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RLA-150

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RLA-150 Credit: © Mark Wade

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

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.