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
Payload* (52o inclination, 200 km) |
Space
Station Payload* (51.6o inclination, 407 km) |
LEO
Payload* (90o inclination, 200 km) |
Sun
Synch. Payload* (98.6o inclination, 800 km) |
Launch
Cost* |
Launch
Mass* |
| Start -
1 |
1,393
lbm
632 kg |
1,100
lbm
500 kg |
1,393
lbm
632 kg |
368
lbm
167 kg |
US
$9 M |
100,900
lbm
46,000 kg |
| Start |
|
|
1,420
lbm
645 kg |
|
US
$10.5 M |
129,600
lbm
59,000 kg |
*
Performance from AIAA, "International Reference Guide to
Space Launch Systems", 3rd edition
Vehicle Configuration
| |
Start-1
Stage 1
(Start Stage 1) |
Start-1
Stage 2
(Start Stages 2 & 3) |
Start-1
Stage 3
(Start Stage 4) |
Start-1
Stage 4
(Start Stage 5) |
| Length |
27.9
ft
8.5 m |
19.5
ft
6 m |
10
ft
3 m |
8
ft
2.5 m |
| Diameter |
5.3
ft
1.6 m |
|
|
|
| Gross Mass |
57,000
lbm
26,000 kg |
28,700
lbm
13,000 kg |
13,000
lbm
6,000 kg |
2,200
lbm
1,000 kg |
Propellant
Propellant Mass |
Solid
51,000 lbm
23,000 kg |
Solid
25,400 lbm
11,500 kg |
Solid
11,000 lbm
5,000 kg |
Solid
1,550 lb
700 kg |
Engine**
Thrust
Isp |
220,000
lbf
980,000 N
263 sec |
110,000
lbf
490,000 N
280 sec |
55,000
lbf
245,000 N
280 sec |
23,000
lbf
100,000 N
295 sec |
| Number of Engines |
1 |
1 |
1 |
1 |
| Nominal Burn Time |
60 sec |
64 sec |
56 sec |
207 sec |
** Note: Vacuum engine
performance unless otherwise specified.
|
