N.A.S.A. | Space Shuttle SSME Baseline |
Space Shuttle SSME Phase-1 |
Space Shuttle SSME Phase-2 |
Space Shuttle SSME Phase-2 |
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Overall Vehicle |
Operational | from | 12.04.1981 | 04.04.1983 | 29.09.1988 | |||||
to | 11.11.1982 | 28.01.1986 | 23.07.1999 | |||||||
Orbital flights | 5 | 20 | 57 | |||||||
Payload weight | t | STS-5 | 14.555 | STS-25 | 23.733 | STS-26 | 21.088 | STS- 30 | 20.344 | |
Gross liftoff weight | t | ~2,046 | ~2,055 | ~2,048 | ~2,051 | |||||
Gross propellant weight | t | < 1,743.71 | < 1,748.85 | < 1,749.32 | < 1,749.32 | |||||
Total length | m | 56.14 | 56.14 | 56.14 | 56.14 | |||||
Max. diameter (span) | m | 23.79 | 23.79 | 23.79 | 23.79 | |||||
Total liftoff thrust (s.l.) | kN | 29,738 | 29,738 | 31,827 | 31,827 | |||||
Total impulse (vac) | MN*s | < 5,817.7 | < 5,840.7 | < 5,932.2 | < 5,932.2 | |||||
Bay |
Total length | m | 18.29 | 18.29 | 18.29 | 18.29 | ||||
Diameter | m | 4.57 | 4.57 | 4.57 | 4.57 | |||||
Total weight | t | - | - | - | - | |||||
Orbiter |
Name | Columbia | Challenger | Discovery | Atlantis | |||||
Length | m | 37.24 | 37.24 | 37.24 | 37.24 | |||||
Diameter | m | |||||||||
Liftoff weight (excl. payload) | t | 97.536 | 98.209 | 94.407 | 97.610 | |||||
Propellant weight | t | < 21.650 | < 21.650 | < 21.650 | < 21.650 | |||||
Engines | 2 OMS | AJ-10-190 | AJ-10-190 | AJ-10-190 | AJ-10-190 | |||||
Propellant |
MMH/N2O4 |
MMH/N2O4 |
MMH/N2O4 |
MMH/N2O4 |
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Total thrust (vac) | kN | 53.4 | 53.4 | 53.4 | 53.4 | |||||
Specific impulse (vac) | N*s/kg | 2886 | 2886 | 2886 | 2886 | |||||
Burn time | s | < 1,170 | < 1,170 | < 1,170 | < 1,170 | |||||
Total impulse (vac) | MN*s | < 62.5 | < 62.5 | < 62.5 | < 62.5 | |||||
Stage 1 |
Name | External Tank 1 | External Tank 2 | LWET | LWET | |||||
Length | m | 46.88 | 46.88 | 46.88 | 46.88 | |||||
Diameter | m | 8.41 | 8.41 | 8.41 | 8.41 | |||||
Liftoff weight | t | 754.53 | 756.49 | 754.58 | 754.58 | |||||
Propellant weight | t | 719.11 | 724.25 | 724.25 | 724.25 | |||||
Engines | 3 | Rock. SSME | Rock. SSME | Rock. SSME | Rock. SSME | |||||
Propellant | LH2/LOX | LH2/LOX | LH2/LOX | LH2/LOX | ||||||
Total thrust (s.l.) | kN | 5,004.0 | 5,004.0 | 5,004.0 | 5,004.0 | |||||
Specific impulse (s.l.) | N*s/kg | 3550 | 3550 | 3557 | 3557 | |||||
Burn time | s | 515 | 509.5 | 510.5 | 510.5 | |||||
Total impulse (vac) | MN*s | 3,198.0 | 3,221.0 | 3,227.4 | 3,227.4 | |||||
Booster |
Name | 2 SRM-1 | 2 SRM-2 | 2 RSRM | 2 RSRM | |||||
Length | m | 45.46 | 45.46 | 45.46 | 45.46 | |||||
Diameter | m | 3.71 | 3.71 | 3.71 | 3.71 | |||||
Liftoff weight | t | 1,179.50 | 1,176.60 | 1,178.20 | 1,178.20 | |||||
Propellant weight | t | 1,002.95 | 1,002.95 | 1,003.42 | 1,003.42 | |||||
Engines | Thiokol | Thiokol | Thiokol | Thiokol | ||||||
Propellant | solid PBAN | solid PBAN | solid PBAN | solid PBAN | ||||||
Total thrust (s.l.) | kN | 24,734 (max) | 24,734 (max) | 26,823 (max) | 26,823 (max) | |||||
Specific impulse (s.l.) | N*s/kg | 2324 | 2324 | 2375 | 2383 | |||||
Burn time | s | 123 | 123 | 122.2 | 122.2 | |||||
Total impulse (vac) | MN*s | 2,557.2 | 2,557.2 | 2,642.3 | 2,642.3 |