Encyclopedia Astronautica

Nuclear/Ammonia+Alcohol propellant rocket stage. Loaded/empty mass 96,000/8,800 kg. Thrust 1,660.00 kN. Vacuum specific impulse 470 seconds. Nuclear-propelled ICBM with engines in development by Bondayuk. Four expansion nozzles fed by single reactor. Payload 4,000 kg to 14,000 km. Empty mass, vehicle length calculated.

Status: Development ended 1960.
Gross mass: 96,000 kg (211,000 lb).
Unfuelled mass: 8,800 kg (19,400 lb).
Height: 23.00 m (75.00 ft).
Diameter: 3.33 m (10.92 ft).
Span: 3.33 m (10.92 ft).
Thrust: 1,660.00 kN (373,180 lbf).
Specific impulse: 470 s.
Specific impulse sea level: 430 s.
Burn time: 235 s.

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Associated Countries
Associated Engines
  • YaRD OKB-670 Bondaryuk nuclear/ammonia+alcohol rocket engine. 1667 kN. Development ended 1960. Isp=470s. Proposed for YaRD nuclear-powered ICBM. Propellant was heated in the reactor and exhausted through four expansion nozzles. More...

Associated Launch Vehicles
  • OKB-670 Russian intercontinental range ballistic missile. Variant using a Bondaryuk nuclear engine heating mixed alcohol and ammonia as a propellant. More...

Associated Propellants
  • Nuclear/Ammonia+Alcohol Nuclear thermal engines use the heat of a nuclear reactor to heat a propellant. Although early Russian designs used ammonia or an ammonia/alcohol mixture as propellant, the ideal working fluid for space applications is the liquid form of the lightest element, hydrogen. Although successfully ground-tested in both Russia, they have never been flown due primarily to environmental and safety concerns. More...

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