RLA-135
Credit: © Mark Wade
Russian heavy-lift orbital launch vehicle. Heavyweight booster concept with a payload to low earth orbit of 100 metric tons using two modules as the first stage and the RLA-120 core. Glushko proposed that the booster could launch a Soviet manned lunar landing by 1981. The government rejected the RLA concept, but it did lead to the Zenit-2 and Energia boosters of the 1980's.
LEO Payload: 100,000 kg (220,000 lb) to a 185 km orbit at 52.00 degrees. Development Cost $: 12,500.000 million in 1974 dollars.
Stage Data - RLA-135
- Stage 1. 2 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: 2,650,000 kg (5,840,000 lb).
Payload: 100,000 kg (220,000 lb).
Height: 45.00 m (147.00 ft).
Diameter: 6.00 m (19.60 ft).
Thrust: 32,000.00 kN (7,193,000 lbf).
Apogee: 185 km (114 mi).
More... - Chronology...
Associated Countries
Associated Engines
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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
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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
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Korolev Russian manufacturer of rockets, spacecraft, and rocket engines. Korolev Design Bureau, Kaliningrad, Russia. More...
Associated Stages
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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...
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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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