Proton (rocket family)
| Proton 8K82K | ||
|---|---|---|
 | ||
| Stages | 4 | |
| 1 - Boosters | Engines | 6 X RD-253-11D48 |
| Thrust | 1,745 kN X 6 = 10,470 kN | |
| Burn time | 124 seconds | |
| Fuels | N2O4/UDMH | |
| 2 - Core Stage | Engines | 4 X RD-0210 |
| Thrust | 600 kN X 4 = 2,400 kN | |
| Burn time | 206 seconds | |
| Fuels | N2O4/UDMH | |
| 3 - 3rd Stage | Engine | 1 X RD-0212 |
| Thrust | 630.2 kN | |
| Burn time | 238 seconds | |
| Fuels | N2O4/UDMH | |
| 4 - Blok D Stage | Engine | 1 X RD-58M |
| Thrust | 85.02 kN | |
| Burn time | 610 seconds | |
| Fuels | Lox/Kerosene | |
| Launch Vehicle | 1st Launch March 10, 1967 | |
| Payload LEO 51-deg | 20,000 kg | |
| Payload Geo-sync orbit | 6,000 kg | |
| Payload Escape Velocity | 5,800 kg | |
The Proton rocket (formal designation: UR-500, also known as D-1) is a Russian unmanned space vehicle design first launched in 1965 and still in use as of 2005.
Proton initially started life as a "super ICBM." It was designed to throw a 10-MT (or larger) nuclear warhead over a distance of 12,000 km. It was, of course, hugely oversized for an ICBM and was never used in such a capacity. Its real purpose was as a launch vehicle. It was the brainchild of Vladimir Chelomei's design bureau as a foil to Sergei Korolev's N1 booster with the specific intent of sending a two man Zond craft around the moon. With the termination of the Saturn V programme Proton became the largest Expendable Launch Vehicle in service until the Energia rocket first flew in 1987.
Proton is fuelled by unsymmetrical dimethyl hydrazine and nitrogen tetroxide. These are hypergolic fuels which burn on contact, voiding the need for an ignition system. They are stored at ambient temperatures avoiding the need for low-temperature-tolerant components and also allowing the rocket to sit on the pad indefinitely without need for continuous topping up of boiling off cryogenic fuels. They are, however, very toxic fuels that require special handling care.
Between the first flight in 1965 and 1970, the Proton was a very unreliable launcher causing the loss of many space vehicles. By the early 1970s the flaws were worked out and it became a very reliable rocket which it remains to this day.
Proton launched the unmanned Soviet circumlunar flights and would very likely have launched the first humans to circle the Moon had the flight of Apollo 8 been conducted as originally planned (i.e. without going to Moon orbit). Proton launched the Salyut space stations, Mir core segment, and both Zarya and Zvezda of the ISS. It also launched many probes to the Moon, Mars, and Venus (using the 4-stage D-1e version).
Proton also launched commercial satellites, most of them being managed by the International Launch Services.
Launch capacity to low Earth orbit is about 20 metric tons. Interplanetary transfer capacity is about 5–6 metric tons.
Proton 8K82K Specifications
- Stage Number: 1. Proton K-1
- Gross Mass: 450,510 kg
- Empty Mass: 31,100 kg
- Thrust (vac): 10,470 kN
- Isp: 316 s (3.10 kN·s/kg)
- Burn time: 124 s
- Isp(sl): 267 s (2.62 kN·s/kg)
- Diameter: 4.15 m
- Span: 7.40 m
- Length: 21.20 m
- Propellants: N2O4/UDMH
- Engines: 6 x RD-253-11D48
- Other designations: 8S810K
- Stage Number: 2. Proton K-2
- Gross Mass: 167,828 kg
- Empty Mass: 11,715 kg
- Thrust (vac): 2,399 kN
- Isp: 327 s (3.21 kN·s/kg)
- Burn time: 206 s
- Isp(sl): 230 s (2.26 kN·s/kg)
- Diameter: 4.15 m
- Length: 14.00 m
- Propellants: N2O4/UDMH
- Engines: 4 RD-0210
- Other designations: 8S811K.
- Stage Number: 3. Proton K-3
- Gross Mass: 50,747 kg
- Empty Mass: 4,185 kg
- Thrust (vac): 630 kN
- Isp: 325 s (3.19 kN·s/kg)
- Burn time: 238 s
- Diameter: 4.15 m
- Length: 6.50 m
- Propellants: N2O4/UDMH
- Engines: 1. RD-0212
- Stage Number: 4
- Proton 11S824
- Gross Mass: 13,360 kg
- Empty Mass: 1,800 kg
- Thrust (vac): 83 kN
- Isp: 346 s (3.39 kN·s/kg)
- Burn time: 470 s
- Diameter: 3.70 m
- Length: 5.50 m
- Propellants: Lox/Kerosene
- Engines: 1. RD-58
- Other designations: 11S824; Block D; D-1-e.
Proton 8K82K / Briz-M
Latest version is the Proton-M. A Proton M can launch 3 to 3.2 metric tons (6612 to 7053 lbm) into geostationary orbit or 5.5 metric tons (12,122 lbm) into a geostationary transfer orbit. It can place up to 22 metric tons (48,488 lbm) in low Earth orbit with a 51.6-degree inclination, the orbit of the International Space Station (ISS).
- Orbital launch vehicle.
- Family: UR.
- Country: Russia.
- Status: Hardware.
- Other Designations: Proton KM.
- Article Number: 8K82KM.
- Manufacturer's Designation: UR-500KM.
Improved Proton. Improvements in lower stages to reduce structural mass, increase thrust, and fully utilize propellants (reducing release of toxic chemicals in stage impact areas). Briz M storable propellant upper stage replaces Block D cyrogenic stage.
Narrative: 4 stage vehicle consisting of 1 x 8S810 + 1 x 8S811 + 1 x 8S812 + 1 x Briz-M.
Manufacturer: Chelomei. Launches: 4. Failures: 1. Success Rate: 75.00% pct. First Launch Date: 5 July 1999. Last Launch Date: 10 December 2003. Launch data is: continuing. LEO Payload: 21,000 kg. to: 185 km Orbit. at: 51.6 degrees. Payload: 2,920 kg. to a: geosynchronous orbital trajectory. Apogee: 40,000 km. Associated Spacecraft: Gorizont, Raduga, Spacebus 3000. Liftoff Thrust: 965,580 kgf. Liftoff Thrust: 9,469.10 kN. Total Mass: 712,800 kg. Core Diameter: 7.40 m. Total Length: 53.00 m.
Stage Data - Proton 8K82K / Briz-M
- Stage Number: 1.
- 1 x Proton KM-1
- Gross Mass: 450,400 kg.
- Empty Mass: 31,000 kg.
- Thrust (vac): 1,074,000 kgf.
- Isp: 317 sec.
- Burn time: 108 sec.
- Isp(sl): 285 sec.
- Diameter: 7.40 m.
- Span: 7.40 m.
- Length: 21.00 m.
- Propellants: N2O4/UDMH
- No Engines: 6. RD-253-14D14
- Status: In Production.
- Stage Number: 2.
- 1 x Proton K-2
- Gross Mass: 167,828 kg.
- Empty Mass: 11,715 kg.
- Thrust (vac): 244,652 kgf.
- Isp: 327 sec.
- Burn time: 206 sec.
- Isp(sl): 230 sec.
- Diameter: 4.15 m.
- Span: 4.15 m.
- Length: 14.00 m.
- Propellants: N2O4/UDMH
- No Engines: 4. RD-0210
- Other designations: 8S811K.
- Status: In Production.
- Stage Number: 3.
- 1 x Proton K-3
- Gross Mass: 50,747 kg.
- Empty Mass: 4,185 kg.
- Thrust (vac): 64,260 kgf.
- Isp: 325 sec.
- Burn time: 238 sec.
- Isp(sl): 230 sec.
- Diameter: 4.15 m.
- Span: 4.15 m.
- Length: 6.50 m.
- Propellants: N2O4/UDMH
- No Engines: 1. RD-0212
- Status: In Production.
- Stage Number: 4.
- 1 x Proton KM-4 Briz M
- Gross Mass: 22,170 kg.
- Empty Mass: 2,370 kg.
- Thrust (vac): 2,000 kgf.
- Isp: 326 sec.
- Burn time: 3,000 sec.
- Diameter: 2.50 m.
- Span: 4.10 m.
- Length: 2.61 m.
- Propellants: N2O4/UDMH
- No Engines: 1. S5.98M
- Other designations: Briz M.
- Status: In Production.
New upper stage for Proton, replacing Energia Corporation's Block DM, making Proton an all-Khrunichev launch vehicle. The Khrunichev-built Briz-M upper stage is a derivative of the flight-proven Briz -K stage (as used on the Rokot booster). The Briz-M consists of a central cylinder and a jettisonable external propellant tank. Propellant carried is dependent on the specific mission requirements and is varied to maximize performance for the mission. The Briz-M is capable of operating, on-orbit, for a minimum of 24-hours and is controlled by a closed loop, triple redundant guidance system that is commandable in flight.
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