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.
| |
GTO Payload*
(27 degree inclination) |
GSO Payload*
(0 degree inclination) |
Estimated Launch Price |
Configuration |
Launch Mass |
| Atlas V 401 |
11,000 lb
5,000 kg |
--- |
US $90 M |
Common Core +
Centaur (1x RL-10A-4-1) |
734,850 lb
334,045 kg |
| Atals V 501 |
9,000 lb
4,100 kg |
1,500 lb
3,300 kg |
US $85 M |
Common Core +
Centaur (1x RL-10A-4-2) |
741,165 lb
336,895 kg |
| Atals V 511 |
10,800 lb
4,900 kg |
3,900 lb
1,750 kg |
US $90 M |
Common Core + 1 SRB +
Centaur (1x RL-10A-4-2) |
831,180 lb
377,805 kg |
| Atlas V 521 |
13,200 lb
6,000 kg |
4,900 lb
2,200 kg |
US $95 M |
Common Core + 2 SRB's +
Centaur (1x RL-10A-4-2) |
921,200 lb
418,725 kg |
| Atlas V 531 |
15,200 lb
6,900 kg |
6,600 lb
3,000 kg |
US $100 M |
Common Core + 3 SRB's +
Centaur (1x RL-10A-4-2) |
1,011,220 lb
459,545 kg |
| Atlas V 541 |
16,700 lb
7,600 kg |
7,500 lb
3,400 kg |
US $105 M |
Common Core + 4 SRB's +
Centaur (1x RL-10A-4-2) |
1,101,230 lb
500,365 kg |
| Atlas V 551 |
18,080 lb
8,200 kg |
8,200 lb
3,750 kg |
US $110 M |
Common Core + 5 SRB's +
Centaur (1x RL-10A-4-2) |
1,191,250 lb
541,195 kg |
| Atlas V Heavy ++ |
30,000 lb
13,605 kg |
13,000 lb
5,900 kg |
US $130 M |
Common Core + 2 Common Core
Boosters + Centaur (1x RL-10A-4-2) |
2,120,000 lb
961,451 kg |
++ Atlas V Heavy performance
and configuration has been estimated.
| |
ETR Reference Orbit* |
WTR Reference Orbit* |
Estimated Launch Price |
Configuration |
Launch Mass |
| Atlas V 402 |
27,550 lb
12,500 kg |
23,700 lb
10,750 kg |
US $90 M |
Common Core +
Centaur (2x RL-10A-4-1) |
735,850 lb
334,500 kg |
| Atals V 502 |
22,660 lb
10,300 kg |
20,000 lb
9,050 kg |
US $85 M |
Common Core +
Centaur (2x RL-10A-4-2) |
742,165 lb
337,350 kg |
| Atals V 512 |
26,600 lb
12,050 kg |
22,500 lb
10,200 kg |
US $90 M |
Common Core + 1 SRB +
Centaur (2x RL-10A-4-2) |
832,180 lb
378,260 kg |
| Atlas V 522 |
30,800 lb
13,950 kg |
26,100 lb
11,800 kg |
US $95 M |
Common Core + 2 SRB's +
Centaur (2x RL-10A-4-2) |
922,200 lb
419,180 kg |
| Atlas V 532 |
38,000 lb
17,250 kg |
32,200 lb
14,600 kg |
US $100 M |
Common Core + 3 SRB's +
Centaur (2x RL-10A-4-2) |
1,012,220 lb
460,000 kg |
| Atlas V 542 |
41,300 lb
18,750 kg |
35,000 lb
15,800 kg |
US $105 M |
Common Core + 4 SRB's +
Centaur (2x RL-10A-4-2) |
1,102,230 lb
500,820 kg |
| Atlas V 552 |
44,200 lb
20,050 kg |
37,400 lb
17,000 kg |
US $110 M |
Common Core + 5 SRB's +
Centaur (2x RL-10A-4-2) |
1,192,250 lb
541,650 kg |
* Performance values
from ILS Atlas V Payload User's Guide
Vehicle Configuration
| |
Solid Strap-Ons |
Stage 1
(Common Core) |
Stage 2
(Centaur) |
Stage 2
(Stretched Centaur) |
| Length |
39 ft
17.7 m |
106.2 ft
32.4 m |
33.5 ft
10.2 m |
38.5 ft
11.7 m |
| Diameter |
3.4 ft
1.55 m |
12.5 ft
3.8 m |
10 ft
3.0 m |
10 ft
3.0 m |
| Gross Mass |
90,000 lb
40,824 kg |
683,650 lb
310,045 kg |
41,800 lb
18,960 kg |
51,200 lb
23,220 kg |
Propellant
Propellant Mass |
HTPB
85,300 lb
38,770 kg |
LOX / RP
627,000 lb
284,350 kg |
LOX / LH2
37,000 lb
16,780 kg |
LOX / LH2
45,000 lb
20,410 kg |
Engine**
Thrust
Isp |
Atlas 5 SRB
255,405 lbf SL
1,134 kN SL
275 sec SL |
RD-180
860,400 lbf SL
3,820 kN SL
311 sec SL |
RL-10A-4-1
22,300 lbf
99,000 N
451 sec |
RL-10A-4-2
22,300 lbf
99,000 N
451 sec |
| Number of Engines |
0 - 5 |
1 |
1 |
2 |
| Nominal Burn Time |
94 sec |
236 sec |
894 sec |
429 sec |
** Note: Vacuum engine
performance unless otherwise specified.
|
