Lockheed Martin Astronautics / USAF |
Titan IVA (34D7) | Titan IVA (IUS) | Titan IVA (Centaur) | |||||
Overall |
Operational | from | 08.06.1990 | 14.06.1989 | 07.02.1994 | |||
|
to | 23.10.1997 | 22.12.1994 | 12.08.1998 | ||||
Orbital flights | 10 | 3 | 9 | |||||
Payload weight | t | LEO | 17.70 | GEO | 2.38 | GEO | 4.54 | |
Gross liftoff weight | t | |||||||
Gross propellant weight | t | 723.91 | 735.80 | 744.78 | ||||
Total length | m | 51.36 | 53.21 | 59.30 | ||||
Max. diameter (span) | m | |||||||
Total liftoff thrust (s.l.) | kN | 14,951 | 14,951 | 14,951 | ||||
Total impulse (vac) | MN*s | 1,983.0 | 2,019.4 | 2,073.9 | ||||
Fairing |
Total length | m | 15.18/17.03 | 17.03/20.07 | 20.07/23.12/26.17 | |||
Diameter | m | 5.08 | 5.08 | 5.08 | ||||
Total weight | t | 3.6/5.0 | 5.0/5.5 | 5.5/5.9/6.3 | ||||
Stage 4 |
Name |
IUS-2 | ||||||
Length | m | 1.68 (1.90) | ||||||
Diameter | m | 2.89 (1.60) | ||||||
Liftoff weight | t | 3.865 | ||||||
Propellant weight | t | 2.735 | ||||||
Engines | ORBUS-6E | |||||||
Propellant |
solid ANB |
|||||||
Total thrust (vac) | kN | 79.2 | ||||||
Specific impulse (vac) | N*s/kg | 2979 | ||||||
Burn time | s | 103 | ||||||
Total impulse (vac) | MN*s | 8.1 | ||||||
Stage 3 |
Name |
IUS-1 | Centaur-T | |||||
Length | m | 3.50 (3.15) | 8.98 | |||||
Diameter | m | 2.34 | 4.32 | |||||
Liftoff weight | t | 11.00 | 23.880 | |||||
Propellant weight | t | 9.759 | 20.865 | |||||
Engines (Chambers) | ORBUS-21 | LR-10A-3-3A (2) | ||||||
Propellant | solid HTPB | LH2/LOX | ||||||
Total thrust (vac) | kN | 183.7 | 146.8 | |||||
Specific impulse (vac) | N*s/kg | 2898 | 4358 | |||||
Burn time | s | 154 | 619.5 | |||||
Total impulse (vac) | MN*s | 28.3 | 90.9 | |||||
Stage 2 |
Name |
|||||||
Length +adapter | m | 8.93 | 8.93 | 8.93 | ||||
Diameter | m | 3.05 | 3.05 | 3.05 | ||||
Liftoff weight | t | 39.54 | 39.54 | 39.54 | ||||
Propellant weight | t | 34.74 | 34.74 | 34.74 | ||||
Engines | LR-91-AJ-11A | LR-91-AJ-11A | LR-91-AJ-11A | |||||
Propellant | Aerozine50/N2O4 | Aerozine50/N2O4 | Aerozine50/N2O4 | |||||
Total thrust (vac) | kN | 467.1 | 467.1 | 467.1 | ||||
Specific impulse (vac) | N*s/kg | 3094 | 3094 | 3094 | ||||
Burn time | s | 230 | 230 | 230 | ||||
Total impulse (vac) | MN*s | 107.5 | 107.5 | 107.5 | ||||
Stage 1 |
Name | |||||||
Length +interstage | m | 26.37 | 26.37 | 26.37 | ||||
Diameter | m | 3.05 | 3.05 | 3.05 | ||||
Liftoff weight | t | 161.21 | 161.21 | 161.21 | ||||
Propellant weight | t | 152.57 | 152.57 | 152.57 | ||||
Engines | 2 | LR-87-AJ-11A | LR-87-AJ-11A | LR-87-AJ-11A | ||||
Propellant | Aerozine50/N2O4 | Aerozine50/N2O4 | Aerozine50/N2O4 | |||||
Total thrust (s.l.) | kN | 2,034.6 | 2,034.6 | 2,034.6 | ||||
Specific impulse (s.l.) | N*s/kg | 2473 | 2473 | 2473 | ||||
Burn time | s | 185.5 | 185.5 | 185.5 | ||||
Total impulse (vac) | MN*s | 454.7 | 454.7 | 454.7 | ||||
Booster |
Name | 2 SRM | 2 SRM | 2 SRM | ||||
Length | m | 34.14 | 34.14 | 34.14 | ||||
Diameter | m | 3.11 | 3.11 | 3.11 | ||||
Liftoff weight | t | 623.25 | 623.25 | 623.25 | ||||
Propellant weight | t | 536.60 | 536.60 | 536.60 | ||||
Engines | UTC UA-1207 | UTC UA-1207 | UTC UA-1207 | |||||
Propellant | HTPB | HTPB | HTPB | |||||
Total thrust (s.l.) | kN | 12,916.4 (max) | 12,916.4 (max) | 12,916.4 (max) | ||||
Specific impulse (s.l.) | N*s/kg | 2403 | 2403 | 2403 | ||||
Burn time | s | 128.9 | 128.9 | 128.9 | ||||
Total impulse (vac) | MN*s | 1,420.8 | 1,420.8 | 1,420.8 |