 Start-1 launch vehicle lifting off from the Svobodny Cosmodrome | |
| Function | Small orbital launch vehicle |
|---|---|
| Manufacturer | Moscow Institute of Thermal Technology |
| Country of origin | Russia |
| Size | |
| Height | 22.7 m (74 ft) |
| Diameter | 1.8 m (5.9 ft) |
| Mass | 47,200 kg (104,100 lb) |
| Stages | 4 |
| Capacity | |
| Payload to LEO | |
| Mass | 550 kg (1,210 lb) |
| Payload to SSO | |
| Mass | 167 kg (368 lb) |
| Launch history | |
| Status | Retired |
| Launch sites | LC-5, Svobodny Cosmodrome LC-158, Plesetsk Cosmodrome |
| Total launches | 7 |
| Success(es) | 6 |
| Failure(s) | 1 |
| First flight | 25 March 1993 |
| Last flight | 25 April 2006 |
| First stage – 15Zh58A | |
| Powered by | 1 MIHT-1 |
| Maximum thrust | 980 kN (220,000 lbf) |
| Specific impulse | 263 s (2.58 km/s) |
| Burn time | 60 seconds |
| Propellant | Solid |
| Second stage – 15Zh58B | |
| Powered by | 1 MIHT-2 |
| Maximum thrust | 490 kN (110,000 lbf) |
| Specific impulse | 280 s (2.7 km/s) |
| Burn time | 64 seconds |
| Propellant | Solid |
| Third stage – 15Zh58V | |
| Powered by | 1 MIHT-3 |
| Maximum thrust | 245 kN (55,000 lbf) |
| Specific impulse | 280 s (2.7 km/s) |
| Burn time | 56 seconds |
| Propellant | Solid |
| Fourth stage – Start | |
| Powered by | 1 MIHT-4 |
| Maximum thrust | 9.8 kN (2,200 lbf) |
| Specific impulse | 295 s (2.89 km/s) |
| Burn time | 207 seconds |
| Propellant | Solid |
Start-1 is a Russian satellite launch vehicle based on the RT-2PM Topol, a Soviet intercontinental ballistic missile developed by Moscow Institute of Thermal Technology.