Polar Satellite Launch Vehicle
PSLV-C8 (CA Variant) carrying the AGILE x-ray and γ-ray astronomical satellite of the ASI lifting off from Sriharikota
|Function||Medium lift launch system|
|Country of origin||India|
|Height||44 metres (144 ft)|
|Diameter||2.8 metres (9 ft 2 in)|
|Mass||294,000 kilograms (648,000 lb)|
|3,250 kilograms (7,170 lb)|
|1,600 kilograms (3,500 lb)|
|1,410 kilograms (3,110 lb)|
|Partial failures||1 (PSLV)|
|First flight||PSLV: 20 September 1993
PSLV-CA: 23 April 2007
PSLV-XL: 22 October 2008
|Notable payloads||Chandrayaan-1, Mars Orbiter Mission|
|Boosters (Stage 0)|
|Engines||1 x SLV per booster|
|Thrust||502.600 kilonewtons (112,989 lbf)|
|Total thrust||6 x 502.600 kilonewtons (112,989 lbf)|
|Specific impulse||262 seconds (4.37 min)|
|Burn time||44 seconds (0.73 min)|
|Engines||1 x PSLV-1|
|Thrust||4,860 kilonewtons (1,090,000 lbf)|
|Specific impulse||269 seconds (4.48 min)|
|Burn time||105 seconds (1.75 min)|
|Engines||1 x Vikas|
|Thrust||800 kilonewtons (180,000 lbf)|
|Specific impulse||293 seconds (4.88 min)|
|Burn time||158 seconds (2.63 min)|
|Engines||1 x PSLV-3|
|Thrust||328 kilonewtons (74,000 lbf)|
|Specific impulse||294 seconds (4.90 min)|
|Burn time||83 seconds (1.38 min)|
|Engines||2 x PSLV-4|
|Thrust||14 kilonewtons (3,100 lbf)|
|Specific impulse||308 seconds (5.13 min)|
|Burn time||425 seconds (7.08 min)|
The Polar Satellite Launch Vehicle, commonly known by its abbreviation PSLV, is an expendable launch system developed 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, commercially available only from Russia. PSLV can also launch small size satellites into geostationary transfer orbit (GTO).
As of 2014[update] the PSLV has launched 65 satellites / spacecrafts (30 Indian and 35 Foreign Satellites) into a variety of orbits. Some notable payloads launched by PSLV include India's Chandrayaan-1 lunar probe and the Mars Orbiter Mission. It is the most successful launch vehicle in ISRO, till date, with 25 consecutively successful flights out of 26 launches.
- 1 Development
- 2 Vehicle description
- 3 Launch history
- 4 Notable flights
- 5 Launch failures
- 6 See also
- 7 References
- 8 External links
PSLV was designed and developed in the early 1990s at Vikram Sarabhai Space Centre (VSSC), Thiruvananthapuram, Kerala. The inertial 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 are developed by the Liquid Propulsion Systems Centre (LPSC) at Mahendragiri (Tirunelveli),Tamil Nadu. The solid propellant motors are processed at Satish Dhawan Space Centre (SHAR) which also carries out launch operations.
After some delays, the PSLV had its first launch on 20 September 1993. Although all main engines performed as expected, an attitude control problem was reported in the second and third stages.[clarification needed] After this initial setback,[clarification needed] ISRO met complete success with the third developmental launch in 1996. After a partially unsuccessful launch in 1997, further successful launches followed in 1999 and 2001.
PSLV continues to be the workhorse of Indian satellite launches, especially for 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 India's Mars Orbiter Mission into an elliptical orbit around Earth. Mars Orbiter Mission is India's first interplanetary mission to planet Mars with an orbiter craft designed to orbit Mars in an elliptical orbit.
The PSLV has four stages using solid and liquid propulsion systems alternately. The first stage is one of the largest solid-fuel rocket boosters in the world and carries 138 tonnes of Hydroxyl-terminated polybutadiene (HTPB) bound propellant with a diameter of 2.8 m. The motor case is made of maraging steel. The booster develops a maximum thrust of about 4,430 kN. Six strap-on motors, four of which are ignited on the ground, augment the first stage thrust. Each of these solid propellant strap-on motors carries nine tonnes of HTPB propellant and produces 677 kN thrust. Pitch and yaw control of the PSLV during the thrust phase of the solid motor is achieved by injection of an aqueous solution of strontium perchlorate in the nozzle to constitute Secondary Injection Thrust Vector Control System (SITVC). The injection is stored in two cylindrical aluminum tanks strapped to the solid rocket motor and pressurized with nitrogen. There are two additional small liquid engine control power plants in the first stage, the Roll Control Thrusters (RCT), fixed radially opposite one on each side, between the triplet set of strap-on boosters. RCT is used for roll control during the first stage and the SITVC in two strap-on motors is for roll control augmentation.
The second stage employs the Vikas engine and carries 41.5 tonnes (40 tonnes till C-5 mission) of liquid propellant – Unsymmetrical Di-Methyl Hydrazine (UDMH) as fuel and Nitrogen tetroxide (N2O4) as oxidizer. It generates a maximum thrust of 800 kN (724 till C-5 mission). Pitch & yaw control is obtained by hydraulically gimbaled engine (±4°) and two hot gas reaction control for roll.
The third stage uses 7 tonnes of HTPB-based solid propellant and produces a maximum thrust of 324 kN. It has a Kevlar-polyamide fiber case and a submerged nozzle equipped with a flex-bearing-seal gimbaled nozzle (±2°) thrust-vector engine for pitch & yaw control. For roll control it uses the RCS (Reaction Control System) of[clarification needed] fourth stage.
The fourth and the terminal stage of PSLV has a twin engine configuration using liquid propellant. With a propellant loading of 2 tonnes (Mono-Methyl Hydrazine as fuel + Mixed Oxides of Nitrogen as oxidiser), each of these engines generates a maximum thrust of 7.4 kN. Engine is gimbaled (±3°) for pitch, yaw & roll control and for control during the coast phase uses on-off RCS. PSLV-C4 used a new lightweight carbon composite payload adapter to enable a greater GTO payload capability.
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 three operational versions of the PSLV — the standard (PSLV), the core-alone (PSLV-CA) without the six strap-on booster motors, and the (PSLV-XL) version, which carries more solid fuel in its strap-on motors than the standard version. All the three versions have proved to be unalloyed successes. These configurations provide wide variations in payload capabilities ranging from 3800 kg in LEO to 1800 kg in sun synchronous orbit.
- PSLV (Operational)
The standard version of the PSLV has four stages using solid and liquid propulsion systems alternately and six strap-on boosters. It currently has capability to launch 1,678 kg to 622 km into sun synchronous orbit.
- PSLV-CA (Operational)
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. Two small roll control modules and two first stage motor control injection tanks were still attached to the side of the first stage. The fourth stage of the CA variant has 400 kg less propellant when compared to its standard version. It currently has capability to launch 1,100 kg to 622 km sun synchronous orbit.
- PSLV-XL (Operational)
PSLV-XL is the uprated version of Polar Satellite Launch Vehicle in its standard configuration boosted by more powerful, stretched strap-on boosters. Weighing 320 tonnes at lift-off, the vehicle uses larger strap-on motors (PSOM-XL) to achieve higher payload capability. PSOM-XL uses larger 13.5m, 12 tonnes of solid propellants instead of 9 tonnes used in the earlier configuration of PSLV. On 29 December 2005, ISRO successfully tested the improved version of strap-on booster for the PSLV. The first version of PSLV-XL was the launch of Chandrayaan-1 by PSLV-C11. The payload capability for this variant is 1800 kg compared to 1600 kg for the other variants. Other launches include the RISAT Radar Imaging Satellite and GSAT-12.
|PSLV-CA (Core Alone)||9||9||0||0|
- PSLV-HP (Under development / Proposed)
As reported on the website of The New Indian Express newspaper (26 April 2007), PSLV project director N Narayanamoorthy spoke of another version being planned called the PSLV-HP, standing for ‘high performance.’ It will have improved strap-ons motors, and the payload capability will be raised to 2000 kg. The HP version will be used to launch a constellation of seven navigation satellites between 2010 and 2012. Among other things, the efficiency of the stage 4 engine will be improved in this version.
- PSLV-3S (Under development / Proposed)
ISRO is also considering the development of a three-stage version of the rocket without six strap-on boosters (with the second stage of the four-stage version removed) which will be capable of placing 500 kg to LEO.
As of 1 November 2013[update] the PSLV has made 25 launches, with 23 successfully reaching their planned orbits.[needs update] All launches have occurred from the Satish Dhawan Space Centre, known before 2002 as the Sriharikota Range.
|Flight||Variant||Launch date/time (UTC)||Launch pad||Payload||Payload mass||Result||Note(s)|
|D1||PSLV||20 September 1993
|First||IRS 1E||846 kg||Failure||Maiden flight; attitude control failure at second stage separation|
|D2||PSLV||15 October 1994
|D3||PSLV||21 March 1996
|C1||PSLV||29 September 1997
|First||IRS 1D||1,250 kg||Partial failure||First operational flight; fourth stage underperformed resulting in lower than planned orbit (Accuracy Loss)|
|C2||PSLV||26 May 1999
|Success||First commercial launch and first to carry multiple satellites|
|C3||PSLV||22 October 2001
|C4||PSLV||12 September 2002
|First||METSAT 1 (Kalpana 1)||1,060 kg||Success||India's first launch to GTO, GTO payload capability has reached 1200 kg from 2002 onward, compared to 1050 kg previously.|
|C5||PSLV||17 October 2003
|First||ResourceSat 1||1,360 kg||Success||Payload capability had been progressively increased by more than 600 kg since the first PSLV launch. Launch took place despite heavy rain.|
|C6||PSLV||5 May 2005
|Second|| CartoSat 1
|Success||First PSLV launch from the second launch pad|
|C7||PSLV||10 January 2007
|First|| CartoSat 2
|Success||First flight of hardware upgrade, first launch of reentry capsule (SRE)|
|C8||PSLV-CA||23 April 2007
|Success||First flight of the 'Core-Alone' configuration.
ISRO's first exclusively commercial launch.
|C10||PSLV-CA||21 January 2008
|First||TecSAR||295 kg||Success||ISRO's first fully commercially launch.|
|C9||PSLV-CA||28 April 2008
|C11||PSLV-XL||22 October 2008
|Second||Chandrayaan-1||1,380 kg||Success||First flight of the PSLV-XL configuration, first Indian Lunar probe.|
|C12||PSLV-CA||20 April 2009
|Success||India's first radar imaging satellite (RISAT).|
|C14||PSLV-CA||23 September 2009
|Success||Rubin 9.1 and 9.2 intentionally remained attached to the fourth stage. SwissCube-1 was the first Swiss satellite, and ITUpSAT1 was the first satellite to be constructed in Turkey.|
|C15||PSLV-CA||12 July 2010
|Success||AISSat-1 and TIsat are part of NLS-6.|
|C16||PSLV||20 April 2011
|C17||PSLV-XL||15 July 2011
|Second||GSAT-12||1410 kg||Success||First use of Vikram flight computer.|
|C18||PSLV-CA||12 October 2011
|C19||PSLV-XL||26 April 2012
|C21||PSLV-CA||9 September 2012
|First|| SPOT-6 (France)
||720 kg 15 kg||Success||mRESINS tested avionics for future PSLV launches|
|C20||PSLV-CA||25 February 2013
|Success||TUGSAT-1 and UniBRITE were the first Austrian satellites.|
|C22||PSLV-XL||1 July 2013
|First||IRNSS-1A||1425 kg||Success||India’s first regional navigation satellite|
|C25||PSLV-XL||5 November 2013
|First||Mars Orbiter Mission||1,350 kg||Success||India's first Mars mission.|
|C24||PSLV-XL||4 April 2014
|First||IRNSS-1B||1,432 kg||Success||India's second regional navigation satellite|
|C23||PSLV-CA||June 2014||First|| SPOT-7
PSLV flight D1
This was the first developmental flight of the PSLV d1. The IRS-1E satellite which was proposed to be launched was derived from the engineering model of IRS-1A incorporating a similar camera and an additional German-built monocular electro-optical stereo scanner. Even though the mission was a failure, the launch team and an expert committee appointed thereafter noted that the mission had validated many technologies and that most sub-systems had performed optimally.
PSLV flight C1
PSLV flight C2
In the flight sequence, IRS-P4 was injected first, followed by KITSAT-3 and DLR-TUBSAT in that order. The mission was supported by ISTRAC network of ground stations located at Bangalore, Sriharikota, Lucknow, Mauritius, Bearslake, Russia and Biak, Indonesia. During the initial phase of the mission the ground station at Wilhem in Germany also provided network support. Upon injection of the satellites, data from the IRS-P4 was received at Hyderabad while KITSAT-3 data was received at the ground station in Korea and the data from the TUBSAT was received at the university ground station in Berlin.
PSLV flight C5
The launch took place despite heavy rain which commenced half an hour before the scheduled launch. However, ISRO decided to go ahead with the launch as despite rain, there were no strong winds and there were weather reports suggested that the monsoons would set in by the next day. Following the launch, a press statement released by the Minister of State (Space) announced that the PSLV has been proposed for the Chandrayan 1 moon mission.
PSLV flight C6
The President, Dr. Abdul Kalam, witnessed the launch from the Mission Control Centre. It was the first PSLV launch from second pad, using integrate-transfer-and-launch technology. After its integration in the Vehicle Assembly Building, the PSLV-C6 was transported on rails to the Umbilical Tower (UT) located one km away using the Mobile Launch Pedestal where the final operations were carried out.
PSLV flight C7
- first use of DLA (Dual Payload Adapter) to launch 2 primary satellites in time
- reduction of propellant from 2.5 tonne to 2 tonne in the fourth liquid propellant stage
- incorporation of a video imaging system to capture payload and DLA separation events
- altitude based day of launch wind-biased steering programme during Open Loop Guidance
- removal of Secondary Injection Thrust Vector Control (SITVC) system for one of the strapons ignited in the air.
PSLV flight C9
The fourth stage first fired Cartosat-2A into orbit at an altitude of 637 km about 885 seconds after lift-off. About 45 seconds later, it propelled IMS-1 into the orbit. Then the six nano satellites belonging to a cluster called NLS-4 were injected into orbit at intervals of 20 seconds each. NLS-5, a single satellite, flew out and finally the tenth satellite Rubin-8 went along with the fourth stage into orbit. Two satellites belonged to India and the remaining were nanosatellites built by universities in different countries.
PSLV flight C21
Launch attended by Prime Minister Manmohan Singh. mRESINS ( mini Redundant Strapdown Inertial Navigation System) bolted to the vehicle's fourth stage, have tested avionics for future PSLV missions.
PSLV flight C22
Earlier launch date for PSLV C22 was fixed as 12 June 2013 (1.01AM) but the launch had been postponed because of a technical snag in the 2nd stage.
The launch of the first satellite in the Indian Regional Navigation Satellite System of the Indian Space Research Organization (ISRO), scheduled for June 12 from Sriharikota, has been postponed by 14 days after an anomaly was discovered just 11 days before launch. The satellite IRNSS-1A, which would be the first in a series of seven navigation satellites was scheduled to be launched on board the Polar Satellite Launch Vehicle (PSLV) C22 at 1.01 am on June 12. The satellite has undergone its pre-launch checks successfully. However, ISRO said the launch vehicle had an anomaly in one electro-hydraulic control actuators. “During the electrical checks of the launch vehicle, an anomaly was observed in one of the electro-hydraulic control actuators in the second stage. It has been decided to replace this actuator,” a statement by ISRO said. Officials added that the replacement of the actuator would take two weeks and it would be carried out at the launch pad and vehicle assembly area.
ISRO then replaced a faulty component in the PSLV-C22 rocket and rescheduled the flight of the IRNSS-1A satellite on it for 11:41 p.m. on July 1. PSLV-C22, successfully launched IRNSS-1A, the first satellite in the Indian Regional Navigation Satellite System (IRNSS).
At the completion of the countdown, PSLV-C22 lifted off from the First Launch Pad at 23:41 hrs 1 July 2013 with the ignition of the first stage and four strap-on motors of the launch vehicle.
PSLV flight C25
The Mars Orbiter Mission (MOM), informally called Mangalyaan is a Mars orbiter that was successfully injected into Earth orbit on 5 November 2013 at 2:38 PM IST (9:08 UTC) atop a PSLV-XL launch vehicle from Satish Dhawan Space Centre, Shriharikota (SHAR).
On September 20, 1993 a PSLV-D1, the first developmental flight, rocket failed during launch. A significant attitude disturbance occurred during second to third-stage separation, causing the attitude control command to exceed its maximum value. Because of the programming error in the pitch control loop of the digital autopilot software in the guidance and control processor, the required reversal of command polarity did not take place, causing the pitch loop to become unstable, resulted in loss of attitude control and failure to achieve orbit. The attitude control disturbance was traced to failure of one of the retro rockets designed to pull the burnt second stage away from the third stage. The vehicle crashed into the Bay of Bengal 700 seconds after take off.
On September 29, 1997 a PSLV-C1 rocket has failed during launch. Anomalous interaction between the primary and secondary pressure regulators of the fourth stage caused a reduction in propellant flow and thrust after 250 s of burn time. As a result, the fourth stage was shut down by a software override timer after burning 435 s, before reaching the target orbit or depleting propellant. The injection velocity was 140 m/s low, resulting in orbit 301x823 km instead of the planned 817 km circular SSO. Initially, a leak of helium gas from one of the components in the fourth stage was suspected, similar to recent Long March 3 launch failure, but later ruled out. Resulted orbit was partially corrected using satellite on-board thrusters, thereby raising the perigee to 737 km, while the apogee remained at 821 km.
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