Proton rocket
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| Proton 8K82K | ||
|---|---|---|
| ||
| Stages | 4 | |
| 1 - Boosters | Engines | 6 × RD-253-11D48 |
| Thrust | 1,745 kN × 6 = 10,470 kN | |
| Burn time | 124 seconds | |
| Fuels | N2O4/UDMH | |
| 2 - Core Stage | Engines | 4 × RD-0210 |
| Thrust | 600 kN × 4 = 2,400 kN | |
| Burn time | 206 seconds | |
| Fuels | N2O4/UDMH | |
| 3 - 3rd Stage | Engine | 1 × RD-0212 |
| Thrust | 630.2 kN | |
| Burn time | 238 seconds | |
| Fuels | N2O4/UDMH | |
| 4 - Blok D Stage | Engine | 1 × 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 GTO | 6,000 kg | |
| Payload Escape Velocity | 5,800 kg | |
Proton initially started life as a "super ICBM." It was designed to throw a 10-Megaton (or larger) nuclear warhead over a distance of 12,000 km. It was hugely oversized for an ICBM and was never used in such a capacity. It was eventually utilized as a space 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 system 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, avoiding 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 the 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 has continued to be 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 the Zarya and Zvezda modules of the ISS. It also launched many probes to the Moon, Mars, and Venus (using the 4-stage D-1e version).
Proton also launches commercial satellites, most of them being managed by International Launch Services.
On March 1 2006, the Proton-M rocket failed to launch ArabSat4. Following successful first, second, and third stage burns, its upper stage shut down early and failed to place ArabSat4 into its proper geostationary orbit. It is currently undergoing failure review.
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 M
The latest version is the Proton M. A Proton M can launch 3 to 3.2 metric tons (6600 to 7050 lbm) into geostationary orbit or 5.5 metric tons (12,100 lbm) into a geostationary transfer orbit. It can place up to 22 metric tons (48,500 lbm) in low Earth orbit with a 51.6-degree inclination, the orbit of the International Space Station (ISS).
The Proton M's improvements include modifications to the lower stages to reduce structural mass, increase thrust, and fully utilize propellants (reducing release of toxic chemicals in stage impact areas). A Briz M storable propellant upper stage replaces the Block D stage.
- 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 9,469.1 kN
- Total Mass: 712,800 kg
- Core Diameter: 7.40 m. Total Length: 53.00 m.
Proton stages
| Stage | Gross Mass | Empty Mass | Thrust (vac) | Isp | Burn time | Isp(sl) | Diameter | Span | Length | Propellants | Engines | Status |
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| Proton KM-1 | 450,400 kg | 31,000 kg | 1,074,000 kgf | 317 s | 108 s | 285 s | 7.40 m | 7.40 m | 21.00 m | N2O4/UDMH | 6 x RD-253-14D14 | In production |
| Proton K-2 8S811K | 167,828 kg | 11,715 kg | 244,652 kgf | 327 s | 206 s | 230 s | 4.15 m | 4.15 m | 14.00 m | N2O4/UDMH | 4 x RD-0210 | In production |
| Proton K-3 | 50,747 kg | 4,185 kg | 64,260 kgf | 325 s | 238 s | 230 s | 4.15 m | 4.15 m | 6.50 m | N2O4/UDMH | 1 x RD-0212 | In production |
| Proton KM-4 Briz M | 22,170 kg | 2,370 kg | 2,000 kgf | 326 s | 3,000 s | 2.50 m | 4.10 m | 2.61 m | N2O4/UDMH | 1 x S5.98M | In production |
External links
- [Proton rocket specifications sheet]
- [Proton M Debuts With Successful Ekran Launch on April 7, 2001]
- [Proton 8K82K / Briz-M (www.astronautix.com)]
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