General Dynamics Space Systems Div. |
Atlas B | Atlas D Able II | Atlas D/OV | Atlas D/Mercury | ||||||
Overall |
Operational | from | 18.12.1958 | 24.09.1959 | 21.01.1965 | 29.07.1960 | ||||
to | 15.12.1960 | 27.07.1967 | 15.05.1963 | |||||||
Orbital flights | 1 | 3 | 7 | 8 | ||||||
Payload weight | t | Score | 0.068 | IPT | 0.180 | LEO | 1.40 | LEO | 1.40 | |
Gross liftoff weight | t | 105.50 | 120.40 | 117.10 | 117.10 | |||||
Gross propellant weight | t | 98.00 | 112.48 | 110.30 | 110.30 | |||||
Total length | m | 24.91 | 30.89 | ? | 28.29 (29.08) | |||||
Max. diameter (span) | m | 4.88 | 4.88 | 4.88 | 4.88 | |||||
Total liftoff thrust (s.l.) | kN | 1,571 | 1,596 | 1,596 | 1,596 | |||||
Total impulse (vac) | MN*s | 278.1 | 320.0 | 315.2 | 315.2 | |||||
Fairing |
Total length | m | 4.39 | 3.21 | 5.28 | 8.55 (9.34) | ||||
Diameter | m | 1.78 | 1.37 | 1.78 | 1.83 | |||||
Total weight | t | ? | 0.15 | - | - | |||||
Stage 3 |
Name |
Altair IA | ||||||||
Length | m | 1.83 (1.53) | ||||||||
Diameter | m | 0.84 (0.48) | ||||||||
Liftoff weight | t | 0.238 | ||||||||
Propellant weight | t | 0.207 | ||||||||
Engines | ABL X-248 | |||||||||
Propellant | solid | |||||||||
Total thrust (vac) | kN | 12.3 | ||||||||
Specific impulse (vac) | N*s/kg | 2496 | ||||||||
Burn time | s | 42 | ||||||||
Total impulse (vac) | MN*s | 0.52 | ||||||||
Stage 2 |
Name |
Able II | ||||||||
Length | m | 6.55 | ||||||||
Diameter | m | 0.84 | ||||||||
Liftoff weight | t | 2.110 | ||||||||
Propellant weight | t | 1.575 | ||||||||
Engines | AJ-10-101A | |||||||||
Propellant | UDMH/WFNA | |||||||||
Total thrust (vac) | kN | 33.4 | ||||||||
Specific impulse (vac) | N*s/kg | 2648 | ||||||||
Burn time | s | 125 | ||||||||
Total impulse (vac) | MN*s | 4.17 | ||||||||
Stage 1 |
Name | Atlas B | Atlas D | Atlas D | LV-3 | |||||
Length | m | 20.52 | 21.13 (20.52) | 20.52 | 20.52 | |||||
Diameter | m | 3.05 | 3.05 | 3.05 | 3.05 | |||||
Liftoff weight | t | 105.00 | 117.95 | 117.55 | 115.70 | |||||
Propellant weight | t | 98.00 | 110.70 | 110.30 | 110.30 | |||||
Engines | LR-105-NA-3 | LR-105-NA-5 | LR-105-NA-5 | LR-105-NA-5 | ||||||
Propellant | Kerosene/LOX | Kerosene/LOX | Kerosene/LOX | Kerosene/LOX | ||||||
Total thrust (s.l.) | kN | 245 + 9 | 253 + 9 | 253 + 9 | 253 + 9 | |||||
Specific impulse (s.l.) | N*s/kg | 2108 | 2108 | 2108 | 2108 | |||||
Burn time | s | 245 | 295 | 310 | 310 | |||||
Total impulse (vac) | MN*s | 88.4 | 110.6 | 116.9 | 116.9 | |||||
Stage 0 |
Name | Rock. MA-1 | Rock. MA-2 | Rock. MA-2 | Rock. MA-2 | |||||
Length | m | 4.50 | 4.50 | 4.50 | 4.50 | |||||
Diameter | m | 4.88 | 4.88 | 4.88 | 4.88 | |||||
Liftoff weight | t | - | - | - | - | |||||
Propellant weight | t | - | - | - | - | |||||
Engines | 2 | LR-89-NA-3 | LR-89-NA-5 | LR-89-NA-5 | LR-89-NA-5 | |||||
Propellant | Kerosene/LOX | Kerosene/LOX | Kerosene/LOX | Kerosene/LOX | ||||||
Total thrust (s.l.) | kN | 1,317 | 1,334 | 1,334 | 1,334 | |||||
Specific impulse (s.l.) | N*s/kg | 2432 | 2432 | 2432 | 2432 | |||||
Burn time | s | 127 | 135 | 131 | 131 | |||||
Total impulse (vac) | MN*s | 189.7 | 205.2 | 198.3 | 198.3 |