Encyclopedia Astronautica
Albatros



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Albatros 3 view
Credit: © Mark Wade
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Albatros Shuttle
Credit: © Mark Wade
Unique Russian space shuttle design of 1974. Hydrofoil-launched, winged recoverable first and second stages. Hydrofoil would have been propelled to launch speed by the launch vehicles rocket engines, using a 200 tonne fuel store in the hydrofoil. Advantages: launch from the Caspian Sea into a variety of orbital inclinations, variations in launch track possible to meet range safety requirements. Proposal of Alexeyev/Sukhoi OKBs.

LEO Payload: 30,000 kg (66,000 lb) to a 220 km orbit.

Stage Data - Albatros

  • Stage 0. 1 x Albatros Momentum Block. Gross Mass: 2,000,000 kg (4,400,000 lb). Empty Mass: 1,800,000 kg (3,900,000 lb). Thrust (vac): 0.0000 N ( lbf). Isp: 455 sec. Burn time: 110 sec. Isp(sl): 337 sec. Diameter: 10.00 m (32.00 ft). Span: 20.00 m (65.00 ft). Length: 70.00 m (229.00 ft). Propellants: Lox/LH2. Engine: None. Status: Study 1974. Comments: Unique hydrofoil launch stage for Albatros. Contains 200,000 kg propellants for acceleration by Albatros stage 1 motors to 50 m/s / 180 km/hr launch conditions. Designed by Alexeyev Hydrofoil/Ekranoplan OKB.
  • Stage 1. 1 x Albatros Carrier Aircraft. Gross Mass: 1,250,000 kg (2,750,000 lb). Empty Mass: 210,000 kg (460,000 lb). Thrust (vac): 7,840.000 kN (1,762,500 lbf). Isp: 455 sec. Burn time: 580 sec. Isp(sl): 337 sec. Diameter: 7.00 m (22.90 ft). Span: 40.00 m (131.00 ft). Length: 91.00 m (298.00 ft). Propellants: Lox/LH2. No Engines: 4. Engine: RD-0120. Status: Study 1974. Comments: Configuration: delta wing with wingtip vertical stabilizers and canards. Engine type and performance, empty weight estimated.
  • Stage 2. 1 x Albatros Raketoplan. Gross Mass: 320,000 kg (700,000 lb). Empty Mass: 82,000 kg (180,000 lb). Thrust (vac): 1,960.000 kN (440,620 lbf). Isp: 455 sec. Burn time: 270 sec. Isp(sl): 337 sec. Diameter: 7.00 m (22.90 ft). Span: 25.00 m (82.00 ft). Length: 49.00 m (160.00 ft). Propellants: Lox/LH2. No Engines: 4. Status: Study 1974. Comments: Configuration: delta wing with wingtip vertical stabilizers.

Status: Study 1974.
Gross mass: 320,000 kg (700,000 lb).
Payload: 30,000 kg (66,000 lb).
Height: 109.00 m (357.00 ft).
Diameter: 7.00 m (22.90 ft).
Thrust: 7,263.40 kN (1,632,877 lbf).
Apogee: 220 km (130 mi).

More... - Chronology...


Associated Countries
Associated Spacecraft
  • Albatros Raketoplan Russian manned spaceplane. Study 1974. Unique Russian space shuttle design of 1974. Hydrofoil-launched, winged recoverable first and second stages. More...

Associated Engines
  • None Indicates that the stage shown is a propellant tank. The engine on another stage is drawing propellants from this tank. Performance shown is for that of the engine on the other stage. First flight 1964. More...
  • RD-0120 Kosberg lox/lh2 rocket engine. 1961 kN. Energia core stage. Design 1987. Isp=455s. First operational Russian cryogenic engine system, built to the same overall performance specifications as America's SSME, but using superior Russian technology. More...

See also
  • Winged In the beginning, nobody (except Jules Verne) thought anybody would be travelling to space and back in ballistic cannon balls. The only proper way for a space voyager to return to earth was at the controls of a real winged airplane. More...

Associated Manufacturers and Agencies
  • Alekseyev Russian manufacturer of rockets and spacecraft. Alekseyev Design Bureau, Russia. More...
  • Sukhoi Russian manufacturer of rockets and spacecraft. Sukhoi Design Bureau, Russia. More...

Bibliography
  • Kidger, Neville, "The Soviet Shuttle (Letter)", Spaceflight, 1983, Volume 25, page 251.

Associated Stages
  • Albatros Carrier Aircraft Lox/LH2 propellant rocket stage. Loaded/empty mass 1,250,000/210,000 kg. Thrust 7,840.00 kN. Vacuum specific impulse 455 seconds. Configuration: delta wing with wingtip vertical stabilizers and canards. Engine type and performance, empty weight estimated. More...
  • Albatros Momentum Block Lox/LH2 propellant rocket stage. Loaded/empty mass 2,000,000/1,800,000 kg. Unique hydrofoil launch stage for Albatros. Contains 200,000 kg propellants for acceleration by Albatros stage 1 motors to 50 m/s / 180 km/hr launch conditions. Designed by Alexeyev Hydrofoil/Ekranoplan OKB. More...
  • Albatros Raketoplan Lox/LH2 propellant rocket stage. Loaded/empty mass 320,000/82,000 kg. Thrust 1,960.00 kN. Vacuum specific impulse 455 seconds. Configuration: delta wing with wingtip vertical stabilizers. More...

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