Encyclopedia Astronautica
YaKhR-2



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YaKhR-2 exterior
YaKhR-2 Nuclear-powered Launch Vehicle
Credit: © Mark Wade
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Yard
Russian nuclear-powered orbital launch vehicle. First large space launcher considered in the Soviet Union. It would have had the same layout as the R-7, but with six strap-ons increased in size by 50%. The core, igniting at altitude, used a nuclear thermal engine using ammonia as propellant. Dropped in favor of development of conventional chemical propulsion.

LEO Payload: 40,000 kg (88,000 lb) to a 185 km orbit.

Stage Data - YaKhR-2

  • Stage 0. 6 x YaKhR-2 Strap-on. Gross Mass: 110,000 kg (240,000 lb). Empty Mass: 8,250 kg (18,180 lb). Thrust (vac): 2,393.724 kN (538,131 lbf). Isp: 311 sec. Burn time: 125 sec. Isp(sl): 269 sec. Diameter: 3.33 m (10.92 ft). Span: 3.33 m (10.92 ft). Length: 27.00 m (88.00 ft). Propellants: Lox/Kerosene. No Engines: 6. Engine: RD-111. Status: Study 1959. Comments: R-7 strap-ons increased in size dimensionally 50%, equipped with 6 engines from R-9. Boost nuclear thermal core stage to altitude before ignition of nuclear engine. Masses calculated based on vehicle total weight and performance.
  • Stage 1. 1 x YaKhR-2 Core. Gross Mass: 180,000 kg (390,000 lb). Empty Mass: 22,000 kg (48,000 lb). Thrust (vac): 1,660.000 kN (373,180 lbf). Isp: 470 sec. Burn time: 430 sec. Isp(sl): 430 sec. Diameter: 3.33 m (10.92 ft). Span: 3.33 m (10.92 ft). Length: 37.00 m (121.00 ft). Propellants: Nuclear/Ammonia. No Engines: 1. Engine: YaRD OKB-456. Status: Study 1959. Comments: Engines in development by Bondayuk and Glushko. Alternate propellants ammonia only or ammonia/alcohol mixture. Four expansion nozzles fed by single reactor. Masses calculated based on given vehicle gross weight and performance.

Status: Cancelled 1949.
Gross mass: 888,000 kg (1,957,000 lb).
Payload: 40,000 kg (88,000 lb).
Height: 44.00 m (144.00 ft).
Diameter: 3.33 m (10.92 ft).
Thrust: 12,422.80 kN (2,792,757 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • RD-111 Glushko Lox/Kerosene rocket engine. 1628 kN. R-9 stage 1. Isp=317s. Developed for R-9 ICBM. It had special flexible pipelines and gimbals, allowing lox loading in 20 minutes. First flight 1961. More...
  • YaRD OKB-456 Glushko nuclear/ammonia rocket engine. 1373 kN. Development ended 1960. Isp=470s. Used nuclear reactor in cylindrical housing, operating at 3000 deg K. Propellant heated in the reactor and exhausted through four expansion nozzles More...

See also
Associated Manufacturers and Agencies
  • Korolev Russian manufacturer of rockets, spacecraft, and rocket engines. Korolev Design Bureau, Kaliningrad, Russia. More...

Bibliography
  • Semenov, Yu. P., S P Korolev Space Corporation Energia, RKK Energia, 1994.

Associated Stages
  • YaKhR-2 Core Nuclear/Ammonia propellant rocket stage. Loaded/empty mass 180,000/22,000 kg. Thrust 1,660.00 kN. Vacuum specific impulse 470 seconds. Engines in development by Bondayuk and Glushko. Alternate propellants ammonia only or ammonia/alcohol mixture. Four expansion nozzles fed by single reactor. Masses calculated based on given vehicle gross weight and performance. More...
  • YaKhR-2 Strap-on Lox/Kerosene propellant rocket stage. Loaded/empty mass 110,000/8,250 kg. Thrust 2,393.72 kN. Vacuum specific impulse 311 seconds. R-7 strap-ons increased in size dimensionally 50%, equipped with 6 engines from R-9. Boost nuclear thermal core stage to altitude before ignition of nuclear engine. Masses calculated based on vehicle total weight and performance. More...

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