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:

• 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.

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]

• A larger dual S-250 solid strap-on boosters as compared to the S-200 boosters used in LVM3;
• A semi-cryogenic core stage similar to LVM3 with SCE-200 engine;
• A semi cryogenic third stage with a new CE-50 engine;
• A new fourth stage with cryogenic C10 engine.^[11]

Comparable rockets

• Angara
• Atlas V
• Delta IV
• H3

See also

• Comparison of orbital launchers families
• Comparison of orbital launch systems
• GSLV Mk I/II
• LVM3
• ISRO Orbital Vehicle
• PSLV

References

1. Brügge, Norbert. "ULV (LMV3-SC)". B14643.de. Retrieved 2015-08-14.
2. "ISRO Unified Launch Vehicle (ULV)". NASAspaceflight. 2013-05-03. Retrieved 2015-08-14.
3. Brügge, Norbert. "Propulsion ULV". B14643.de. Retrieved 2015-08-14.
4. "PSLV". ISRO. Retrieved 2015-08-14.
5. PSLV-C28 DMC3 Mission Brochure (PDF). ISRO. Retrieved 2015-08-14.
6. GSLV-D5 GSAT-14 Mission Brochure (PDF). ISRO. Retrieved 2015-08-14.
7. "GSLV". ISRO. Retrieved 2015-08-14.
8. "LVM3". ISRO. Retrieved 2015-08-14.
9. "ISRO Unified Launch Vehicle Update". Antariksh Space. 2013-05-03. Retrieved 2016-05-25.
10. 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.".

External links

• ULV Description
• ULV development discussion