|
Lockheed Martin Astronautics |
SLV-3D Centaur | Atlas-G Centaur | Atlas I | |||||
|
Overall |
Operational | from | 26.09.1975 | 09.06.1984 | 27.07.1990 | |||
|
|
to | 19.05.1983 | 25.09.1989 | 24.04.1997 | ||||
| Orbital flights | 26 | 7 | 11 | |||||
| Payload weight | t | GTO | 1.81 | GTO | 2.34 | GTO | 2.25 | |
| Gross liftoff weight | t | 149.42 | 163.55 | 164.29 | ||||
| Gross propellant weight | t | 138.29 | 151.32 | 151.32 | ||||
| Total length | m | 39.75 | 41.80 | 42.82 | ||||
| Max. diameter (span) | m | 4.88 | 4.88 | 4.88 | ||||
| Total liftoff thrust (s.l.) | kN | 1,957 | 1,957 | 1,957 | ||||
| Total impulse (vac) | MN*s | 424.5 | 462.4 | 462.4 | ||||
|
Fairing |
Total length | m | 8.44/9.36 | 9.36 | 10.38/12.01 | |||
| Diameter | m | 3.05 | 3.05 | 3.30/4.20 | ||||
| Total weight | t | 1.25 | 1.25 | 1.410/2.085 | ||||
| Stage 2 |
Name |
Centaur D-1AR | Centaur D-1AR | Centaur D-1B | ||||
| Length | m | 9.14 | 9.14 | 9.14 | ||||
| Diameter | m | 3.05 | 3.05 | 3.05 | ||||
| Liftoff weight | t | 16.76 | 16.76 | 16.76 | ||||
| Propellant weight | t | 13.79 | 13.79 | 13.79 | ||||
| Engines (Chambers) | RL-10A-3-3A (2) | RL-10A-3-3A (2) | RL-10A-3-3A (2) | |||||
| Propellant | LH2/LOX | LH2/LOX | LH2/LOX | |||||
| Total thrust (vac) | kN | 146.8 | 146.8 | 146.8 | ||||
| Specific impulse (vac) | N*s/kg | 4358 | 4358 | 4378 | ||||
| Burn time | s | 409.5 | 409.5 | 409.5 | ||||
| Total impulse (vac) | MN*s | 60.1 | 60.1 | 60.1 | ||||
|
Stage 1 |
Name | SLV-3D | Atlas G | Atlas I | ||||
| Length | m | 21.25 | 23.30 | 23.30 | ||||
| Diameter | m | 3.05 | 3.05 | 3.05 | ||||
| Liftoff weight | t | 129.60 | 143.20 | 143.20 | ||||
| Propellant weight | t | 124.50 | 137.53 | 137.53 | ||||
| Engines | LR-105-NA-7 | LR-105-NA-7 | LR-105-NA-7 | |||||
| Propellant | Kerosene/LOX | Kerosene/LOX | Kerosene/LOX | |||||
| Total thrust (s.l.) | kN | 268.7 + 8.9 | 268.7 + 8.9 | 268.7 + 8.9 | ||||
| Specific impulse (s.l.) | N*s/kg | 2161 | 2161 | 2161 | ||||
| Burn time | s | 241 (240) | 256.1 (255) | 256.1 (255) | ||||
| Total impulse (vac) | MN*s | 95.7 | 101.6 | 101.6 | ||||
|
Stage 0 |
Name | Rock. MA-5 | Rock. MA-5 | Rock. MA-5 | ||||
| Length | m | 4.50 | 4.50 | 4.50 | ||||
| Diameter | m | 4.88 | 4.88 | 4.88 | ||||
| Liftoff weight | t | - | - | - | ||||
| Propellant weight | t | - | - | - | ||||
| Engines | 2 | LR-89-NA-7 | LR-89-NA-7 | LR-89-NA-7 | ||||
| Propellant | Kerosene/LOX | Kerosene/ LOX | Kerosene/LOX | |||||
| Total thrust (s.l.) | kN | 1,679 | 1,679 | 1,679 | ||||
| Specific impulse (s.l.) | N*s/kg | 2541 | 2541 | 2541 | ||||
| Burn time | s | 141 | 158 | 158 | ||||
| Total impulse (vac) | MN*s | 268.7 | 300.7 | 300.7 | ||||