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.
Korolev began work on 3 nuclear launchers on 30 June 1958. Competing engine design was by Glushko. Used nuclear reactor in cylindrical housings, operating at 3000 deg K.
Application: nuclear launcher.
Propellant Formulation: Nuclear/NH3+Alcohol (C2H5OH).
Status: Development ended 1960.
More... - Chronology...
Thrust: 1,667.00 kN (374,756 lbf).
Specific impulse: 470 s.
Specific impulse sea level: 430 s.
Burn time: 500 s.
First Launch: 1958-.
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 Manufacturers and Agencies
Bondaryuk Russian manufacturer of rocket engines. Bondaryuk Design Bureau, Russia. More...
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...
Semenov, Yuri P Editor, Raketno-kosmicheskaya korporatsiya 'Energia' imeni S P Koroleva, Moscow, Russia, 1996.
Semenov, Yu. P., S P Korolev Space Corporation Energia, RKK Energia, 1994.
YaRD ICBM OKB-670 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. More...
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