Polar Satellite Launch Vehicle
PSLV C35 on launch pad
|Function||Medium lift launch system|
|Country of origin||India|
|Cost per launch||$21-31 million ₹130-200 crore |
|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)
|Payload to LEO||3,800 kg (8,400 lb)|
|Payload to SSO(620 km)||1,750 kg (3,860 lb)|
|Payload to Sub-GTO||1,425 kg (3,142 lb)|
|Payload to GTO||1,200 kg (2,600 lb)|
|First flight||PSLV: 20 September 1993|
PSLV-CA: 23 April 2007
PSLV-XL: 22 October 2008
|Notable payloads||Chandrayaan-1, Mars Orbiter Mission, Astrosat, SRE-1, NAVIC|
|Boosters (PSLV-G) – S9|
|Thrust||510 kN (110,000 lbf)|
|Specific impulse||262 s (2.57 km/s)|
|Burn time||44 seconds|
|Boosters (PSLV-XL) – S12|
|Length||12 m (39 ft)|
|Diameter||1 m (3.3 ft)|
|Propellant mass||12,200 kg (26,900 lb) each|
|Thrust||703.5 kN (158,200 lbf) |
|Specific impulse||262 s (2.57 km/s)|
|Burn time||70 seconds |
|Length||20 m (66 ft)|
|Diameter||2.8 m (9.2 ft)|
|Propellant mass||138,200 kg (304,700 lb) each|
|Thrust||4,846.9 kN (1,089,600 lbf) |
|Specific impulse||237 s (2.32 km/s) (sea level)|
269 s (2.64 km/s) (vacuum)
|Burn time||110 seconds |
|Length||12.8 m (42 ft)|
|Diameter||2.8 m (9.2 ft)|
|Propellant mass||42,000 kg (93,000 lb) each|
|Thrust||803.7 kN (180,700 lbf) |
|Specific impulse||293 s (2.87 km/s)|
|Burn time||133 seconds |
|Length||3.6 m (12 ft)|
|Diameter||2 m (6.6 ft)|
|Propellant mass||7,600 kg (16,800 lb) each|
|Thrust||240 kN (54,000 lbf)|
|Specific impulse||295 s (2.89 km/s)|
|Burn time||83 seconds|
|Length||3 m (9.8 ft)|
|Diameter||1.3 m (4.3 ft)|
|Propellant mass||2,500 kg (5,500 lb) each|
|Engines||2 x L-2-5|
|Thrust||14.66 kN (3,300 lbf) |
|Specific impulse||308 s (3.02 km/s)|
|Burn time||425 seconds|
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, commercially available only from Russia. PSLV can also launch small size satellites into Geostationary Transfer Orbit (GTO).
Some notable payloads launched by PSLV include India's first lunar probe Chandrayaan-1, India's first interplanetary mission, Mars Orbiter Mission (Mangalyaan) and India's first space observatory, Astrosat.
PSLV has gained credence as a small satellite launcher due its numerous multi-satellite deployment campaigns with auxiliary payloads usually ride sharing along an Indian primary payload. 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 most number of satellites sent to space on a single launch.
Studies to develop a vehicle capable of delivering 600 kg payload to 550 km Sun-synchronous orbit from SHAR began in 1978. Among 35 proposed configurations, four were picked and 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 Perigee-Apogee System (PAS) was being considered.
By 1981, confidence grew in remote sensing spacecraft development with launch of Bhaskara-1 and the PSLV project objectives were upgraded to have vehicle deliver 1000 kg payload in 900 km SSO. As technology transfer of Viking rocket engine firmed up, a new lighter configuration shifting away from relying on three large solid boosters was proposed by team led by APJ Abdul Kalam and eventually selected. Funding was approved in July 1982 for finalized design employing a single large S125 solid core as first stage with six 9 tonne strap-ons (S9) derived from 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 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 first stage. Apart from increasing precision, liquid upper stage also absorbed any deviation in performance of solid third stage. Final configuration of PSLV D1 to fly in 1993 was (6 × S9 + S125) + L37.5 + S7 + L2.
The inertial navigation systems are developed by ISRO Inertial Systems Unit (IISU) at Thiruvananthapuram. The liquid propulsion stages for the second and fourth stages of PSLV as well as the Reaction control systems (RCS) are developed by the Liquid Propulsion Systems Centre (LPSC) at Mahendragiri near Tirunelveli, Tamil Nadu. 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. 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. After this initial setback, the PSLV successfully completed its second mission in 1994. The fourth launch of PSLV suffered a partial failure in 1997, leaving its payload in a lower than planned orbit. By Nov 2014 the PSLV had launched 34 times with no further failures. (Although launch 41: Aug 2017 PSLV-C39 was unsuccessful.)
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.
ISRO is planning to privatise the operations of PSLV and will work through a joint venture with private industries. The integration and launch will be managed an industrial consortium through Antrix Corporation.
In June 2018, the Union Cabinet approved ₹6,131 crore (US$850 million) for 30 operational flights of the PSLV scheduled to take place between 2019 and 2024.
The PSLV has four stages using solid and liquid propulsion systems alternately. The first stage, one of the largest solid rocket boosters in the world, carries 138 t (304,000 lb) tonnes of hydroxyl-terminated polybutadiene-bound (HTPB) propellant and develops a maximum thrust of about 4,800 kilonewtons (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 kilograms (66,600 lb). Pitch and yaw control during first stage flight is provided by the Secondary Injection Thrust Vector Control System (SITVC), which injects an aqueous solution of strontium perchlorate into the nozzle to produce asymmetric thrust. The solution is stored in two cylindrical aluminium tanks strapped to the solid rocket motor and pressurised with nitrogen. Roll control is provided by two small liquid engines on opposite sides of the stage, the Roll Control Thrusters (RCT).
On the PSLV 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 (20,000 lb) or 12 t (26,000 lb) (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. The PSLV-CA uses no strap-on boosters.
The second stage employs the Vikas engine and carries 41.5 t (91,000 lb) of liquid propellant – unsymmetrical dimethylhydrazine (UDMH) as fuel and nitrogen tetroxide (N2O4) as oxidiser. It generates a maximum thrust of 800 kN (180,000 lbf). The engine is hydraulically gimbaled (±4°) to provide pitch and yaw control, while roll control is provided by two hot gas reaction control motors.
The third stage uses 7 t (15,000 lb) of hydroxyl-terminated polybutadiene-based solid propellant and produces a maximum thrust of 240 kN (54,000 lbf). It has a Kevlar-polyamide fibre case and a submerged nozzle equipped with a flex-bearing-seal gimbaled nozzle (±2°) thrust vector engine for pitch & yaw control. Roll control is provided by the fourth stage reaction control system (RCS).
The fourth stage is powered by regeneratively cooled twin engines, burning monomethylhydrazine (MMH) and mixed oxides of nitrogen (MON). Each engine generates 7.4 kN (1,700 lbf) thrust and is gimbaled (±3°) to provide pitch, yaw & roll control during powered flight. Coast phase attitude control is provided by RCS. The stage carries up to 2,500 kg (5,500 lb) of propellant in the PSLV and PSLV-XL and 2,100 kg (4,600 lb) in the PSLV-CA.
PSLV is developed with a group of wide-range control units.
|Stage 1||Stage 2||Stage 3||Stage 4|
|Pitch||SITVC||Engine Gimbal||Flex Nozzle||Engine Gimbal|
|Yaw||SITVC||Engine Gimbal||Flex Nozzle||Engine Gimbal|
|Roll||RCT and SITVC in 2 PSOMs||HRCM Hot Gas Reaction Control Motor||PS4 RCS||PS4 RCS|
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 any strap-on motors, and the (PSLV-XL) version, with six extended length (XL) strap-on motors carrying 12 tonnes of HTPB based propellant each. 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.
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 last operational launch of PSLV-G before its discontinuation.
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. The fourth stage of the CA variant has 400 kg (880 lb) less propellant when compared to its standard version. It currently has capability to launch 1,100 kg (2,400 lb) to 622 km (386 mi) Sun synchronous orbit.
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. Weighing 320 t (710,000 lb) at lift-off, the vehicle uses larger strap-on motors (PSOM-XL or S12) to achieve higher payload capability. On 29 December 2005, ISRO successfully tested the improved version of strap-on booster for the PSLV. 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 SSO. Other launches include the RISAT (Radar Imaging Satellite) and GSAT-12. All three PSLV launches in 2017 were of the -XL.
|PSLV-CA (Core Alone)||12||12||0||0|
|Total till September 2018||44||41||2||1|
- 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.
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