Unified Launch Vehicle

HLV (Heavy Lift Launch Vehicle)
Function Mid-Heavy lift launch vehicle
Manufacturer Indian Space Research Organisation[1]
Country of origin India
Size
Mass 270,000 kg (600,000 lb) to 700,000 kg (1,500,000 lb)
Stages 2
Capacity
Payload to LEO 6 x S13:4,500 kg (9,900 lb)
2 x S60:10,000 kg (22,000 lb)
2 x S139:12,000 kg (26,000 lb)
2 x S200:15,000 kg (33,000 lb)
Payload to GTO 6 x S13:1,500 kg (3,300 lb)
2 x S60:3,000 kg (6,600 lb)
2 x S139:4,500 kg (9,900 lb)
2 x S200:6,000 kg (13,000 lb)
Boosters - S-12[2][3][4]
No. boosters 6
Length 12 m (470 in)[5]
Diameter 1 m (39 in)[5]
Propellant mass 12,200 kg (26,900 lb)[5]
Motor S12
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 S60
Thrust
Fuel HTPB
Boosters - S-139[2][3]
No. boosters 2
Length 20.1 m (790 in)[6]
Diameter 2.8 m (110 in)[6]
Propellant mass 138,200 kg (304,700 lb)[6]
Motor S139
Thrust 4,800 kN (1,100,000 lbf)[7]
Burn time 100 seconds[6]
Fuel HTPB
Boosters - S200
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 S200
Thrust 4,658 kN (475.0 tf) each[8][9]
Total thrust 9,316 tf (91,360 kN; 9,169 LTf; 10,269 STf)
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 HLV or Heavy Lift Launch Vehicle is a launch vehicle in development by the Indian Space Research Organisation (ISRO).[10] The project core objective is to design a modular architecture that will enable the replacement of the PSLV, GSLV Mk I/II and GSLV Mk III with a single family of launchers.[11]

Design

As of June 2015, the design disclosed by specialized site is of a common core and upper stage, with four different boosters.[10] All four version of boosters are solid motors, with at least three versions reusing current motors from the PSLV, GSLV Mk I/II and GSLV Mk III.[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.[11]

The four booster options are:

Comparable rockets

See also

References

  1. ↑ Brügge, Norbert. "LVM3, ULV & HLV". 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. ↑ "India to test world's third largest solid rocket booster". Science and Technology Section. The Hindu News Paper. 2009-12-07. Retrieved 2009-12-07.
  10. 1 2 Lift-launch-vehicle.html "ISRO Unified Launch vehicle" Check |url= value (help). Antariksh Space. 2012-01-02. Retrieved 2015-08-14.
  11. 1 2 Brügge, Norbert. "ULV (LMV3-SC)". B14643.de. Retrieved 2015-08-14.

External links

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