Unified Launch Vehicle

Unified Launch Vehicle
Function Medium- to Heavy-lift launch vehicle
Manufacturer Indian Space Research Organisation[1]
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[2][3][4]
No. boosters 6
Length 12 m (39 ft)[5]
Diameter 1 m (3 ft 3 in)[5]
Propellant mass 12,200 kg (26,900 lb)[5]
Motor S-13
Thrust 716 kN (161,000 lbf)[5]
Burn time 70 seconds[5]
Fuel HTPB
Boosters - S-60[2][3]
No. boosters 2
Propellant mass 60,000 kg (130,000 lb)
Motor S-60
Fuel HTPB
Boosters - S-139[2][3]
No. boosters 2
Length 20.1 m (66 ft)[6]
Diameter 2.8 m (9 ft 2 in)[6]
Propellant mass 138,200 kg (304,700 lb)[6]
Motor S-139
Thrust 4,700 kN (1,100,000 lbf)[7]
Burn time 100 seconds[6]
Fuel HTPB
Boosters - S-200
No. boosters 2
Length 25 m (82 ft)[8]
Diameter 3.2 m (10 ft)[8]
Propellant mass 207,000 kg (456,000 lb)[8]
Motor S-200
Thrust 4,658 kN (1,047,000 lbf) each
Total thrust 9,316 kN (2,094,000 lbf)[8]
Specific impulse 274.5 (vacuum)[8]
Burn time 130 sec[8]
Fuel HTPB[8]
Core stage - SC-160
Propellant mass 160,000 kg (350,000 lb)
Engines SCE-200[3]
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[3]
Thrust 200 kN (45,000 lbf)
Specific impulse 443 s (4.34 km/s)
Burn time 650 sec
Fuel LH2 / LOX

The 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.[1] The design may include a heavy-lift variant dubbed HLV.

Design

As of May 2013, based on ISRO data, the design comprised a common core and upper stage, with four different booster sizes.[9] All four versions of the boosters are solid motors, with at least three versions reusing current motors from the PSLV, GSLV Mk I/II and LVM3.[2] The core, known as the SC160 (Semi-Cryogenic stage with 160 tonnes of propellant, in the ISRO nomenclature), would have 160,000 kg (350,000 lb) of Kerosene / LOX propellant and be powered by a single SCE-200 rocket engine. The upper stage, known as the C30 (Cryogenic stage with 30 tonnes of propellant) would have 30,000 kg (66,000 lb) of LH2 / LOX propellant and be powered by a single CE-20 engine.[1][10]

The four booster options are:

A potential heavy-lift variant (HLV) of the unified launcher capable of placing up to 9 ton class of spacecrafts into Geosynchronous Transfer Orbit would include:[1][10]

Comparable rockets

See also

References

  1. 1 2 3 4 Brügge, Norbert. "ULV (LMV3-SC)". B14643.de. Retrieved 2015-08-14.
  2. 1 2 3 4 "ISRO Unified Launch Vehicle (ULV)". NASAspaceflight. 2013-05-03. Retrieved 2015-08-14.
  3. 1 2 3 4 5 Brügge, Norbert. "Propulsion ULV". B14643.de. Retrieved 2015-08-14.
  4. ↑ "PSLV". ISRO. Retrieved 2015-08-14.
  5. 1 2 3 4 5 PSLV-C28 DMC3 Mission Brochure (PDF). ISRO. Retrieved 2015-08-14.
  6. 1 2 3 4 GSLV-D5 GSAT-14 Mission Brochure (PDF). ISRO. Retrieved 2015-08-14.
  7. ↑ "GSLV". ISRO. Retrieved 2015-08-14.
  8. 1 2 3 4 5 6 7 "LVM3". ISRO. Retrieved 2015-08-14.
  9. ↑ "ISRO Unified Launch Vehicle Update". Antariksh Space. 2013-05-03. Retrieved 2016-05-25.
  10. 1 2 Brügge, Norbert. "LVM3, ULV & HLV". B14643.de. Retrieved 2015-08-14.
  11. ↑ ""Indigenous Development of Materials for Space Programme" By Dr A. S. Kiran Kumar Presentation Slides. Indian Institute Of Science iisc.ernet.in Date: 21 August 2015.".
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