Saturn MLV 5-1

Apollo CSM is made by Riksh.

AG1 : Light
AG2 : Antenn (Also activates Service modulle engine)
AG3 : Abort
AG4 : Deteach LAS
AG9 : Rotate Antenn (Named Solar Panels, I forgot to rename)
AG10 : RCS

American orbital launch vehicle. MSFC study, 1965. Improved Saturn V configuration studied under contract NAS8-11359. Saturn IC stretched 240 inches with 5.6 million pounds propellant and 5 F-1A engines; S-II stretched 41 inches with 1.0 million pounds propellant and 5 J-2 engines; S-IVB strengthened but with standard 230,000 lbs propellant, 1 J-2 engine.
Status: Study 1965. Payload: 137,250 kg (302,580 lb). Thrust: 40,019.90 kN (8,996,831 lbf). Gross mass: 3,501,350 kg (7,719,150 lb). Height: 111.00 m (364.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 185 km (114 mi).

LEO Payload: 137,250 kg (302,580 lb) to a 185 km orbit at 28.00 degrees. Payload: 49,600 kg (109,300 lb) to a translunar trajectory.

Stage Data - Saturn MLV-V-1

Stage 1. 1 x Saturn MS-IC-1. Gross Mass: 2,694,703 kg (5,940,803 lb). Empty Mass: 169,719 kg (374,166 lb). Thrust (vac): 45,948.754 kN (10,329,691 lbf). Isp: 310 sec. Burn time: 158 sec. Isp(sl): 270 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 48.15 m (157.97 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1A. Status: Study NASA 1966. Comments: Basic Saturn IC stretched 240 inches with F-1A engines uprated 20% in thrust and 6 second improvement in specific impulse.
Stage 2. 1 x Saturn MS-II-1. Gross Mass: 521,447 kg (1,149,593 lb). Empty Mass: 49,877 kg (109,959 lb). Thrust (vac): 5,165.790 kN (1,161,316 lbf). Isp: 425 sec. Burn time: 361 sec. Isp(sl): 306 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 25.88 m (84.90 ft). Propellants: Lox/LH2. No Engines: 5. Engine: J-2. Status: Study NASA 1966. Comments: Basic Saturn II with 41 inch stretch of hydrogen tank.
Stage 3. 1 x Saturn MS-IVB-1. Gross Mass: 120,500 kg (265,600 lb). Empty Mass: 13,900 kg (30,600 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 475 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 18.08 m (59.31 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Study 1965. Comments: Marshall studies, 1965: S-IVB structurally strengthened to handle larger payloads, otherwise unchanged.

From : astronautix