Editing Polar Satellite Launch Vehicle (section)

=== 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}}