.ac.in/avionics/sudharshan.kaarthik|url-status=live}}</ref> an experimental [[Automatic identification system|AIS]] payload by ISRO, and AISAT by [[Satellize]].<ref>{{cite web|url=https://satellize.com/index.php/exseed-sat-2/|title=Exseed Sat-2|publisher=Satellize|access-date=23 February 2020|archive-date=23 February 2020|archive-url=https://web.archive.org/web/20200223011624/https://satellize.com/index.php/exseed-sat-2/|url-status=live}}</ref> To function as orbital platform, fourth stage was put in [[Spin-stabilisation|spin-stabilized]] mode using its RCS thrusters.<ref>{{Cite web |date=16 June 2021 |title=Opportunity for Scientific Experiments on PSLV Upper Stage Orbital Platform |url=https://www.unoosa.org/documents/pdf/psa/hsti/Hyper-Microgravity_Webinar2021/Hyper-Microgravity_Webinar2021/9_RegionalActivities/R._Senan_Hypermicrogravity_ISRO.pdf |archive-url=https://ghostarchive.org/archive/20221009/https://www.unoosa.org/documents/pdf/psa/hsti/Hyper-Microgravity_Webinar2021/Hyper-Microgravity_Webinar2021/9_RegionalActivities/R._Senan_Hypermicrogravity_ISRO.pdf |archive-date=2022-10-09 |url-status=live}}</ref>

On the [[PSLV-C53]] campaign, the PS4-OP is referred to as the [[PSLV-C53#PSLV Orbital Experimental Module|PSLV Orbital Experimental Module (POEM)]], and it hosted six payloads. POEM was the first PSLV fourth stage based orbital platform to be actively stabilised using Helium based cold gas thrusters after the primary mission and stage passivization.<ref>{{Cite web |last=Kumar |first=Chethan |date=June 25, 2012 |title=Bengaluru's Digantara, Hyderabad startup Dhruva become first to get IN-SPACe authorisation |url=https://timesofindia.indiatimes.com/india/bengaluru-digantara-hyderabad-startup-dhruva-become-first-to-get-in-space-authorisation/articleshow/92460375.cms |url-status=live |archive-url=https://web.archive.org/web/20220625153537/https://timesofindia.indiatimes.com/india/bengaluru-digantara-hyderabad-startup-dhruva-become-first-to-get-in-space-authorisation/articleshow/92460375.cms |archive-date=2022-06-25 |access-date=2022-06-26 |website=The Times of India |language=en}}</ref><ref>{{Cite web |title=PSLV-C53/DS-EO mission |url=https://www.isro.gov.in/sites/default/files/article-files/pslv-c53-ds-eo-mission/pslv-c53-ds-eo-mission-brochure-english/brochure_pslv_c53-ds-eo_mission_english.pdf |archive-url=https://web.archive.org/web/20220705162540/https://www.isro.gov.in/sites/default/files/article-files/pslv-c53-ds-eo-mission/pslv-c53-ds-eo-mission-brochure-english/brochure_pslv_c53-ds-eo_mission_english.pdf |archive-date=5 July 2022}}</ref><ref>{{Cite web |title=పీఎస్‌ఎల్‌వీ-సి53లో నూతన సాంకేతికత |url=https://www.eenadu.net/telugu-news/related-stories/general/2505/122117906 |url-status=live |archive-url=https://web.archive.org/web/20220706195945/https://www.eenadu.net/telugu-news/related-stories/general/2505/122117906 |archive-date=2022-07-06 |access-date=2022-07-06 |website=EENADU |language=te}}</ref><ref>{{Cite web |author=News9 Staff |date=2022-09-08 |title=Har Ghar Tiranga happened in Antriksh. ISRO did hoist the Indian flag in Space! |url=https://www.news9live.com/india/har-ghar-tiranga-happened-in-antriksh-isro-did-hoist-the-indian-flag-in-space-194691 |access-date=2022-09-09 |website=NEWS9LIVE |language=en |archive-date=9 September 2022 |archive-url=https://web.archive.org/web/20220909095750/https://www.news9live.com/india/har-ghar-tiranga-happened-in-antriksh-isro-did-hoist-the-indian-flag-in-space-194691 |url-status=live }}</ref>

==== PS4 on RLV-OREX ====
The [[RLV Technology Demonstration Programme|Reusable Launch Vehicle Technology Demonstration program]] is an prototype [[spaceplane]] project currently being processed by ISRO. It is planned to use a GSLV, modified by replacing it's Cryogenic Upper Stage(CUS) with the PS-4 as the RLV would not required the excess thrust created by the CUS.<ref>{{Cite news |title=RLV re-entry mission to use GSLV with PSLV last stage; landing gear to change & more |url=https://timesofindia.indiatimes.com/india/rlv-re-entry-mission-to-use-gslv-with-pslv-last-stage-landing-gear-to-change-more/articleshow/111267553.cms |access-date=2024-06-26 |work=The Times of India |issn=0971-8257}}</ref><ref>{{Cite web |title=MSN |url=https://www.msn.com/en-in/news/other/rlv-re-entry-mission-to-use-gslv-with-pslv-last-stage-landing-gear-to-change-more/ar-BB1oSNaF |access-date=2024-06-26 |website=www.msn.com}}</ref>

=== Payload fairing ===
[[File:PSLV heat shield at HAL museum, Bengaluru (Ank Kumar) 01.jpg|left|thumb|PSLV heat shield at [[HAL Aerospace Museum]], [[Bengaluru]]]]
Payload fairing of PSLV, also referred as its "Heatshield" consists of a conical upper section with spherical nose-cap, a cylindrical middle section and a lower boat-tail section. Weighing {{Convert|1,182|kg|lb}}, it has 3.2 meter diameter and 8.3 meter height.<ref name="ODC2019">{{cite web|url=https://www.hou.usra.edu/meetings/orbitaldebris2019/orbital2019paper/pdf/6159.pdf |archive-url=https://ghostarchive.org/archive/20221009/https://www.hou.usra.edu/meetings/orbitaldebris2019/orbital2019paper/pdf/6159.pdf |archive-date=2022-10-09 |url-status=live|title=IRNSS-1H/PSLV-C39 Orbit Evolution and Re-entry Analysis|last=Singh|first=Satyendra|date=11 December 2019 |access-date=19 December 2019}}</ref> It has [[Isogrid]] construction and is made out of [[7075 aluminium alloy|7075 aluminum alloy]] with a 3&nbsp;mm thick steel nose-cap.<ref>{{cite web|last1=Ramamurti|first1=V|last2=Rajarajan|first2=S|last3=Rao|first3=G Venkateswara|date=Oct 2001|title=Dynamic studies of a typical payload fairing for different boat tail configurations|url=http://nopr.niscair.res.in/bitstream/123456789/24368/1/IJEMS%208%285%29%20247-254.pdf|url-status=live|archive-url=https://web.archive.org/web/20200806085530/http://nopr.niscair.res.in/bitstream/123456789/24368/1/IJEMS%208%285%29%20247-254.pdf|archive-date=6 August 2020}}</ref><ref>{{cite AV media|url=http://mmcr.iisc.ernet.in:8008/cgi-bin/nwayfiles.py?folder=Any+folder&date=2015-08-21&title=Any+title&presenter=Any+presenter&button=Search|title=Indigenous Development of Materials for Space Programme|date=21 August 2015|time=20 minutes 40 seconds|access-date=8 January 2020|archive-date=3 December 2020|archive-url=https://web.archive.org/web/20201203100310/http://mmcr.iisc.ernet.in:8008/cgi-bin/nwayfiles.py?folder=Any%2Bfolder&date=2015-08-21&title=Any%2Btitle&presenter=Any%2Bpresenter&button=Search|url-status=live}}</ref> The two halves of fairing are separated using a [[Pyrotechnics|pyrotechnic]] device based jettisoning system consisting of horizontal and lateral separation mechanisms.<ref>{{Cite web|last1=Chakraborty|first1=D|last2=Vasantha|first2=S|title=Aerodynamic simulation of heatshield separation on ground.|url=https://www.aero.iitb.ac.in/~debasis/assets/int/JP-int-2.pdf |archive-url=https://ghostarchive.org/archive/20221009/https://www.aero.iitb.ac.in/~debasis/assets/int/JP-int-2.pdf |archive-date=2022-10-09|url-status=live}}</ref> To protect the spacecraft from damage due to excessive acoustic loads during launch, the heatshield interior is lined with acoustic blankets.<ref name=":4" />

<!-- see https://www.isro.gov.in/launchers/pslv -->
{| class="wikitable" style="margin: 1em auto 1em auto;background:#fff; font-size:95%;width:60%"
|-
!
! Stage 1
! Stage 2
! Stage 3
! Stage 4
|-
! Pitch
| SITVC
| Engine Gimbal
| Nozzle Flex
| Engine Gimbal
|-
! Yaw
| SITVC
| Engine Gimbal
| Nozzle Flex
| Engine Gimbal
|-
! Roll
| RCT and SITVC in 2 PSOMs
| HRCM Hot Gas Reaction Control Motor
| PS4 RCS
| PS4 RCS
|}
{{Clear}}

== Variants ==
ISRO has envisaged a number of variants of PSLV to cater to different mission requirements. There are currently two operational versions of the PSLV — the core-alone (PSLV-CA) without strap-on motors, and the (PSLV-XL) version, with six extended length (XL) strap-on motors carrying 12 tonnes of HTPB based propellant each.<ref name=hi>{{cite news|url=http://www.thehindu.com/sci-tech/science/article2230282.ece|title=The PSLV is a proud symbol of ISRO's self-reliance|location=Chennai, India|work=The Hindu|first=T.S.|last=Subramanian|date=15 July 2011|access-date=16 July 2011|archive-date=26 October 2012|archive-url=https://web.archive.org/web/20121026015701/http://www.thehindu.com/sci-tech/science/article2230282.ece|url-status=live}}</ref> These configurations provide wide variations in payload capabilities up to {{cvt|3800|kg}} in LEO and {{cvt|1800|kg}} in sun-synchronous orbit.

=== PSLV-G ===
The standard or "Generic" version of the PSLV, '''PSLV-G''' had four stages using solid and liquid propulsion systems alternately and six strap-on motors (PSOM or S9) with 9 tonne propellant loading. It had capability to launch {{cvt|1678|kg}} to {{cvt|622|km}} into sun-synchronous orbit. [[PSLV-C35]] was the last operational launch of PSLV-G before its discontinuation.<ref>{{cite news|url=https://www.hindustantimes.com/india-news/pslv-c34-isro-s-biggest-launch-event-as-it-unfolded/story-60VI3nZjesqzhjWVUifj4H.html|title=Where India reaches for the stars: Inside ISRO's Sriharikota Centre|date=2016-06-22|publisher=Hindustan Times|access-date=2018-09-15|quote=Today, the PSLV is available in three configurations — the generic vehicle with six strap-ons, which is the earlier edition of PSLV (which will be discontinued soon)|archive-date=15 September 2018|archive-url=https://web.archive.org/web/20180915230041/https://www.hindustantimes.com/india-news/pslv-c34-isro-s-biggest-launch-event-as-it-unfolded/story-60VI3nZjesqzhjWVUifj4H.html|url-status=live}}</ref><ref>{{cite web|url=https://www.isro.gov.in/sites/default/files/article-files/node/7064/outcomebudget2016-2017.pdf|url-status=dead|title=Outcome Budget 2016–2017|publisher=Government of India, Department of Space|date=2016|access-date=15 September 2018|quote=Currently, two versions of PSLV are operational, namely PSLV-XL (with six extended version of Strap-on motors) and the PSLV Core-alone (without Strap-on motors).|archive-date=25 June 2017|archive-url=https://web.archive.org/web/20170625163259/http://isro.gov.in/sites/default/files/article-files/node/7064/outcomebudget2016-2017.pdf}}</ref><ref name=":0">{{cite book|title=From Fishing Hamlet to Red Planet: India's Space Journey|publisher=Harpercollins|year=2015|isbn=978-9351776895|chapter=2.6 PSLV: The workhorse of ISRO by N. Narayanamoorthy}}</ref>

=== PSLV-CA ===
The '''PSLV-CA''', CA meaning "Core Alone", model premiered on 23 April 2007. The CA model does not include the six strap-on boosters used by the PSLV standard variant but two SITVC tanks with Roll Control Thruster modules are still attached to the side of the first stage with addition of two cylindrical aerodynamic stabilizers.<ref name="sport">{{cite web |url=http://www.spacelaunchreport.com/pslv.html |title=PSLV Datasheet |access-date=27 September 2009 |archive-date=28 July 2020 |archive-url=https://web.archive.org/web/20200728073632/http://www.spacelaunchreport.com/pslv.html |url-status=usurped }}</ref><ref name=":0"/> The fourth stage of the CA variant has {{cvt|400|kg}} less propellant when compared to its standard version.<ref name="sport"/> It currently has capability to launch {{cvt|1100|kg}} to {{cvt|622|km}} [[Sun-synchronous orbit]].<ref name="versions">{{cite web|url=http://www.earth2orbit.com/pdf/PSLV.PDF|title=India's PSLV|date=15 March 2009|website=www.earth2orbit.com |archive-url=https://web.archive.org/web/20110710163553/http://www.earth2orbit.com/pdf/PSLV.PDF|archive-date=10 July 2011|url-status=dead}}</ref>

=== PSLV-XL ===
'''PSLV-XL''' is the upgraded version of Polar Satellite Launch Vehicle in its standard configuration boosted by more powerful, stretched strap-on boosters with 12 tonne propellant load.<ref name="sport"/> Weighing {{cvt|320|MT}} at lift-off, the vehicle uses larger strap-on motors (PSOM-XL or S12) to achieve higher payload capability.<ref name="Chandrayaan_1_Launch">[http://isro.org/pressrelease/Oct22_2008.htm PSLV-C11 Successfully Launches Chandrayaan-1] {{webarchive|url=https://web.archive.org/web/20081025031443/http://www.isro.org/pressrelease/Oct22_2008.htm|date=25 October 2008}}</ref> On 29 December 2005, ISRO successfully tested the improved version of strap-on booster for the PSLV.<ref>{{cite web|url=http://www.isro.org/newsletters/spaceindia/oct2005mar2006/Newsolid.htm|title=New Solid Propellant Motor to Increase PSLV Capability|publisher=ISRO|archive-url=https://web.archive.org/web/20090217222352/http://isro.org/newsletters/spaceindia/oct2005mar2006/Newsolid.htm|archive-date=17 February 2009|url-status=live|access-date=27 April 2007}}</ref> The first use of PSLV-XL was the launch of [[Chandrayaan-1]] by PSLV-C11. The payload capability for this variant is {{cvt|1800|kg}} to Sun-synchronous orbit.<ref name="versions"/>

=== PSLV-DL ===
'''PSLV-DL''' variant has only two strap-on boosters with 12 tonne propellant load on them. [[PSLV-C44]] on 24 January 2019 was the first flight to use PSLV-DL variant of Polar Satellite Launch Vehicle.<ref name="PSLV_DL">{{cite news|last1=Rajwi|first1=Tiki|title=SLV-C44 to lift-off with added features|url=https://www.thehindu.com/sci-tech/science/pslv-c44-to-lift-off-with-added-features/article25972663.ece|access-date=11 January 2019|archive-date=11 January 2019|archive-url=https://web.archive.org/web/20190111210842/https://www.thehindu.com/sci-tech/science/pslv-c44-to-lift-off-with-added-features/article25972663.ece|url-status=live}}</ref><ref>{{cite news|url=https://www.thehindu.com/news/national/kerala/pslv-lift-off-with-added-features/article25981654.ece|title=PSLV lift-off with added features|last=Rajwi|first=Tiki|date=2019-01-12|newspaper=The Hindu|access-date=2019-01-12|issn=0971-751X|archive-date=6 August 2020|archive-url=https://web.archive.org/web/20200806161530/https://www.thehindu.com/news/national/kerala/pslv-lift-off-with-added-features/article25981654.ece|url-status=live}}</ref> It is capable of launching {{Cvt|1257|kg|lb}} to {{Cvt|600|km|mi}} Sun-synchronous orbit.<ref name="VSSC_PSLV"/>

=== PSLV-QL ===
[[File:PSLV C45 EMISAT campaign 22.jpg|thumb|290px|[[PSLV-C45]] lift off]]

'''PSLV-QL''' variant has four ground-lit strap-on boosters, each with 12 tonnes of propellant. [[PSLV-C45]] on 1 April 2019 was the first flight of PSLV-QL.<ref name="c45_kit">{{cite web|url=https://www.isro.gov.in/pslv-c45-emisat-mission/launch-kit|title=Launch Kit C45|publisher=ISRO|access-date=23 March 2019|archive-date=24 March 2019|archive-url=https://web.archive.org/web/20190324134458/https://www.isro.gov.in/pslv-c45-emisat-mission/launch-kit|url-status=live}}</ref> It has the capacity to launch {{Cvt|1523|kg|lb}} to {{Cvt|600|km|mi}} Sun-synchronous orbit.<ref name="VSSC_PSLV">{{cite web|title=The Polar Satellite Launch Vehicle (PSLV)|url=https://www.vssc.gov.in/PSLV.html|archive-url=https://web.archive.org/web/20220126162242/https://www.vssc.gov.in/PSLV.html|archive-date=26 January 2022|access-date=27 January 2022}}</ref>

=== PSLV-3S (concept) ===
PSLV-3S was conceived as a three-staged version of PSLV with its six strap-on boosters and second liquid stage removed. The total lift-off mass of PSLV-3S was expected to be 175 tonnes with capacity to place 500&nbsp;kg in 550&nbsp;km [[low Earth orbit]].<ref name="versions"/><ref>{{cite web|url=http://www.ias.ac.in/currsci/dec252007/1697.pdf|title=Evolution of Indian launch vehicle technologies|date=25 December 2007 |website=www.ias.ac.in|publisher=Indian Academy of Sciences|archive-url=https://web.archive.org/web/20110524225122/http://www.ias.ac.in/currsci/dec252007/1697.pdf|archive-date=24 May 2011|url-status=dead}}</ref><ref>{{cite web|url=http://spl.gov.in/nsss2016/Program/web/SPS/SPS-1-2.pdf|title=Future of Space Transportation: S. Somanath|date=9 February 2016|archive-url=https://web.archive.org/web/20181024195940/http://spl.gov.in/nsss2016/Program/web/SPS/SPS-1-2.pdf|archive-date=24 October 2018|url-status=dead}}</ref><ref>{{cite web |url=https://www.mcgill.ca/iasl/files/iasl/Session_3_KRS_Murthi.pdf |archive-url=https://web.archive.org/web/20221010085517/https://www.mcgill.ca/iasl/files/iasl/Session_3_KRS_Murthi.pdf |archive-date=2022-10-10|url-status=live|title=Space Debris Mitigation – Coordination and Implementation efforts in India|last=Murthi|first=K.R. Sridhara|date=9 May 2009|access-date=22 November 2017}}</ref><ref name=":2">{{cite news|url=https://www.newindianexpress.com/states/kerala/2018/jan/02/isros-baby-rocket-to-carry-small-satellites-likely-to-take-off-in-2019-1742052.html|title=ISRO's baby rocket to carry small satellites, likely to take off in 2019|publisher=The New Indian Express|access-date=2018-01-02|archive-date=3 January 2018|archive-url=https://web.archive.org/web/20180103072531/http://www.newindianexpress.com/states/kerala/2018/jan/02/isros-baby-rocket-to-carry-small-satellites-likely-to-take-off-in-2019-1742052.html|url-status=live}}</ref>

== Launch profile ==
'''PSLV - XL:'''

* The PS1 ignites at T+0 providing 4846{{Spaces|1|nbsp}}kN of thrust.
* Within T+1, 4 out of the 6 boosters ignite on ground, each producing 703&nbsp;kN of thrust. 7658{{Spaces|1|nbsp}}kN of total thrust is produced by the combined propulsion of the PSOMs and the PS1.
* At around T+23/26, the remaining 2 unlit boosters are air-lit bringing the rocket at its maximum thrust capacity.
* At T+1:10, the first 4 ground-lit PSOMs have depleted its propellant and now separates and falls down to the  ocean. The remaining 2 PSOMs and the PS1 continue to burn.
* At T+1:35, the remaining 2 PSOMs complete its 70 seconds burn and separate, leaving the rocket in a Core Alone configuration.
* At T+1:50, the PS1 has completed its 110-second burn and it separates and the [[Vikas (rocket engine)|Vikas Engine]] inside the PS2 ignites.
* The second stage burns for around 130 seconds and around T+4 minutes, the second stages shuts off and separates.
* The third stage, which is a solid rocket booster, and burns 80 seconds and then coasts for the remainder of time and around T+8/10 minutes, it separates and the 4th stage ignites to give the rocket a final push into the orbit.
* This 4th stage burn is highly variable and depends on the mass and number of payloads and usually is around 500 seconds long. The 4th stage may shut off around T+16/18 minutes followed by the '''Payload Deployment'''.

<ref>{{Cite web|title=Flight Profile – PSLV C40 {{!}} Spaceflight101|url=https://spaceflight101.com/pslv-c40/flight-profile/|access-date=2022-02-15|language=en-US|archive-date=13 February 2022|archive-url=https://web.archive.org/web/20220213150054/https://spaceflight101.com/pslv-c40/flight-profile/|url-status=live}}</ref><ref>{{Cite web|title=Flight Profile – PSLV C38 {{!}} Spaceflight101|date=23 June 2017 |url=https://spaceflight101.com/pslv-c38/flight-profile/|access-date=2022-02-15|language=en-US|archive-date=15 February 2022|archive-url=https://web.archive.org/web/20220215015926/https://spaceflight101.com/pslv-c38/flight-profile/|url-status=live}}</ref><ref>{{Cite web|title=PSLV-C24 Brochure|url=https://www.isro.gov.in/sites/default/files/pslv-c24-brochure.pdf|url-status=dead|website=Isro|access-date=15 February 2022|archive-date=20 March 2022|archive-url=https://web.archive.org/web/20220320182325/https://www.isro.gov.in/sites/default/files/pslv-c24-brochure.pdf}}</ref>

== Launch statistics ==
{{main|List of PSLV launches}}
{{#section-h: List of PSLV launches | 1993–2009 }}
;Launch system status:
{{legend|#949090|Retired}}
{| class="wikitable" style="margin: 1em auto 1em auto;background:#fff; font-size:95%;width:60%"
|-
! Variant
! Launches
! Successes
! Failures
! Partial failures
|-style="background:#949090"
| PSLV-G (Standard)
| 12
| 10
| 1
| 1
|-
| PSLV-CA (Core Alone)
| 17
| 17
| 0
| 0
|-
| PSLV-XL (Extended)<ref name="pslv"/>
| 26
| 25
| 1
| 0
|-
|-
| PSLV-DL<ref name="pslv"/>
| 4
| 4
| 0
| 0
|-
|-
| PSLV-QL<ref name="pslv"/>
| 2
| 2
| 0
| 0
|-
| Total {{as of|2024|Dec|df=US|lc=yes}}<ref>{{cite web|url=http://www.isro.gov.in/launchers/pslv|title=Polar Satellite Launch Vehicle|access-date=29 November 2018|archive-date=22 December 2016|archive-url=https://web.archive.org/web/20161222143633/http://www.isro.gov.in/launchers/pslv|url-status=live}}</ref>
| 61
| 58
| 2
| 1
|}

;Decade-wise summary of PSLV launches:

{| class="wikitable" style="margin: 1em auto 1em auto;background:#fff; font-size:95%;width:60%"
|-
! Decade
! Successful
! Partial success
! Failure
! Total
|-
|1990s
| 3
| 1
| 1
| 5
|-
| 2000s
| 11
| 0
| 0
| 11
|-
| 2010s
| 33
| 0
| 1
| 34
|-
| 2020s
| 11
| 0
| 1
| 12
|-
| Total
| 58
| 1
| 3
| 61
|}

== See also ==
{{Portal|India|Rocketry|Spaceflight}} 
* [[Geosynchronous Satellite Launch Vehicle]]
* [[LVM3]]
* [[Next Generation Launch Vehicle]]
* [[Comparison of orbital launchers families]]
* [[Medium-lift launch vehicle]], 2,000 to 20,000&nbsp;kg to LEO
* [[Comparison of orbital rocket engines]]
* [[Comparison of orbital launch systems]]

== References ==
{{reflist|30em}}

== External links ==
{{commons category}}
* [http://www.isro.gov.in/launchers/pslv PSLV : Official ISRO Page] {{Webarchive|url=https://web.archive.org/web/20161222143633/http://www.isro.gov.in/launchers/pslv |date=22 December 2016 }}
* [https://web.archive.org/web/20091027104026/http://geocities.com/hari_ghk/pslv.htm India in Space PSLV page]

{{PSLV}}
{{Expendable launch systems}}
{{Indian space programme}}

[[Category:Polar Satellite Launch Vehicle| ]]
[[Category:ISRO space launch vehicles]]
[[Category:Vehicles introduced in 1993]]
[[Category:Expendable space launch systems]]