| Indian Space Research Organisation | LVM3-X | LVM3 (D1) | LVM3 (D2/M) | LVM3 (M+) | ||||||
|
Overall |
Operational | from | 18.12.2014 | 05.06.2017 | 14.11.2018 | 2023 ? | ||||
| to | 14.07.2023 | |||||||||
| Orbital flights | - | 1 | 5 | 0 | ||||||
| Payload weight | t | Suborbital | 3.735 | GTO | 4.00 | GTO | 4.00 | GTO | 4.50 | |
| Gross liftoff weight | t | ~626 | ~642.5 | ~643 | ~643.5 | |||||
| Gross propellant weight | t | 529.6 | 559.3 | 559.9 | 559.9 | |||||
| Total length | m | 43.43 | 43.43 | 43.43 | 43.43 | |||||
| Max. diameter (span) | m | |||||||||
| Total liftoff thrust (s.l.) | kN | 8,654 (max) | 8,654 (max) | 8,654 (max) | 8,654 (max) | |||||
| Total impulse (vac) | MN*s | 1,456.8 | 1,583.0 | 1,587.8 | 1,602.9 | |||||
|
Fairing |
Total length | m | 10.70 | 10.70 | 10.70 | 10.70 | ||||
| Diameter | m | 5.00 | 5.00 | 5.00 | 5.00 | |||||
| Total weight | t | ~3 | ~3 | ~3 | ~3 | |||||
| Stage 2 |
Name |
C-25X | C-25 | C-25 | C-25 | |||||
| Length + interstage | m | 13.545 | 13.545 | 13.545 | 13.545 | |||||
| Diameter | m | 4.00 | 4.00 | 4.00 | 4.00 | |||||
| Liftoff weight | t | 18.3 | 33 | 33.6 | 33.6 | |||||
| Propellant weight | t | 15.0 (LN2) | 28 | 28.6 | 28.6 | |||||
| Engines | CE-20 | CE-20 | CE-20 | CE-20 | ||||||
| Propellant | mass simulator | LH2/LOX | LH2/LOX | LH2/LOX | ||||||
| Total thrust (vac) | kN | 186.3 | 189.3 | 189.3 | ||||||
| Specific impulse (vac) | N*s/kg | 4334 | 4401 | 4401 | ||||||
| Burn time | s | 650 | 665 | 665 | ||||||
| Total impulse (vac) | MN*s | 121.1 | 125.9 | 125.9 | ||||||
|
Stage 1 |
Name | L-110 | L-110 | L-110 | L-110 | |||||
| Length (+ interstage) | m | 21.39 | 21.39 | 21.39 | 21.39 | |||||
| Diameter | m | 4.00 | 4.00 | 4.00 | 4.00 | |||||
| Liftoff weight | t | 125.8 | 127.5 | 127.5 | 127.5 | |||||
| Propellant weight | t | 116.1 | 117.8 | 117.8 | 117.8 | |||||
| Engines | HTVE SL (2) | HTVE SL (2) | HTVE SL (2) | HPVE-1 (2) | ||||||
| Propellant | UH25/N2O4 | UH25/N2O4 | UH25/N2O4 | UH25/N2O4 | ||||||
| Total thrust (s.l.) | kN | 1,514.2 | 1,514.2 | 1,514.2 | 1,611.2 | |||||
| Specific impulse (s.l.) | N*s/kg | 2648 | 2648 | 2648 | 2775 | |||||
| Burn time | s | 203 | 206 | 206 | 203 | |||||
| Total impulse (vac) | MN*s | 343.8 | 348.9 | 348.9 | 364.0 | |||||
|
Booster |
Name | 2 (S-200) | 2 (S-200) | 2 (S-200) | 2 (S-200) | |||||
| Length | m | 26.20 | 26.20 | 26.20 | 26.20 | |||||
| Diameter | m | 3.20 | 3.20 | 3.20 | 3.20 | |||||
| Liftoff weight | t | 475 | 475 | 475 | 475 | |||||
| Propellant weight | t | 413.48 | 413.48 | 413.48 | 413.48 | |||||
| Engines |
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|
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| Propellant |
solid HTPB |
solid HTPB |
solid HTPB |
solid HTPB |
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| Total thrust (s.l.) | kN | 8,654 (max) | 8,654 (max) | 8,654 (max) | 8,654 (max) | |||||
| Specific impulse (s.l.) | N*s/kg | 2226 | 2226 | 2226 | 2226 | |||||
| Burn time | s | 128.6 | 128.6 | 128.6 | 128.6 | |||||
| Total impulse (vac) | MN*s | 1,113 | 1,113 | 1,113 | 1,113 | |||||