Polar Satellite Launch Vehicle

Main article: PSLV Orbital Experiment Module

PS4 has carried hosted payloads like AAM on PSLV-C8, ^[43] Rubin 9.1/Rubin 9.2 on PSLV-C14 ^[58] and mRESINS on PSLV-C21. ^[59] 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. ^{[60] [61] [62]}

On PSLV-C37 and PSLV-C38 campaigns, ^[63] as a demonstration PS4 was kept operational and monitored for over ten orbits after delivering spacecraft. ^{[64] [65] [66]}

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. ^[67] It carried KalamSAT-V2 as a fixed payload, a 1U CubeSat by Space Kidz India based on Interorbital Systems kit. ^{[68] [69]}

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. ^[70] The three payloads hosted on PS4-OP were the Advanced Retarding Potential Analyzer for Ionospheric Studies (ARIS 101F) by IIST, ^[71] an experimental AIS payload by ISRO, and AISAT by Satellize. ^[72] To function as orbital platform, fourth stage was put in spin-stabilized mode using its RCS thrusters. ^[73]

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. ^{[74] [75] [76] [77]}

PS4 on RLV-OREX

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. ^{[78] [79]}

Payload fairing

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. ^[80] It has Isogrid construction and is made out of 7075 aluminum alloy with a 3 mm thick steel nose-cap. ^{[81] [82]} The two halves of fairing are separated using a pyrotechnic device based jettisoning system consisting of horizontal and lateral separation mechanisms. ^[83] To protect the spacecraft from damage due to excessive acoustic loads during launch, the heatshield interior is lined with acoustic blankets. ^[29]

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 croreorUS$18 million in 2023) - ₹ 200 crore (equivalent to ₹235 croreorUS$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]

	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

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. ^[84] 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

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. ^{[85] [86] [87]}

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. ^{[50] [87]} The fourth stage of the CA variant has 400 kg (880 lb) less propellant when compared to its standard version. ^[50] It currently has capability to launch 1,100 kg (2,400 lb) to 622 km (386 mi) Sun-synchronous orbit. ^[88]

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. ^[50] 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. ^[89] On 29 December 2005, ISRO successfully tested the improved version of strap-on booster for the PSLV. ^[90] 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. ^[88]

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. ^{[91] [92]} It is capable of launching 1,257 kg (2,771 lb) to 600 km (370 mi) Sun-synchronous orbit. ^[5]

PSLV-QL

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. ^[93] It has the capacity to launch 1,523 kg (3,358 lb) to 600 km (370 mi) Sun-synchronous orbit. ^[5]

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 kg in 550 km low Earth orbit. ^{[88] [94] [95] [96] [97]}

Launch profile

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.

^{[98] [99] [100]}

Launch statistics

Main article: List of PSLV launches

As of 5 December 2024 ^[update] , the PSLV has made 61 launches, with 58 successfully reaching their planned orbits, two outright failures and one partial failure, yielding a success rate of 95% (or 97% including the partial failure). ^[101] 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]	26	25	1	0
PSLV-DL [2]	4	4	0	0
PSLV-QL [2]	2	2	0	0
Total as of December 2024 [update] [102]	61	58	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	11	0	0	11
Total	58	1	2	61

See also

• 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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External links

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