Vehicle Overview
Note: Payload
performance and estimated cost provided for information only. If you are interested
in contracting for launch services, we recommend that you contact the service provider
directly using the information above.
|
LEO
28.6° (150 x 175 km) |
LEO
90°
(185 km) |
GSO
Payload
(0° inclination) |
Estimated Launch Price |
Titan IV 405 NUS |
47,800 lbm
21,680 kg |
--- |
--- |
US
$350 - 450 M |
Titan I V 403 NUS |
--- |
38,300 lbm
17,600 kg |
--- |
US
$350 - 450 M |
Titan I V 401
Centaur |
--- |
--- |
12,700 lbm
5,760 kg |
US
$350 - 450 M |
Titan I V 402 IUS |
--- |
--- |
5,250 lbm
2,380 kg |
US
$350 - 450 M |
* Performance values
from AIAA, "International Reference Guide to Space Launch
Systems", 3rd edition. (NUS is no upper stage)
Vehicle Configuration
|
SRMU |
Stage 1 |
Stage
2 |
Length |
112.4 ft
34.3 m |
86.5 ft
26.4 m |
32.7 ft
10.0 m |
Diameter |
10.5 ft
3.2 m |
10.0 ft
3.05 m |
10.0 ft
3.05 m |
Gross Mass |
769,000 lbm
350,000 kg |
359,000 lbm
163,000 kg |
87,000 lbm
39,500 kg |
Propellant
Propellant Mass |
88%
HTPB
688,000 lbm
313,000 kg |
N2O4/Aerozine-50
340,000 lbm
155,000 kg |
N2O4/Aerozine-50
77,200 lbm
35,000 kg |
Engine**
Thrust
Isp |
SRMU
1,700,000 lbf
7,500 kN
285.6 sec |
LR87-AJ-11
551,200 lbf
2,452 kN
302 sec |
LR91-AJ-11
106,150 lbf
472,200 kN
316 sec |
Number of Engines |
2 |
2 |
1 |
Nominal Burn Time |
137.8 sec |
164 sec |
223 sec |
|
Centaur |
IUS Stage
1 |
IUS Stage
2 |
Length |
29.5 ft
9.0 m |
11.5 ft
3.5 m |
6.9 ft
2.1 m |
Diameter |
14 ft
4.3 m |
7.7 ft
2.34 m |
9.5 ft
2.9 m |
Gross Mass |
52,650 lbm
23,880 kg |
24,040 lbm
10,900 kg |
8,520 lbm
3,865 kg |
Propellant
Propellant Mass |
LOX /
LH2
46,185 lbm
20,950 kg |
HTPB
21,580 lbm
9,790 kg |
HTPB
6,060 lbm
2,750 kg |
Engine**
Thrust
Isp |
RL10A-3-3A
16,500 lbf
73,000 N
444 sec |
SRM-1,
Orbus 21
41,800 lbf
186,000 N
294 sec |
SRM-2, Orbus 6E
17,200 lbf
76,500 N
EEC: 303.8 sec
w/o EEC: 289.6 sec |
Number of Engines |
2 |
1 (1
segment) |
1 (1
segment) |
Nominal Burn Time |
600 sec |
153 sec |
104 sec |
|