| Weapons Research Establishment |
Redstone-Sparta |
||
|
Overall Vehicle |
Operational | from | 28.11.1966 |
|
|
to | 29.11.1967 | |
| Orbital flights (+ suborbital) | 1 (+ 9) | ||
| Payload weight | t | 0.073 | |
| Gross liftoff weight | t | 24.50 | |
| Gross propellant weight | t | 20.93 | |
| Total length | m | 21.77 | |
| Max. diameter (span) | m | 3.66 | |
| Total liftoff thrust (s.l.) | kN | 311.4 | |
| Total impulse (vac) | MN*s | 47.3 | |
|
Fairing |
Total length | m | 2.17 |
| Diameter | m | 0.76 | |
| Total weight | t | 0.00 | |
| Stage 3 | Name | Alcyone | |
| Length | m | 0.81 | |
| Diameter | m | 0.48 | |
| Liftoff weight | t | 0.098 | |
| Propellant weight | t | 0.087 | |
| Engines | BE-3 | ||
| Propellant | solid | ||
| Total thrust (vac) | kN | 27.5 | |
| Specific impulse (vac) | N*s/kg | 2677 | |
| Burn time | s | 8.4 | |
| Total impulse (vac) | MN*s | 0.2 | |
| Stage 2 |
Name |
Antares II | |
| Length | m | 1.70 | |
| Diameter | m | 0.76 | |
| Liftoff weight | t | 1.525 | |
| Propellant weight | t | 1.168 | |
| Engines | ABL X-259 | ||
| Propellant | solid | ||
| Total thrust (vac) | kN | 93.2 | |
| Specific impulse (vac) | N*s/kg | 2579 | |
| Burn time | s | 38 | |
| Total impulse (vac) | MN*s | 3.5 | |
|
Stage 1 |
Name | Redstone | |
| Length | m | 17.00 | |
| Diameter | m | 1.78 (1.60) | |
| Liftoff weight | t | 22.80 | |
| Propellant weight | t | 19.67 | |
| Engines | NAA75-110-A6 | ||
| Propellant | Ethyl-Alcohol/LOX | ||
| Total thrust (s.l.) | kN | 311.4 | |
| Specific impulse (s.l.) | N*s/kg | 1917 | |
| Burn time | s | 121 | |
| Total impulse (vac) | MN*s | 43.6 | |