ISRO Future Launch Vehicles

I have come to collect Indian Space Research Organisation (ISRO) Future Launch Vehicles , so if you have any info related to its Unified Launch Vehicle then will you plz let me know about the same ?

[KunwarR]

As you want here I am telling Unified Launch Vehicle (ULV) is a development project by the Indian Space Research Organisation (ISRO) whose core objective is to design a modular architecture that could eventually replace the PSLV, GSLV Mk I/II and LVM3 with a single family of launchers.

Unified Launch Vehicle info

Function Medium- to Heavy-lift launch vehicle
Manufacturer Indian Space Research Organisation
Country of origin India
Size
Mass 270,000 to 700,000 kg (600,000 to 1,540,000 lb)
Stages 2
Capacity
Payload to LEO 6 × S-13: 4,500 kg (9,900 lb)
2 × S-60: 10,000 kg (22,000 lb)
2 × S-139: 12,000 kg (26,000 lb)
2 × S-200: 15,000 kg (33,000 lb)
Payload to GTO 6 × S-13: 1,500 kg (3,300 lb)
2 × S-60: 3,000 kg (6,600 lb)
2 × S-139: 4,500 kg (9,900 lb)
2 × S-200: 6,000 kg (13,000 lb)

Boosters – S-13
No. boosters 6
Length 12 m (39 ft)
Diameter 1 m (3 ft 3 in)
Propellant mass 12,200 kg (26,900 lb)
Motor S-13
Thrust 716 kN (161,000 lbf)
Burn time 70 seconds
Fuel HTPB
Boosters – S-60
No. boosters 2
Propellant mass 60,000 kg (130,000 lb)
Motor S-60
Fuel HTPB
Boosters – S-139
No. boosters 2
Length 20.1 m (66 ft)
Diameter 2.8 m (9 ft 2 in)
Propellant mass 138,200 kg (304,700 lb)
Motor S-139
Thrust 4,700 kN (1,100,000 lbf)
Burn time 100 seconds
Fuel HTPB
Boosters – S-200
No. boosters 2
Length 25 m (82 ft)
Diameter 3.2 m (10 ft)
Propellant mass 207,000 kg (456,000 lb)
Motor S-200
Thrust 4,658 kN (1,047,000 lbf) each
Total thrust 9,316 kN (2,094,000 lbf)
Specific impulse 274.5 (vacuum)
Burn time 130 sec
Fuel HTPB[8]
Core stage – SC-160
Propellant mass 160,000 kg (350,000 lb)
Engines SCE-200
Thrust SL: 1,820 kN (410,000 lbf)
Vac: 2,030 kN (460,000 lbf)
Specific impulse SL: 299 s (2.93 km/s)
Vac: 335 s (3.29 km/s)
Burn time 259 sec
Fuel Kerosene / LOX
Upper stage – C-30
Propellant mass 30,000 kg (66,000 lb)
Engines CE-20
Thrust 200 kN (45,000 lbf)
Specific impulse 443 s (4.34 km/s)
Burn time 650 sec
Fuel LH2 / LOX