As you asking I am telling Polar Satellite Launch Vehicle, (PSLV) is an expendable launch system developed and operated by the Indian Space Research Organisation (ISRO).

Polar Satellite Launch Vehicle, (PSLV) 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 Polar Satellite Launch Vehicle, (PSLV) , commercially available only from Russia. PSLV can also launch small size satellites into geostationary transfer orbit (GTO):

Function Medium lift launch system
Manufacturer ISRO
Country of origin India
Cost per launch PSLV-CA 90 crore($15M)
Size
Height 44 metres (144 ft)
Diameter 2.8 metres (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)
Stages 4
Capacity
Payload to LEO 3,250 kg (7,170 lb)
Payload to SSO(600 km) 1,750 kg (3,860 lb)
Payload to Sub-GTO/GTO 1,425 kg (3,142 lb)
Launch history
Status Active
Launch sites Sriharikota
Total launches 34
PSLV-G: 11
PSLV-CA: 11
PSLV-XL: 12
Successes 32
PSLV-G: 9
PSLV-CA: 11
PSLV-XL: 12
Failures 1 (PSLV-G)
Partial failures 1 (PSLV-G)
First flight PSLV: 20 September 1993
PSLV-CA: 23 April 2007
PSLV-XL: 22 October 2008
Notable payloads Chandrayaan-1, Mars Orbiter Mission, Astrosat

Boosters (PSLV-G) - S9
No. boosters 6
Thrust 510 kN (110,000 lbf)
Specific impulse 262 s (2.57 km/s)
Burn time 44 seconds
Fuel Hydroxyl-terminated polybutadiene
Boosters (PSLV-XL) - S12
No. boosters 6
Thrust 719 kN (162,000 lbf)
Specific impulse 262 s (2.57 km/s)
Burn time 49 seconds
Fuel Hydroxyl-terminated polybutadiene
First stage
Propellant mass 138,000 kg (304,000 lb)
Motor S139
Thrust 4,800 kN (1,100,000 lbf)
Specific impulse 237 s (2.32 km/s) (sea level)
269 s (2.64 km/s) (vacuum)
Burn time 105 seconds
Fuel HTPB
Second stage
Engines 1 Vikas
Thrust 799 kN (180,000 lbf)
Specific impulse 293 s (2.87 km/s)
Burn time 158 seconds
Fuel N2O4/UDMH
Third stage
Motor HPS3
Thrust 240 kN (54,000 lbf)
Specific impulse 295 s (2.89 km/s)
Burn time 83 seconds
Fuel Hydroxyl-terminated polybutadiene
Fourth stage
Engines 2 x L-2-5
Thrust 15.2 kN (3,400 lbf)
Specific impulse 308 s (3.02 km/s)
Burn time 425 seconds
Fuel MMH/MON