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 | |
| Mass | 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) HLV(Variant):20,000 kg (44,000 lb) SHLV(Variant):41,300 kg (91,100 lb) |
| Payload to GTO | |
| Mass | 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) HLV(Variant):10,000 kg (22,000 lb) SHLV(Variant):16,300 kg (35,900 lb) |
| Boosters – S-13[2][3][4] | |
| No. boosters | 6 |
| Height | 12 m (39 ft)[5] |
| Diameter | 1 m (3 ft 3 in)[5] |
| Propellant mass | 12,200 kg (26,900 lb)[5] |
| Powered by | S-13 |
| Maximum thrust | 716 kN (161,000 lbf)[5] |
| Burn time | 70 seconds[5] |
| Propellant | HTPB |
| Boosters – S-60[2][3] | |
| No. boosters | 2 |
| Propellant mass | 60,000 kg (130,000 lb) |
| Powered by | S-60 |
| Propellant | HTPB |
| Boosters – S-139[2][3] | |
| No. boosters | 2 |
| Height | 20.1 m (66 ft)[6] |
| Diameter | 2.8 m (9 ft 2 in)[6] |
| Propellant mass | 138,200 kg (304,700 lb)[6] |
| Powered by | S-139 |
| Maximum thrust | 4,700 kN (1,100,000 lbf)[7] |
| Burn time | 100 seconds[6] |
| Propellant | HTPB |
| Boosters – S-200 | |
| No. boosters | 2 |
| Height | 25 m (82 ft)[8] |
| Diameter | 3.2 m (10 ft)[8] |
| Propellant mass | 207,000 kg (456,000 lb)[8] |
| Powered by | S-200 |
| Maximum 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] |
| Propellant | HTPB[8] |
| Core stage – SC-160 | |
| Propellant mass | 160,000 kg (350,000 lb) |
| Powered by | SCE-200[3] |
| Maximum 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 |
| Propellant | Kerosene / LOX |
| Upper stage – C-30 | |
| Propellant mass | 30,000 kg (66,000 lb) |
| Powered by | CE-20[3] |
| Maximum thrust | 200 kN (45,000 lbf) |
| Specific impulse | 443 s (4.34 km/s) |
| Burn time | 650 sec |
| Propellant | 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, as well as super heavy-lift variant called SHLV with a cluster stage of five SCE-200 engines each replacing the main core stage SC-160 and as well as the two solid boosters.[1][9]
Design
As of May 2013, based on ISRO data, the design comprised a common core and upper stage, with four different booster sizes.[10] 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][9]
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][11][9]
- 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
See also
- Comparison of orbital launchers families
- Comparison of orbital launch systems
- GSLV Mk I/II
- LVM3
- ISRO Orbital Vehicle
- PSLV
References
- ^ a b c d e Brügge, Norbert. "ULV (LMV3-SC)". B14643.de. Retrieved 2015-08-14.
- ^ a b c d e f "ISRO Unified Launch Vehicle (ULV)". NASAspaceflight. 2013-05-03. Retrieved 2015-08-14.
- ^ a b c d e Brügge, Norbert. "Propulsion ULV". B14643.de. Retrieved 2015-08-14.
- ^ "PSLV". ISRO. Retrieved 2015-08-14.
- ^ a b c d e PSLV-C28 DMC3 Mission Brochure (PDF). ISRO. Retrieved 2015-08-14.
- ^ a b c d GSLV-D5 GSAT-14 Mission Brochure (PDF). ISRO. Retrieved 2015-08-14.
- ^ "GSLV". ISRO. Retrieved 2015-08-14.
- ^ a b c d e f g "LVM3". ISRO. Retrieved 2015-08-14.
- ^ a b c Brügge, Norbert. "LVM3, ULV & HLV". B14643.de. Retrieved 2015-08-14.
- ^ "ISRO Unified Launch Vehicle Update". Antariksh Space. 2013-05-03. Retrieved 2016-05-25.
- ^ ""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".
