Unified Launch Vehicle

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 GSLV Mk III with a single family of launchers.[1] The design may include a heavy-lift variant dubbed HLV, consisting of the SC-160 stage and two solid rocket boosters, as well as a super heavy-lift variant called SHLV with a cluster stage of five SCE-200 engines .[1][10] As SCE-200 will only fly after the successful completion of the Gaganyaan program, the launcher will not fly before 2022.[2]

Unified Launch Vehicle
FunctionMedium- to Heavy-lift launch vehicle
ManufacturerIndian Space Research Organisation[1]
Country of originIndia
Size
Mass270,000 to 700,000 kg (600,000 to 1,540,000 lb)
Stages2
Capacity
Payload to LEO6 × 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)
HLV(Variant):20,000 kg (44,000 lb)
SHLV(Variant):41,300 kg (91,100 lb)
Payload to GTO6 × 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)
HLV(Variant):10,000 kg (22,000 lb)
SHLV(Variant):16,300 kg (35,900 lb)
Launch history
First flightAfter 2022[2]
Boosters – S-13[3][4][5]
No. boosters6
Length12 m (39 ft)[6]
Diameter1 m (3 ft 3 in)[6]
Propellant mass13,000 kg (29,000 lb)[6]
MotorS-13
Thrust716 kN (161,000 lbf)[6]
Burn time80 seconds[6]
FuelHTPB
Boosters – S-60[3][4]
No. boosters2
Propellant mass60,000 kg (130,000 lb)
MotorS-60
FuelHTPB
Boosters – S-139[3][4]
No. boosters2
Length20.1 m (66 ft)[7]
Diameter2.8 m (9 ft 2 in)[7]
Propellant mass138,200 kg (304,700 lb)[7]
MotorS-139
Thrust4,700 kN (1,100,000 lbf)[8]
Burn time100 seconds[7]
FuelHTPB
Boosters – S-200
No. boosters2
Length25 m (82 ft)[9]
Diameter3.2 m (10 ft)[9]
Propellant mass207,000 kg (456,000 lb)[9]
MotorS-200
Thrust4,658 kN (1,047,000 lbf) each
Total thrust9,316 kN (2,094,000 lbf)[9]
Specific impulse274.5 (vacuum)[9]
Burn time130 sec[9]
FuelHTPB[9]
Core stage – SC-160
Propellant mass160,000 kg (350,000 lb)
EnginesSCE-200[4]
ThrustSL: 1,820 kN (410,000 lbf)
Vac: 2,030 kN (460,000 lbf)
Specific impulseSL: 299 s (2.93 km/s)
Vac: 335 s (3.29 km/s)
Burn time259 sec
FuelKerosene / LOX
Upper stage – C-30
Propellant mass30,000 kg (66,000 lb)
EnginesCE-20[4]
Thrust200 kN (45,000 lbf)
Specific impulse443 s (4.34 km/s)
Burn time650 sec
FuelLH2 / LOX

Design

As of May 2013, based on ISRO data, the design comprised a common core and upper stage, with four different booster sizes.[11] 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.[3] 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:

  • 6 × S-13, slightly larger than the S-12 on PSLV, to burn longer;
  • 2 × S-60, which appears to be a new solid motor development;
  • 2 × S-139, which is the first stage of PSLV and GSLV Mk I/II;
  • 2 × S-200, like on the LVM3.


Heavy Lift Launch Vehicle(HLV-Variant):-

A potential heavy-lift variant (HLV) of the unified launcher capable of placing up to 10 ton class of spacecrafts into Geosynchronous Transfer Orbit would include:[1][12][10]

  • A larger dual S-250 solid strap-on boosters as compared to the S-200 boosters used in LVM3;
  • A L-400 semi-cryogenic core stage, with 400 tonnes of propellant, using a cluster of five SCE-200 engine's;
  • A L-27 cryogenic third stage, with 27 tonnes of propellant, using CE-20 engine.

Comparable rockets
gollark: Alternatively, invoice your brother for the cost of all relevant parts.
gollark: Make one, but subtly sabotage it so he begins disliking fidget spinners.
gollark: If they're on the same network it should work. Just get the IP of the opening one.
gollark: Social norms are orthogonal to actual ethical issues.
gollark: A bigger issue which the article doesn't mention is that any sort of laser powerful enough to visibly affect the moon would probably be ridiculously damaging to anything on the ground with it.

See also

References
  1. Brügge, Norbert. "ULV (LMV3-SC)". B14643.de. Retrieved 14 August 2015.
  2. "Episode 90 – An update on ISRO's activities with S Somanath and R Umamaheshwaran". AstrotalkUK. 24 October 2019. Retrieved 30 October 2019.
  3. "ISRO Unified Launch Vehicle (ULV)". NASAspaceflight. 3 May 2013. Retrieved 14 August 2015.
  4. Brügge, Norbert. "Propulsion ULV". B14643.de. Retrieved 14 August 2015.
  5. "PSLV". ISRO. Retrieved 14 August 2015.
  6. PSLV-C28 DMC3 Mission Brochure (PDF). ISRO. Retrieved 14 August 2015.
  7. GSLV-D5 GSAT-14 Mission Brochure (PDF). ISRO. Retrieved 14 August 2015.
  8. "GSLV". ISRO. Retrieved 14 August 2015.
  9. "LVM3". ISRO. Retrieved 14 August 2015.
  10. Brügge, Norbert. "LVM3, ULV & HLV". B14643.de. Retrieved 14 August 2015.
  11. "ISRO Unified Launch Vehicle Update". Antariksh Space. 3 May 2013. Retrieved 25 May 2016.
  12. ""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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