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RLA-120
Credit: © Mark Wade Russian heavy-lift orbital launch vehicle. Medium booster concept with a payload to low earth orbit of 30 metric tons using the RLA-120 core and a 150 metric ton upper stage. Glushko proposed that the RLA-120 would boost reconnaissance satellites and modules of his POS Permanent Orbital Station into a sun synchronous orbit beginning in 1979. The government rejected the RLA concept, but this design led directly to the successful Zenit-2 booster.
Status: Design 1974. Payload: 30,000 kg (66,000 lb). Thrust: 11,000.00 kN (2,472,000 lbf). Gross mass: 980,000 kg (2,160,000 lb). Height: 45.00 m (147.00 ft). Diameter: 6.00 m (19.60 ft). Apogee: 500 km (310 mi).
LEO Payload: 30,000 kg (66,000 lb) to a 500 km orbit at 97.00 degrees. Development Cost $: 12,500.000 million in 1974 dollars.
Stage Data - RLA-120
- Stage 1. 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 2. 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.
Family: heavy-lift, orbital launch vehicle. Country: Russia. Engines: RLA-1200. Stages: RLA-2, RLA-1. Agency: Korolev bureau. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
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