RLA135
Credit: © Mark Wade
Russian heavylift 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 RLA120 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 Zenit2 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  RLA135
 Stage 1. 2 x RLA1. 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: RLA1200. Status: Study 1974. Comments: Empty mass, specific impulses, length estimated by comparison to smaller Zenit successor design.
 Stage 2. 1 x RLA1. 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: RLA1200. Status: Study 1974. Comments: Empty mass, specific impulses, length estimated by comparison to smaller Zenit successor design.
 Stage 3. 1 x RLA2. 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: RLA300. 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

RLA1200 Glushko Lox/Kerosene rocket engine. 12,700 kN. Design 1974. Proposed engines for the RLA series launch vehicles. This version would use four chambers. 'Downsized' 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 thirdgeneration 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

RLA1 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...

RLA2 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...
Home  Browse  Contact
© / Conditions for Use