Encyclopedia Astronautica
RLA-150



rla150.jpg
RLA-150
Credit: © Mark Wade
Russian heavy-lift orbital launch vehicle. Super-booster concept with a payload to low earth orbit of 250 metric tons using six modules as the first stage and the RLA-120 core. Glushko proposed that the booster could launch a Soviet manned Mars landing by 1983. The government rejected the RLA concept, but it did lead to the Energia booster of the 1980's.

LEO Payload: 250,000 kg (550,000 lb) to a 185 km orbit at 52.00 degrees. Development Cost $: 12,500.000 million in 1974 dollars.

Stage Data - RLA-150

  • Stage 1. 6 x RLA-1. Gross Mass: 800,000 kg (1,760,000 lb). Empty Mass: 45,000 kg (99,000 lb). Thrust (vac): 11,700.000 kN (2,630,200 lbf). Isp: 337 sec. Burn time: 210 sec. Isp(sl): 311 sec. Diameter: 6.00 m (19.60 ft). Span: 6.00 m (19.60 ft). Length: 30.00 m (98.00 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RLA-1200. Status: Study 1974. Comments: Empty mass, specific impulses, length estimated by comparison to smaller Zenit successor design.
  • Stage 2. 1 x RLA-1. Gross Mass: 800,000 kg (1,760,000 lb). Empty Mass: 45,000 kg (99,000 lb). Thrust (vac): 11,700.000 kN (2,630,200 lbf). Isp: 337 sec. Burn time: 210 sec. Isp(sl): 311 sec. Diameter: 6.00 m (19.60 ft). Span: 6.00 m (19.60 ft). Length: 30.00 m (98.00 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RLA-1200. Status: Study 1974. Comments: Empty mass, specific impulses, length estimated by comparison to smaller Zenit successor design.
  • Stage 3. 1 x RLA-2. Gross Mass: 150,000 kg (330,000 lb). Empty Mass: 10,000 kg (22,000 lb). Thrust (vac): 2,940.000 kN (660,930 lbf). Isp: 349 sec. Burn time: 160 sec. Diameter: 6.00 m (19.60 ft). Span: 6.00 m (19.60 ft). Length: 12.00 m (39.00 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RLA-300. Status: Study 1974. Comments: Empty mass, specific impulses, length estimated by comparison to smaller Zenit successor design.

Status: Design 1974.
Gross mass: 6,000,000 kg (13,200,000 lb).
Payload: 250,000 kg (550,000 lb).
Height: 45.00 m (147.00 ft).
Diameter: 6.00 m (19.60 ft).
Thrust: 65,000.00 kN (14,612,000 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • RLA-1200 Glushko Lox/Kerosene rocket engine. 12,700 kN. Design 1974. Proposed engines for the RLA series launch vehicles. This version would use four chambers. 'Down-sized' to 200 tonnes thrust for Energia. More...

See also
  • RLA The RLA (Rocket Flight Apparatus) family of modular, lox/kerosene powered vehicles were designed by Glushko in 1974 to meet the Soviet military's third-generation space launch requirements. The approach was rejected by 1976 in favor of the Zenit/Energia family using both lox/kerosene amd lox/hydrogen stages. More...

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

Associated Stages
  • RLA-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 800,000/45,000 kg. Thrust 11,700.00 kN. Vacuum specific impulse 337 seconds. Empty mass, specific impulses, length estimated by comparison to smaller Zenit successor design. More...
  • RLA-2 Lox/Kerosene propellant rocket stage. Loaded/empty mass 150,000/10,000 kg. Thrust 2,940.00 kN. Vacuum specific impulse 349 seconds. Empty mass, specific impulses, length estimated by comparison to smaller Zenit successor design. More...

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