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*
(51° inclination, 200 km) |
LEO Payload*
(65° inclination, 200 km) |
LEO Payload*
(66° inclination, 200 km) |
Mir/ISS
Payload*
(51.6° inclination, 407 km) |
SSO Payload*
(98.6° inclination, 800 km) |
Estimated Launch Price |
| Tsiklon 2 |
7,370
lbm
3,350 kg |
6,220 lbm
2,820 kg |
--- |
--- |
--- |
US
$20 - 25 M |
| Tsiklon 2 + AKS |
--- |
--- |
--- |
6,280 lbm
2,850 kg |
4,630 lbm
2,100 kg |
US
$20 - 25 M |
| Tsiklon 3 |
--- |
--- |
9,020
lbm
4,100 kg |
--- |
--- |
US
$20 - 25 M |
* Performance values from
AIAA, "International Reference Guide to Space Launch
Systems", 3rd edition.
Vehicle Configuration
| |
Stage 1 |
Stage
2 |
C5M (Stage
3 Tsiklon 3) |
AKS
(Optional Tsiklon 2) |
| Length |
61.5 ft
18.75 m |
33.1 ft
10.08 m |
9.02
ft
2.75 m |
1.0 ft
0.3 m |
| Diameter |
9.8 ft
3.0 m |
9.8 ft
3.0 m |
2.7 ft
2.2 m |
? |
| Gross Mass |
280,000 lbm
127,000 kg |
117,500 lbm
53,300 kg |
10,100 lbm
4,600 kg |
? |
Propellant
Propellant Mass |
N2O4
/ UDMH
261,700 lbm
118,700 kg |
N2O4 /
UDMH
106,900 lbm
48,500 kg |
N2O4 /
UDMH
6,600 lbm
3,000 kg |
N2O4 /
UDMH
1,540 lbm
700 kg |
Engine**
Thrust
Isp |
RD-251
681,000 lbf
3,032 kN
(sea level) 269.6 sec |
RD-252
227,000 lbf
1,010 kN
317.6 sec |
RD-86
/ 11D25
17,500 lbf
79.6 kN
317 sec |
? |
| Number of Engines |
3
(with 2 chambers each + 4 verniers) |
1
engine with 2 chambers and 1 turbine exhaust nozzle + 4
verniers |
1 |
1
main engine + 4 verniers |
| Nominal Burn Time |
120 sec |
160 sec |
125 sec |
? |
** Note: Vacuum engine performance unless
otherwise specified.
|
