Proton-M
Proton-M rocket on the launchpad at Baikonur Cosmodrome | |
| Function | Heavy-lift launch vehicle |
|---|---|
| Manufacturer | Khrunichev |
| Country of origin | Russia |
| Cost per launch | US$65 million |
| Size | |
| Height | 58.2 m (191 ft) |
| Diameter | 7.4 m (24 ft) |
| Mass | 705,000 kg (1,554,000 lb) |
| Stages | 3 or 4 |
| Capacity | |
| Payload to LEO | |
| Mass | 23,000 kg (51,000 lb) |
| Payload to GTO (1800 m/s) | |
| Mass | 6,920 kg (15,260 lb) |
| Payload to GTO (1500 m/s) | |
| Mass | 6,300 kg (13,900 lb) |
| Payload to GSO | |
| Mass | 3,250 kg (7,170 lb) |
| Associated rockets | |
| Family | Universal Rocket (Proton) |
| Based on | Proton-K |
| Comparable | |
| Launch history | |
| Status | Active |
| Launch sites | Baikonur, Sites 81/24 & 200/39 |
| Total launches | 115 |
| Success(es) | 104 |
| Failure(s) | 9 |
| Partial failure(s) | 2 |
| First flight | 7 April 2001 |
| Last flight | 12 March 2023 |
| Carries passengers or cargo | GLONASS, ExoMars, Nauka |
| First stage – 8S810K | |
| Height | 21.18 m (69.5 ft) |
| Diameter | 7.4 m (24 ft) |
| Empty mass | 30,600 kg (67,500 lb) |
| Propellant mass | 428,300 kg (944,200 lb) |
| Powered by | 6 × RD-275M |
| Maximum thrust | 10,532 kN (2,368,000 lbf) |
| Specific impulse | 285 s (2.79 km/s) |
| Burn time | 108 seconds |
| Propellant | N2O4 / UDMH |
| Second stage – 8S811K | |
| Height | 17.05 m (55.9 ft) |
| Diameter | 4.1 m (13 ft) |
| Empty mass | 11,000 kg (24,000 lb) |
| Propellant mass | 157,300 kg (346,800 lb) |
| Powered by | 3 × RD-0210 1 × RD-0211 |
| Maximum thrust | 2,399 kN (539,000 lbf) |
| Specific impulse | 327 s (3.21 km/s) |
| Burn time | 206 seconds |
| Propellant | N2O4 / UDMH |
| Third stage – 8S812 | |
| Height | 4.11 m (13.5 ft) |
| Diameter | 4.1 m (13 ft) |
| Empty mass | 3,500 kg (7,700 lb) |
| Propellant mass | 46,562 kg (102,652 lb) |
| Powered by | 1 × RD-0212 |
| Maximum thrust | 613.8 kN (138,000 lbf) |
| Specific impulse | 325 s (3.19 km/s) |
| Burn time | 238 seconds |
| Propellant | N2O4 / UDMH |
| Fourth stage (optional) – Briz-M | |
| Height | 2.61 m (8 ft 7 in) |
| Diameter | 4.0 m (13.1 ft) |
| Empty mass | 2,370 kg (5,220 lb) |
| Propellant mass | 19,800 kg (43,700 lb) |
| Powered by | 1 × S5.98M |
| Maximum thrust | 19.62 kN (4,410 lbf) |
| Specific impulse | 326 s (3.20 km/s) |
| Burn time | 3,000 seconds |
| Propellant | N2O4 / UDMH |
| Fourth stage (optional) – Blok DM-2 | |
| Powered by | 1 × RD-58M |
| Maximum thrust | 85 kN (19,000 lbf) |
| Specific impulse | 352 s (3.45 km/s) |
| Propellant | RP-1 / LOX |
| Fourth stage (optional) – Blok DM-03 | |
| Powered by | 1 RD-58M/RD-58MF |
| Propellant | RP-1 / LOX |
The Proton-M, (Протон-М) GRAU index 8K82M or 8K82KM, is an expendable Russian heavy-lift launch vehicle derived from the Soviet-developed Proton. It is built by Khrunichev, and launched from sites 81/24 and 200/39 at the Baikonur Cosmodrome in Kazakhstan. Commercial launches are marketed by International Launch Services (ILS), and generally use Site 200/39. The first Proton-M launch occurred on 7 April 2001.
Proton flew its most recent mission on 12 March 2023. As of August 2020, a number of Roscosmos and other Russian government missions remain on Proton launch manifest.