Proton
Click on the list of rocket parts for more information.
Total Liftoff Mass: 691,272 kg
(1,523,565 lbm)
SC Separated Mass: 5,535 kg to reference 1,500m/s GTO
Total Length: 57.2 m (187.6 ft), with standard commercial 4.35 m diameter fairing.

Enhanced insertion orbit range allows launching heavier payloads to low orbit. Using considerable flight heritage from other Russian vehicles, the upgraded guidance & control system's digital avionics suite allows for increased optimization of ascent trajectories, and smaller drop zones. Use of advanced materials provides lower structural mass; and a 50% reduction of propellant residuals plus a residual venting system results an environmentally friendly reduction of downrange contamination.

Payload Fairing
Encloses and protects the spacecraft during ground operations and launch vehicle ascent. Offers increased payload fairing volume due to reduced height of the upper stage.
Payload
Multiple standard payload adaptors are available to meet a multitude of spacecraft mission requirements to accommodate both mass and volume.
Breeze M Upper Stage
Length: 2.61 m
Diameter: 4.0 m
Engine(s): One RD-2000
Thrust: 19.62 kN
Inert Mass: 2,370 kg
Propellant 19,800 kg
Mass:

Comprised of a central core and an additional jettisonable propellant tank and powered by one pump-fed gimballed main engine.

Features increased lift capability of 5,645 kg (12,445 lb) to geosynchronous transfer orbit with a 1,500 m/sec residual velocity to GSO. Strengthened structure allows launching heavier spacecraft with higher center of gravity locations, and even allows for launching multiple spacecraft.

3rd Stage
Length: 4.11 m
Diameter: 4.1 m
Engine(s): One RD-0213
Thrust: 608 kN
Inert Mass: 4,185 kg
Propellant 46,562 kg
Mass:
Powered by one RD-0213 main engine developing 583 kN (131,000 lbf) thrust and one RD-0214 control engine which produces 31 kN (6,900 lbf) thrust.
2nd Stage
Length: 17.05 m
Diameter: 4.1 m
Engine(s): Four RD-0210
Thrust: 2.32 MN
Inert Mass: 11,715 kg
Propellant 156,113 kg
Mass:
Utilizes conventional cylindrical design.

1st Stage

Length: 21.18 m
Diameter: 7.4 m
Engine(s): Six RD-253
Thrust: 10.0 MN
Inert Mass: 31,100 kg
Propellant 419,410 kg
Mass:
Consists of a central tank containing oxidizer surrounded by six outboard fuel tanks, each of which also carries one of the six engines.

  • Payload Fairing
  • Payload
  • Breeze M
  • 3rd Stage
  • 1st & 2nd Stage