Polar Satellite Launch Vehicle (PSLV)

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
Manufacturer	ISRO
Country of origin	India
Size
Height	44 metres (144 ft)
Diameter	2.8 metres (9 ft 2 in)
Mass	294,000 kilograms (650,000 lb)
Stages	4
Capacity
Payload to LEO	3,250 kilograms (7,200 lb)
Payload to HCO	1,600 kilograms (3,500 lb)[1]
Payload to GTO	1,060 kilograms (2,300 lb)[1]
Launch history
Status	Active
Launch sites	Sriharikota
Total launches	17 PSLV: 10 PSLV-CA: 6 PSLV-XL: 1
Successes	15 PSLV: 8 PSLV-CA: 6 PSLV-XL: 1
Failures	1 (PSLV)
Partial failures	1 (PSLV)
Maiden flight	PSLV: 20 September 1993 PSLV-CA: 23 April 2007 PSLV-XL: 22 October 2008
Notable payloads	Chandrayaan-1
Boosters (Stage 0)
№ boosters	6
Engines	1 solid
Thrust	502.600 kN
Specific impulse	262 sec
Burn time	44 seconds
Fuel	HTPB (solid)
First stage
Engines	1 solid
Thrust	4,860 kN
Specific impulse	269 sec
Burn time	105 seconds
Fuel	HTPB (solid)
Second stage
Engines	1 Vikas (liquid)
Thrust	725 kN
Specific impulse	293 sec
Burn time	158 seconds
Fuel	N2O4/UDMH
Third stage
Engines	1 solid
Thrust	328 kN
Specific impulse	294 sec
Burn time	83 seconds
Fuel	Solid
Fourth stage
Engines	2 liquid
Thrust	14 kN
Specific impulse	308 sec
Burn time	425 seconds
Fuel	MMH/MON

The Polar Satellite Launch Vehicle (Hindi: ध्रुवीय उपग्रह प्रक्षेपण यान), 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 viable only from Russia. PSLV can also launch small size satellites into geostationary transfer orbit (GTO). The PSLV has launched 41 satellites (19 Indian and 22 from other countries) into a variety of orbits to date.
PSLV costs 17 million USD flyaway cost for each launch.

Contents [hide] 1 Vehicle description 2 Development 3 Variants 4 Launch history 5 References 6 External links

[edit] Vehicle description

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 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

[edit] Development

PSLV is designed and developed 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), also at Thiruvananthapuram. The solid propellant motors are processed by 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 altitude control problem was reported in the second and third stages. After this initial setback, ISRO met complete success with the third developmental launch in 1996. Further successful launches followed in 1997, 1999, and 2001.
PSLV continues to be the work horse of Indian satellite launches, especially for LEO satellites and the Chandrayaan Projects. It has undergone several improvements with each subsequent version, especially those involving thrust, efficiency as well as weight.

[edit] Variants

ISRO has envisaged a number of variants of PSLV to cater to different mission requirements. These configurations provide wide variations in payload capabilities ranging from 600 kg in LEO to 1900 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 April 23, 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.^[2] The fourth stage of the CA variant has 400 kg less propellant when compared to its standard version.^[2] It currently has capability to launch 1,100 kg to 622 km sun synchronous orbit.^[3]

PSLV-XL (Operational)

PSLV-XL is the uprated version of ISRO’s Polar Satellite Launch Vehicle in its standard configuration boosted by more powerful, stretched strap-on boosters.^[2] 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.^[4] 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.^[3] Future launches include the RISAT Radar Imaging Satellite.^[5]

Variant	Launches	Successes	Failures	Partial failures	Remarks
PSLV (Standard)	10	8	1	1
PSLV-CA (Core Alone)	6	6	0	0	Launched 10 satellites in one go.
PSLV-XL (Extended)	1	1	0	0	Launched Chandrayaan I.

PSLV-HP (Under development / Proposed)

As reported on the website of The New Indian Express newspaper (April 26, 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,^[3] and the payload capability will be raised to 2000 kg.^[3] 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.^[3][6]

[edit] Launch history

Vehicle	Variant	Date of Launch	Launch Location	Payload	Payload Mass	Mission Status	Note(s)
D1	PSLV	20 September 1993[7]	Sriharikota FLP*	IRS 1E	846 kg[7]	Failure	First development flight. Software error causes the vehicle to crash in to the Bay of Bengal 700 seconds after take off.
D2	PSLV	15 October 1994[8]	Sriharikota FLP*	IRS P2	804 kg[8]	Success	First successful development flight.
D3	PSLV	21 March 1996[9]	Sriharikota FLP*	IRS P3	920 kg[9]	Success
C1	PSLV	29 September 1997[10]	Sriharikota FLP*	IRS 1D	1,250 kg[10]	Partial failure	Sub-optimal injection of Satellite.
C2	PSLV	26 May 1999[11]	Sriharikota FLP*	OceanSat 1 DLR-Tubsat KitSat 3	1,050 kg[11] 107 kg[11] 45 kg[11]	Success	First successful commercial flight.
C3	PSLV	22 October 2001[12]	Sriharikota FLP*	TES Proba BIRD	1,108 kg[12] 94 kg[12] 92 kg[12]	Success	Speculated as a Spy Satellite.[13]
C4	PSLV	12 September 2002[14]	Sriharikota FLP*	METSAT 1 (Kalpana 1)	1,060 kg[14]	Success	First launch to Geostationary transfer orbit.[14]
C5	PSLV	17 October 2003[15]	Sriharikota FLP*	ResourceSat 1	1,360 kg[15]	Success
C6	PSLV	5 May 2005[16]	Sriharikota SLP**	CartoSat 1 HAMSAT	1560 kg[16] 42.5 kg[16]	Success
C7	PSLV	10 January 2007[17]	Sriharikota FLP*	CartoSat 2 SRE LAPAN-TUBsat PEHUENSAT-1	680 kg[17] 500 kg[17] 56 kg[17] 6 kg[17]	Success	Used a device called 'Dual Launch Adapter' for the first time to launch four satellites.[18] LAPAN-TUBsat is Indonesia’s first remote sensing satellite.
C8	PSLV-CA	23 April 2007[19]	Sriharikota SLP**	AGILE AAM	352 kg[19] 185 kg[19]	Success	First flight of the 'Core-Alone' version. ISRO's first exclusively commercial launch.[20]
C10	PSLV-CA	21 January 2008[21]	Sriharikota FLP*	TECSAR	295 kg[21]	Success	An Israeli reconnaissance satellite.[22]
C9	PSLV-CA	28 April 2008[23][24]	Sriharikota SLP**	Cartosat-2A IMS-1/TWSAT RUBIN-8 CanX-6/NTS CanX-2 Cute-1.7+APD II Delfi-C3 SEEDS-2 COMPASS-1 AAUSAT-II	690 kg 83 kg 8 kg 6.5 kg 3.5 kg 3 kg 2.2 kg 1 kg 1 kg 0.75 kg	Success	World Record for most satellites (10) launched in a single attempt.
C11	PSLV-XL	22 October 2008[25]	Sriharikota SLP**	Chandrayaan I	1,380 kg[25]	Success	First flight of the PSLV-XL version. India's first mission to the Moon.[26]
C12	PSLV-CA	20 April 2009[27]	Sriharikota SLP**	RISAT-2 ANUSAT	300 kg[27] 40 kg[27]	Success	India's first all weather observation spy satellite.[28] ANUSAT is the first satellite built by an Indian University.
C14	PSLV-CA	23 September 2009[29]	Sriharikota FLP*	Oceansat-2 Rubin 9.1 Rubin 9.2 SwissCube-1 BeeSat UWE-2 ITUpSAT1	960 kg[29] 8 kg[29] 8 kg[29] 1 kg[29] 1 kg[29] 1 kg[29] 1 kg[29]	Success	Rubin 9.1 and 9.2 were non-separable payloads,[30] orbited attached to the vehicle's fourth stage.[31][32] SwissCube-1[33] and ITUpSAT1[34] are Switzerland's and Turkey's first home-grown satellites launched into space.
C15	PSLV-CA	July 12, 2010 [35]	Sriharikota FLP*	Cartosat-2B ALSAT-2A AISSat-1[36] TIsat-1[37][38] STUDSAT	690 kg [39] 117 kg[39] 6.5 kg[39] 1 kg	Success	Main satellite Cartosat-2B and Algeria's ALSAT-2A along with AISSat-1, TIsat-1, and StudSat. TIsat-1 is the second ever Swiss satellite launched into Space. AISSat-1 and TIsat are part of NLS-6.[40][41]
C16	PSLV	20 April 2011[42]	Sriharikota	ResourceSat-2 X-Sat YouthSat	1206 kg[42] 106 kg[42] 92 kg[42]	Success	In the current flight, the standard version, with six solid strap-on booster motors strung around the first stage, was used.[42]
Planned launches
C17	PSLV	2011	Sriharikota	GSAT-12[43]		Planned
C18	PSLV	2011	Sriharikota	RISAT-1		Planned
C??	PSLV-??	2011	Sriharikota	& Megha-Tropiques SRMSAT		Planned
C??	PSLV-??	2011	Sriharikota	Astrosat		Planned

'*'FLP - First Launch Pad, Satish Dhawan Space Centre; **SLP - Second Launch Pad, Satish Dhawan Space Centre