Polar Satellite Launch Vehicle

Indian expendable launch vehicle for launching satellites, developed by ISRO

Polar Satellite Launch Vehicle

PSLV-C35 on the SDSC FLP

Function| Medium-lift launch system
Manufacturer| ISRO
Country of origin| India
Cost per launch| ₹130 crore (equivalent to ₹153 crore or US$18 million in 2023)
-₹200 crore (equivalent to ₹235 crore or US$28 million in 2023)[1]
Size
Height| 44 m (144 ft)
Diameter| 2.8 m (9 ft 2 in)
Mass| PSLV-G: 295,000 kg (650,000 lb)
PSLV-CA: 230,000 kg (510,000 lb)
PSLV-XL: 320,000 kg (710,000 lb)[2]
Stages| 4
Capacity
Payload to LEO (200 km @ 30° inclination)
Mass|

* G: 3,200 kg (7,100 lb)
* CA: 2,100 kg (4,600 lb)
* XL: 3,800 kg (8,400 lb)

[3][4]
Payload to SSO (620 km circular)
Mass|

* G: 1,600 kg (3,500 lb)
* CA: 1,100 kg (2,400 lb)
* XL: 1,750 kg (3,860 lb)

[3][2][5]
Payload to Sub-GTO (284 × 20650 km)
Mass| 1,425 kg (3,142 lb)
(PSLV-XL)[2][5]
Payload to GTO
Mass|

* G: 1,150 kg (2,540 lb)
* XL: 1,300 kg (2,900 lb)

[3][6]
Associated rockets
Comparable| Vega, Nuri
Launch history
Status| Active
Launch sites| Satish Dhawan Space Centre
Total launches| 60
Success(es)| 57
Failure(s)| 2
Partial failure(s)| 1
First flight|

* 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 flight|

* PSLV-G: 26 September 2016
* PSLV-CA: 30 July 2023
* PSLV-XL: 2 September 2023
* PSLV-DL: 1 January 2024
* PSLV-QL: 11 December 2019

Type of passengers/cargo|

* Chandrayaan-1
* Mars Orbiter Mission
* Astrosat
* SRE-1
* NAVIC
* Aditya-L1

Boosters (PSLV-G) – S9
No. boosters| 6
Maximum thrust| 510 kN (110,000 lbf)
Specific impulse| 262 s (2.57 km/s)
Burn time| 44 s
Propellant| HTPB
Boosters (PSLV-XL/QL/DL) – S12
No. boosters| 6 (XL)
4 (QL)
2 (DL)
Height| 12 m (39 ft)[7]
Diameter| 1 m (3 ft 3 in)
Propellant mass| 12,200 kg (26,900 lb) each
Powered by| off
Maximum thrust| 703.5 kN (158,200 lbf)[8]
Total thrust| 4,221 kN (949,000 lbf) (XL)
2,814 kN (633,000 lbf) (QL)
1,407 kN (316,000 lbf) (DL)
Specific impulse| 262 s (2.57 km/s)
Burn time| 70 s
Propellant| HTPB
First stage
Height| 20 m (66 ft)[7]
Diameter| 2.8 m (9 ft 2 in)
Propellant mass| 138,200 kg (304,700 lb) each[7][2]
Powered by| S139
Maximum thrust| 4,846.9 kN (1,089,600 lbf)[8]
Specific impulse| 237 s (2.32 km/s) (sea level)
269 s (2.64 km/s) (vacuum)
Burn time| 110 s
Propellant| HTPB
Second stage
Height| 12.8 m (42 ft)[7]
Diameter| 2.8 m (9 ft 2 in)
Propellant mass| 42,000 kg (93,000 lb) each[7]
Powered by| 1 Vikas
Maximum thrust| 803.7 kN (180,700 lbf)[8]
Specific impulse| 293 s (2.87 km/s)
Burn time| 133 s
Propellant| N2O4/UDMH
Third stage
Height| 3.6 m (12 ft)[7]
Diameter| 2 m (6 ft 7 in)
Propellant mass| 7,600 kg (16,800 lb) each[7]
Powered by| S-7[9]
Maximum thrust| 250 kN (56,000 lbf)
Specific impulse| 295 s (2.89 km/s)
Burn time| 113.5 s[10]
Propellant| HTPB
Fourth stage
Height| 3 m (9.8 ft)[7]
Diameter| 1.3 m (4 ft 3 in)
Propellant mass| 2,500 kg (5,500 lb) each[7]
Powered by| 2 x L-2-5[9]
Maximum thrust| 14.66 kN (3,300 lbf)[8]
Specific impulse| 308 s (3.02 km/s)
Burn time| 525 s
Propellant| MMH/MON

[edit on Wikidata]

The Polar Satellite Launch Vehicle (PSLV) is an expendable medium-lift launch vehicle designed and operated by the Indian Space Research Organisation (ISRO). It was developed to allow India to launch its Indian Remote Sensing (IRS) satellites into Sun-synchronous orbits, 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 (GTO).[11]

Some notable payloads launched by PSLV include India's first lunar probe Chandrayaan-1, India's first interplanetary mission, Mars Orbiter Mission (Mangalyaan), India's first space observatory, Astrosat and India's first Solar mission, Aditya-L1.[2]

PSLV has gained credibility as a leading provider of 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.[12] As of June 2022, PSLV has launched 345 foreign satellites from 36 countries.[13] 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,[14][15] until 24 January 2021, when SpaceX launched the Transporter-1 mission on a Falcon 9 rocket carrying 143 satellites into orbit.[16]

Payloads can be integrated in tandem configuration employing a Dual Launch Adapter.[17][18] Smaller payloads are also placed on equipment deck and customized payload adapters.[19]

## Development[edit]

PSLV-C11 strap-on

Studies by the PSLV Planning group under S Srinivasan to develop a vehicle capable of delivering a 600 kg payload to a 550 km sun-synchronous orbit from SHAR began in 1978.[20][21] 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.[22][23][24][25]

By 1981, confidence grew in remote sensing spacecraft development with the launch of Bhaskara-1, and the PSLV project objectives were upgraded to have the vehicle deliver a 1000 kg payload into a 900 km SSO. As technology transfer of Viking rocket engine firmed up, a new lighter configuration with the inclusion of a liquid powered stage was selected.[26] 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 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.[23][24]

The inertial navigation systems 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 systems (RCS) are developed by the Liquid Propulsion Systems Centre (LPSC) at Valiamala near Thiruvananthapuram, kerala. The solid propellant motors are processed at Satish Dhawan Space Centre (SHAR) at Sriharikota, Andhra Pradesh, which also carries out launch operations.

The PSLV was first launched on 20 September 1993.[27][28] The first and second stages performed as expected, but an attitude control problem led to the collision of the second and third stages at separation, and the payload failed to reach orbit.[29] After this initial setback, the PSLV successfully completed its second mission in 1994.[30] 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.[31] (Although launch 41: August 2017 PSLV-C39 was unsuccessful.[2])

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.[32]

In June 2018, the Union Cabinet approved ₹6,131 crore (equivalent to ₹72 billion or US$860 million in 2023) for 30 operational flights of the PSLV scheduled to take place between 2019 and 2024.[33]

ISRO is working towards handing over the production and operation of PSLV to private industry through a joint venture.[34] On 16 August 2019, NewSpace India Limited issued an invitation to tender for manufacturing PSLV entirely by private industries.[35][36] 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.[37][38][39]

## Vehicle description[edit]

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

### First stage (PS1)[edit]

PSLV-C44 first stage inside Mobile Service Tower.

The first stage, one of the largest solid rocket boosters in the world, carries 138 t (136 long tons; 152 short tons) of hydroxyl-terminated polybutadiene-bound (HTPB) propellant and develops a maximum thrust of about 4,800 kN (1,100,000 lbf). The 2.8 m (9 ft 2 in) diameter motor case is made of maraging steel and has an empty mass of 30,200 kg (66,600 lb).[9]

Pitch and 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 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 Control Thruster (RCT) modules with small bi-propellant (MMH/MON) liquid engine are also attached.[28]

On the PSLV-G and PSLV-XL, first stage thrust is augmented by six strap-on solid boosters. Four boosters are ground-lit and the remaining two ignite 25 seconds after launch. The solid boosters carry 9 t (8.9 long tons; 9.9 short tons) or 12 t (12 long tons; 13 short tons) (for PSLV-XL configuration) propellant and produce 510 kN (110,000 lbf) and 719 kN (162,000 lbf) thrust respectively. Two strap-on boosters are equipped with SITVC for additional attitude control.[9] 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.[40]

### Second stage (PS2)[edit]

PSLV-C50 second stage with Vikas engine

The second stage is powered by a single Vikas engine and carries 41.5 t (40.8 long tons; 45.7 short tons) of Earth store-able liquid propellant - unsymmetrical dimethylhydrazine (UDMH) as fuel and nitrogen tetroxide (N2O4) as oxidiser in two tanks separated by a common bulkhead.[28] It generates a maximum thrust of 800 kN (180,000 lbf). The engine is gimbaled (±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.[41]

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.[40]

Second stage also carries some quantity of water in a toroidal tank at its bottom.[42] Water spray is used to cool hot gases from Vikas' gas generator to about 600 °C before entering turbopump. Propellant and water tanks of second stage are pressurized by Helium.[43][44][45]

### Third stage (PS3)[edit]

Third and fourth stages of PSLV-C45

The third stage uses 7.6 t (7.5 long tons; 8.4 short tons) of HTPB solid propellant and produces a maximum thrust of 250 kN (56,000 lbf). 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 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.[9][10]

### Fourth stage (PS4)[edit]

The fourth stage is powered by regeneratively cooled twin engines,[46] burning monomethylhydrazine (MMH) and mixed oxides of nitrogen (MON). Each pressure fed engine generates 7.4 kN (1,700 lbf) 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.[47] The stage is pressurized by Helium[48] and carries 1,600 kg (3,500 lb) to 2,500 kg (5,500 lb) of propellant depending on the mission requirements. PS4 has three variants L1.6, L2.0 and L2.5 based on propellant tank capacity.[49][50]

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.[51]

As a space debris mitigation measure, PSLV fourth stage gets 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.[52][53][54]

The niobium alloy nozzle used on twin engines of fourth stage is expected to be replaced by lighter, silicon carbide coated carbon–carbon nozzle divergent. The new nozzle was hot tested at facilities of IPRC, Mahendragiri in March and April 2024. This substitution should increase payload capacity of PSLV by 15 kilograms (33 lb).[55]

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 kg to 13.7 kg of metal powder.[56]

#### PS4 stage as orbital platform[edit]

Main article: PSLV Orbital Experiment Module

PS4 has carried hosted payloads like AAM on PSLV-C8,[42] Rubin 9.1/Rubin 9.2 on PSLV-C14[57] and mRESINS on PSLV-C21.[58] 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.[59][60][61]

On PSLV-C37 and PSLV-C38 campaigns,[62] as a demonstration PS4 was kept operational and monitored for over ten orbits after delivering spacecraft.[63][64][65]

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.[66] It carried KalamSAT-V2 as a fixed payload, a 1U cubesat by Space Kidz India based on Interorbital Systems kit.[67][68]

On PSLV-C45 campaign, the fourth stage had its own power generation capability as it was augmented with an array of fixed solar cells around PS4 propellant tank.[69] The three payloads hosted on PS4-OP were the Advanced Retarding Potential Analyzer for Ionospheric Studies (ARIS 101F) by IIST,[70] an experimental AIS payload by ISRO, and AISAT by Satellize.[71] To function as orbital platform, fourth stage was put in spin-stabilized mode using its RCS thrusters.[72]

On the PSLV-C53 campaign, the PS4-OP is referred to as the 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.[73][74][75][76]

#### PS4 on RLV-OREX[edit]

The 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.[77][78]

### Payload fairing[edit]

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 1,182 kilograms (2,606 lb), it has 3.2 meter diameter and 8.3 meter height.[79] It has Isogrid construction and is made out of 7075 aluminum alloy with a 3 mm thick steel nose-cap.[80][81] The two halves of fairing are separated using a pyrotechnic device based jettisoning system consisting horizontal and lateral separation mechanisms.[82] To protect spacecraft from damage due to excessive acoustic loads during launch, the heatshield interior is lined with acoustic blankets.[28]

| 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

## Variants[edit]

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.[83] These configurations provide wide variations in payload capabilities up to 3,800 kg (8,400 lb) in LEO and 1,800 kg (4,000 lb) in sun-synchronous orbit.

### PSLV-G[edit]

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 1,678 kg (3,699 lb) to 622 km (386 mi) into sun-synchronous orbit. PSLV-C35 was the last operational launch of PSLV-G before its discontinuation.[84][85][86]

### PSLV-CA[edit]

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.[49][86] The fourth stage of the CA variant has 400 kg (880 lb) less propellant when compared to its standard version.[49] It currently has capability to launch 1,100 kg (2,400 lb) to 622 km (386 mi) Sun-synchronous orbit.[87]

### PSLV-XL[edit]

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.[49] Weighing 320 t (310 long tons; 350 short tons) at lift-off, the vehicle uses larger strap-on motors (PSOM-XL or S12) to achieve higher payload capability.[88] On 29 December 2005, ISRO successfully tested the improved version of strap-on booster for the PSLV.[89] The first use of PSLV-XL was the launch of Chandrayaan-1 by PSLV-C11. The payload capability for this variant is 1,800 kg (4,000 lb) to Sun-synchronous orbit.[87]

### PSLV-DL[edit]

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.[90][91] It is capable of launching 1,257 kg (2,771 lb) to 600 km (370 mi) Sun-synchronous orbit.[5]

### PSLV-QL[edit]

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.[92] It has the capacity to launch 1,523 kg (3,358 lb) to 600 km (370 mi) Sun-synchronous orbit.[5]

### PSLV-3S (concept)[edit]

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 kg in 550 km low Earth orbit.[87][93][94][95][96]

## Launch profile[edit]

PSLV - XL:

* The PS1 ignites at T+0 providing 4846  kN of thrust.
* Within T+1, 4 out of the 6 boosters ignite on ground, each producing 703 kN of thrust. 7658 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 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.

[97][98][99]

## Launch statistics[edit]

Main article: List of PSLV launches

As of 1 January 2024[update] the PSLV has made 60 launches, with 57 successfully reaching their planned orbits, two outright failures and one partial failure, yielding a success rate of 95% (or 97% including the partial failure).[100] All launches have occurred from the Satish Dhawan Space Centre, known before 2002 as the Sriharikota Range (SHAR).

Launch system status

Retired

Variant  | Launches  | Successes  | Failures  | Partial failures

|
|
|
|

PSLV-G (Standard)  | 12  | 10  | 1  | 1
PSLV-CA (Core Alone)  | 17  | 17  | 0  | 0
PSLV-XL (Extended)[2] | 25  | 24  | 1  | 0
PSLV-DL[2] | 4  | 4  | 0  | 0
PSLV-QL[2] | 2  | 2  | 0  | 0
Total as of January 2024[update][101] | 60  | 57  | 2  | 1

Decade-wise summary of PSLV launches

Decade  | Successful  | Partial success  | Failure  | Total

|
|
|
|

1990s  | 3  | 1  | 1  | 5
2000s  | 11  | 0  | 0  | 11
2010s  | 33  | 0  | 1  | 34
2020s  | 10  | 0  | 0  | 10
Total  | 57  | 1  | 2  | 60

## See also[edit]

* India portal
* Rocketry portal
* Spaceflight portal

* Geosynchronous Satellite Launch Vehicle
* LVM3
* Next Generation Launch Vehicle
* Comparison of orbital launchers families
* Medium-lift launch vehicle, 2,000 to 20,000 kg to LEO
* Comparison of orbital rocket engines
* Comparison of orbital launch systems

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43. ^ Thomas, George; Pant, Bhanu; Ganesan, R.; Singh, S. K.; Sinha, P. P. (1999). "Development & qualification of Titanium Alloy High-Pressure Gas Bottles for PSLV second Stage". Cooperation in Space. 430: 559. Bibcode:1999ESASP.430..559T. Archived from the original on 11 November 2020. Retrieved 7 April 2021.
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45. ^ "Space India Jan-Mar 1990" (PDF). April 1990. Archived (PDF) from the original on 7 April 2021. Retrieved 8 April 2021.
46. ^ "ASACO sub-systems for space". Archived from the original on 11 December 2017. Retrieved 16 October 2018.
47. ^ Ramakrishnan, S.; Somanath, S.; Balakrishnan, S. S. (1 January 2002). "Multi-Orbit Mission by PSLV-C3 and Future Launch Opportunities". Iaf Abstracts: 936. Bibcode:2002iaf..confE.936R.
48. ^ "Latest Volume14-Issue21 News, Photos, Latest News Headlines about Volume14-Issue21". Frontline. Archived from the original on 7 May 2021. Retrieved 7 April 2021.
49. ^ a b c d "PSLV Datasheet". Archived from the original on 28 July 2020. Retrieved 27 September 2009.`{{cite web}}`: CS1 maint: unfit URL (link)
50. ^ "Signatures, Newsletter of the Indian Society of Remote Sensing – Ahmedabad Chapter. Volume: 24, No.2, April- June 2012" (PDF). Archived from the original (PDF) on 21 December 2021. Retrieved 31 July 2023. "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."
51. ^ "ISRO Successfully Tests Multiple Burn Fuel Engine During Launch of Six Singaporean Satellites". Archived from the original on 3 May 2016. Retrieved 16 December 2015.
52. ^ Adimurthy, V.; Ganeshan, A.S. (February 2006). "Space debris mitigation measures in India". Acta Astronautica. 58 (3): 168–174. Bibcode:2006AcAau..58..168A. doi:10.1016/j.actaastro.2005.09.002. Archived from the original on 12 April 2022. Retrieved 26 December 2021.
53. ^ Bonnal, C (1 June 2007). "Design and operational practices for the passivation of spacecraft and launchers at the end of life". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering. 221 (6): 925–931. doi:10.1243/09544100JAERO231. ISSN 0954-4100. S2CID 110656798.
54. ^ "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'" (PDF). Archived (PDF) from the original on 9 October 2022.
55. ^ "ISRO Develops Lightweight Carbon-Carbon Nozzle for Rocket Engines, Enhancing Payload Capacity". www.isro.gov.in. Archived from the original on 19 April 2024. Retrieved 21 April 2024.
56. ^ "With 3D-printed rocket engine, Isro adds another feather to cap". The Times of India. 11 May 2024. ISSN 0971-8257. Retrieved 13 May 2024.
57. ^ "PSLV C14/Oceansat-2 brochure" (PDF). Archived from the original (PDF) on 6 August 2020. Retrieved 23 February 2020.
58. ^ "Space-India July 2012 to August 2013" (PDF). Archived from the original (PDF) on 6 August 2020. Retrieved 23 February 2020.
59. ^ "Opportunities for science experiments in the fourth stage of India's PSLV" (PDF). 21 February 2019. Archived (PDF) from the original on 9 October 2022.
60. ^ "Announcement of Opportunity (AO) for Orbital platform: an avenue for in-orbit scientific experiments" (PDF). 15 June 2019. Archived from the original (PDF) on 6 August 2020. Retrieved 23 February 2020.
61. ^ Kumar, Chethan (15 June 2019). "2 days after Space Station news, Isro calls for "docking experiments" on PSLV stage-4". The Times of India. Archived from the original on 24 August 2019. Retrieved 23 February 2020.
62. ^ "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". www.isro.gov.in. Archived from the original on 21 September 2022. Retrieved 27 June 2022.
63. ^ "Department of Space Annual Report 2017-18" (PDF). Archived (PDF) from the original on 13 February 2018.
64. ^ Singh, Surendra (16 December 2018). "In a first, ISRO will make dead rocket stage "alive" in space for experiments". The Times of India. Archived from the original on 8 November 2020. Retrieved 23 February 2020.
65. ^ rajasekhar, pathri (20 June 2017). "Isro to lower rocket's altitude". Deccan Chronicle. Archived from the original on 6 August 2020. Retrieved 23 February 2020.
66. ^ Rajwi, Tiki (12 January 2019). "PSLV lift-off with added features". The Hindu. ISSN 0971-751X. Archived from the original on 6 August 2020. Retrieved 23 February 2020.
67. ^ "PSLV-C44 - ISRO". isro.gov.in. Archived from the original on 17 January 2019. Retrieved 26 June 2020.
68. ^ Interorbital Systems [@interorbital] (25 January 2019). "Congratulations to ISRO and SpaceKidzIndia on getting their CubeSat into orbit! The students modified their IOS CubeSat kit, complete w/ their own experiments!" (Tweet) - via Twitter.
69. ^ Clark, Stephen. "Indian military satellite, 20 more Planet imaging CubeSats launched by PSLV". Spaceflight Now. Archived from the original on 6 April 2019. Retrieved 23 February 2020.
70. ^ "Department of Avionics, R. Sudharshan Kaarthik, Ph.D (Assistant Professor)". Archived from the original on 13 February 2020. Retrieved 23 February 2020.
71. ^ "Exseed Sat-2". Satellize. Archived from the original on 23 February 2020. Retrieved 23 February 2020.
72. ^ "Opportunity for Scientific Experiments on PSLV Upper Stage Orbital Platform" (PDF). 16 June 2021. Archived (PDF) from the original on 9 October 2022.
73. ^ Kumar, Chethan (25 June 2012). "Bengaluru's Digantara, Hyderabad startup Dhruva become first to get IN-SPACe authorisation". The Times of India. Archived from the original on 25 June 2022. Retrieved 26 June 2022.
74. ^ "PSLV-C53/DS-EO mission" (PDF). Archived from the original (PDF) on 5 July 2022.
75. ^ "పీఎస్‌ఎల్‌వీ-సి53లో నూతన సాంకేతికత". EENADU (in Telugu). Archived from the original on 6 July 2022. Retrieved 6 July 2022.
76. ^ News9 Staff (8 September 2022). "Har Ghar Tiranga happened in Antriksh. ISRO did hoist the Indian flag in Space!". NEWS9LIVE. Archived from the original on 9 September 2022. Retrieved 9 September 2022.`{{cite web}}`: CS1 maint: numeric names: authors list (link)
77. ^ "RLV re-entry mission to use GSLV with PSLV last stage; landing gear to change & more". The Times of India. ISSN 0971-8257. Retrieved 26 June 2024.
78. ^ "MSN". www.msn.com. Retrieved 26 June 2024.
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84. ^ "Where India reaches for the stars: Inside ISRO's Sriharikota Centre". Hindustan Times. 22 June 2016. Archived from the original on 15 September 2018. Retrieved 15 September 2018. "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)"
85. ^ "Outcome Budget 2016–2017" (PDF). Government of India, Department of Space. 2016. Archived from the original (PDF) on 25 June 2017. Retrieved 15 September 2018. "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)."
86. ^ a b "2.6 PSLV: The workhorse of ISRO by N. Narayanamoorthy". From Fishing Hamlet to Red Planet: India's Space Journey. Harpercollins. 2015. ISBN 978-9351776895.
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88. ^ PSLV-C11 Successfully Launches Chandrayaan-1 Archived 25 October 2008 at the Wayback Machine
89. ^ "New Solid Propellant Motor to Increase PSLV Capability". ISRO. Archived from the original on 17 February 2009. Retrieved 27 April 2007.
90. ^ Rajwi, Tiki. "SLV-C44 to lift-off with added features". Archived from the original on 11 January 2019. Retrieved 11 January 2019.
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96. ^ "ISRO's baby rocket to carry small satellites, likely to take off in 2019". The New Indian Express. Archived from the original on 3 January 2018. Retrieved 2 January 2018.
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99. ^ "PSLV-C24 Brochure" (PDF). Isro. Archived from the original (PDF) on 20 March 2022. Retrieved 15 February 2022.
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101. ^ "Polar Satellite Launch Vehicle". Archived from the original on 22 December 2016. Retrieved 29 November 2018.

## External links[edit]

Wikimedia Commons has media related to Polar Satellite Launch Vehicle.

* PSLV : Official ISRO Page Archived 22 December 2016 at the Wayback Machine
* India in Space PSLV page

* v
* t
* e

Polar Satellite Launch Vehicle

1990s|

* PSLV-D1 (20 Sep 1993, failure)
* PSLV-D2 (15 Oct 1994)
* PSLV-D3 (21 Mar 1996)
* PSLV-C1 (29 Sep 1997)
* PSLV-C2 (26 May 1999)

2000s|

* PSLV-C3 (22 Oct 2001)
* PSLV-C4 (METSAT, 12 Sep 2002)
* PSLV-C5 (Resourcesat-1, 17 Oct 2003)
* PSLV-C6 (HAMSAT, 5 May 2005)
* PSLV-C7 (10 Jan 2007)
* PSLV-C8 (23 Apr 2007)
* PSLV-C10 (21 Jan 2008)
* PSLV-C9 (28 Apr 2008)
* PSLV-C11 (22 Oct 2008)
* PSLV-C12 (20 Apr 2009)
* PSLV-C14 (23 Sep 2009)

2010s|

* PSLV-C15 (12 Jul 2010)
* PSLV-C16 (20 Apr 2011)
* PSLV-C17 (15 Jul 2011)
* PSLV-C18 (12 Oct 2011)
* PSLV-C19 (26 Apr 2012)
* PSLV-C21 (9 Sep 2012)
* PSLV-C20 (25 Feb 2013)
* PSLV-C22 (IRNSS-1A, 1 Jul 2013)
* PSLV-C25 (Mars Orbiter Mission, 5 Nov 2013)
* PSLV-C24 (IRNSS-1B, 4 Apr 2014)
* PSLV-C23 (30 Jun 2014)
* PSLV-C26 (IRNSS-1C, 16 Oct 2014)
* PSLV-C27 (IRNSS-1D, 28 Mar 2015)
* PSLV-C28 (DMC-3, 10 Jul 2015)
* PSLV-C30 (28 Sep 2015)
* PSLV-C29 (16 Dec 2015)
* PSLV-C31 (IRNSS-1E, 20 Jan 2016)
* PSLV-C32 (IRNSS-1F, 10 Mar 2016)
* PSLV-C33 (IRNSS-1G, 28 Apr 2016)
* PSLV-C34 (22 Jun 2016)
* PSLV-C35 (SCATSAT-1, 26 Sep 2016)
* PSLV-C36 (Resourcesat-2A, 7 Dec 2016)
* PSLV-C37 (15 Feb 2017)
* PSLV-C38 (23 Jun 2017)
* PSLV-C39 (IRNSS-1H, 31 Aug 2017, failure)
* PSLV-C40 (Cartosat-2F, 12 Jan 2018)
* PSLV-C41 (IRNSS-1I, 11 Apr 2018)
* PSLV-C42 (16 Sep 2018)
* PSLV-C43 (HySIS, 29 Nov 2018)
* PSLV-C44 (Microsat-R, 24 Jan 2019)
* PSLV-C45 (EMISAT, 1 Apr 2019)
* PSLV-C46 (RISAT-2B, 22 May 2019)
* PSLV-C47 (Cartosat-3, 27 Nov 2019)
* PSLV-C48 (RISAT-2BR1, 11 Dec 2019)

2020s|

* PSLV-C49 (EOS-01, 7 Nov 2020)
* PSLV-C50 (CMS-01, 17 Dec 2020)
* PSLV-C51 (Amazônia-1, 28 Feb 2021)
* PSLV-C52 (EOS-04, 14 Feb 2022)
* PSLV-C53 (DS-EO, NeuSAR, Scoob-1, POEM-1 (hosted), 30 Jun 2022)
* PSLV-C54 (EOS-06, BhutanSat aka INS-2B, Anand, 26 Nov 2022)
* PSLV-C55 (TeLEOS-2, Lumelite-4, POEM-2 (hosted), 22 Apr 2023)
* PSLV-C56 (DS-SAR, VELOX-AM, 30 Jul 2023)
* PSLV-C57 (Aditya-L1, 2 Sep 2023)
* PSLV-C58 (XPoSat, POEM-3 (hosted), 1 Jan 2024)

* List of PSLV launches
* Italics indicates future missions

* v
* t
* e

Orbital launch systems

* List of orbital launch systems
* Comparison of orbital launch systems

Current|

* Angara
* 1.2
* A5
* Ariane 6
* Atlas V
* Ceres
* 1
* 1S
* Chollima-1
* Electron
* Falcon 9 Block 5
* Falcon Heavy
* Firefly Alpha
* Gravity-1
* GSLV
* H-IIA
* H3
* Hyperbola-1
* Jielong
* 1
* 3
* KAIROS†
* Kaituozhe 2
* Kinetica 1
* Kuaizhou
* 1
* 1A
* 11
* Long March
* 2C
* 2D
* 2F
* 3A
* 3B/E
* 3C
* 4B
* 4C
* 5
* 5B
* 6
* 6A
* 7
* 7A
* 8
* 11
* 11H
* LVM3
* Minotaur
* I
* IV
* V
* C
* Nuri
* OS-M1†
* Pegasus XL
* Proton-M
* PSLV
* Qaem 100
* Qased
* RS1†
* Shavit 2
* Simorgh
* SLS
* Block 1
* Soyuz-2
* 2.1a / STA
* 2.1b / STB
* 2-1v
* SSLV
* Starship
* Tianlong-2
* Unha
* Vega
* original
* C
* Vulcan Centaur
* Zhuque
* 2

In development|

* Antares 330
* Bloostar
* Cyclone-4M
* Epsilon S
* Eris
* Gravity-2
* Hyperbola-2
* Irtysh
* Kuaizhou
* 21
* 31
* Long March
* 9
* 10
* 12
* Miura 5
* MLV
* Neutron
* New Glenn
* New Line 1
* NGLV
* Nova
* OS-M
* 2
* 4
* Orbex Prime
* Pallas-1
* Red Dwarf
* SLS
* Block 1B
* Block 2
* Soyuz-7
* Terran R
* Tianlong-3
* VLM
* Vega E
* Zero
* Zhuque
* 3
* Zuljanah

Retired|

* Antares
* 110
* 120
* 130†
* 230
* 230+
* Ariane
* 1
* 2
* 3
* 4
* 5
* ASLV
* Athena
* I
* II
* Atlas
* B
* D
* E/F
* G
* H
* I
* II
* III
* LV-3B
* SLV-3
* Able†
* Agena
* Centaur
* Black Arrow
* Conestoga†
* Delta
* A
* B
* C
* D
* E
* G
* J
* L
* M
* N
* 0100
* 1000
* 2000
* 3000
* 4000
* 5000
* II
* III
* IV
* IV Heavy
* Diamant
* Dnepr
* Energia
* Epsilon
* Europa
* I†
* II†
* Falcon 1
* Falcon 9
* v1.0
* v1.1
* v1.2 "Full Thrust"
* Feng Bao 1
* GSLV
* Mk I
* H-I
* H-II
* H-IIB
* Juno I
* Juno II
* Kaituozhe-1
* Kosmos
* original
* 1
* 2/2I
* 3
* 3M
* Lambda
* 4S
* LauncherOne
* Long March
* 1
* 1D†
* 2A
* 2E
* 3
* 3B
* 4A
* Mu
* 4S
* 3C
* 3H
* 3S
* 3SII
* V
* N1†
* N-I
* N-II
* Naro-1
* Paektusan†
* Pilot-2†
* R-7
* Luna
* Molniya
* M
* L
* Polyot
* Soyuz
* original
* FG
* L
* M
* U
* U2
* Soyuz/Vostok
* Sputnik
* Voskhod
* Vostok
* L
* K
* 2
* 2M
* R-29
* Shtil'
* Volna†
* Rocket 3
* Safir
* 1
* 1A
* 1B
* Saturn
* I
* IB
* V
* Scout
* X-1
* Blue Scout II†
* X-2†
* X-2M
* X-3
* X-3M
* X-4
* X-2B†
* B
* A
* B-1
* D-1
* A-1
* E-1
* F-1
* G-1
* Shavit
* original
* 1
* SLV
* Space Shuttle
* SPARK†
* Sparta
* SS-520
* Start-1
* Terran 1†
* Thor
* Able
* Ablestar
* 1
* 2
* Agena
* A
* B
* D
* Burner
* 1
* 2
* Delta
* DSV-2U
* Thorad-Agena
* SLV-2G
* SLV-2H
* Titan
* II GLV
* IIIA
* IIIB
* IIIC
* IIID
* IIIE
* 34D
* 23G
* CT-3
* IV
* Tsyklon
* R-36-O
* original
* 2
* 3
* Universal Rocket
* UR-500 Proton
* Proton-K
* Rokot
* Strela
* Vanguard
* VLS-1†
* Zenit
* 2
* 2M
* 2FG
* 3SL
* 3SLB
* 3F
* Zhuque
* 1†

Classes|

* Sounding rocket
* Small-lift launch vehicle
* Medium-lift launch vehicle
* Heavy-lift launch vehicle
* Super heavy-lift launch vehicle

* This Template lists historical, current, and future space rockets that at least once attempted (but not necessarily succeeded in) an orbital launch or that are planned to attempt such a launch in the future
* Symbol † indicates past or current rockets that attempted orbital launches but never succeeded (never did or has yet to perform a successful orbital launch)

* v
* t
* e

Indian space programme

* Department of Space (DoS)

Organisations|

* Indian Space Research Organisation (ISRO)
* Antrix Corporation
* Indian Institute of Space Science and Technology (IIST)
* Indian Institute of Remote Sensing (IIRS)
* National Atmospheric Research Laboratory (NARL)
* NewSpace India Limited (NSIL)
* Physical Research Laboratory (PRL)
* Development and Educational Communication Unit (DECU)
* Integrated Space Cell
* Defence Space Agency
* Indian National Space Promotion and Authorisation Centre (IN–SPACe)

Programmes|

* Bhaskara
* GAGAN
* GSAT
* INSAT
* IRNSS
* IRS
* Cartosat
* RISAT
* Rohini
* SROSS
* Chandrayaan
* Human Spaceflight Programme

Satellites|

* APPLE
* Aryabhata
* HAMSAT
* IMS-1
* Megha-Tropiques
* NISAR
* SARAL
* South Asia Satellite
* Kalpana-1

Space observatories|

* Astrosat
* Aditya-L1
* XPoSat
* AstroSat-2 (proposed)

Lunar and
planetary spacecraft|

* Chandrayaan-1
* Moon Impact Probe
* Chandrayaan-2
* Vikram lander
* Pragyan rover
* Chandrayaan-3
* Vikram lander
* Pragyan rover
* Chandrayaan-4 (upcoming)
* Lunar Polar Exploration Mission (proposed)
* Mars Orbiter Mission
* Mars Orbiter Mission 2 (proposed)
* Venus Orbiter Mission (proposed)

Human spaceflight|

* Indian human spaceflight programme
* SRE-1
* SRE-II
* Gaganyaan
* CARE
* ISRO Space Station (proposed)

Launch vehicles|

| Active|

* Orbital
* PSLV
* Launches
* GSLV
* Launches
* LVM3
* SSLV

* Suborbital
* Rohini
* ATV

|

In development|

* RLV Technology Demonstration Programme
* NGLV

Retired|

* SLV
* ASLV

Engines|

| Active|

* CE-7.5
* CE-20
* Vikas

|

In development|

* SCE-200

Spaceports|

* Satish Dhawan Space Centre
* Thumba Equatorial Rocket Launching Station

* under development
* Kulasekharapatnam Spaceport

Research facilities|

* Vikram Sarabhai Space Centre
* U R Rao Satellite Centre
* Liquid Propulsion Systems Centre
* ISRO Propulsion Complex
* Space Applications Centre
* ISRO Inertial Systems Unit
* Laboratory for Electro-Optics Systems
* Human Space Flight Centre
* Development and Educational Communication Unit

Communications|

* Indian Deep Space Network
* Indian Space Science Data Centre
* ISRO Telemetry, Tracking and Command Network
* Master Control Facility
* National Remote Sensing Centre

Legislation and policy|

* Space Activities Bill
* Space policy of India
* Draft Spacecom Policy 2020
* SpaceRP Policy 2020
* Technology Transfer Policy and Guidelines

Private companies|

* Pixxel
* Skyroot Aerospace
* Sisir Radar
* Satellize
* AgniKul Cosmos
* Dhruva Space
* Bellatrix Aerospace
* TeamIndus

Related|

* SAGA-220 (supercomputer)
* Statio Shiv Shakti
* RESPOND

* List of Indian satellites
* List of Satish Dhawan Space Centre launches
* List of ISRO missions
* List of ISRO chairpersons

*[v]: View this template
*[t]: Discuss this template
*[e]: Edit this template