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Saturn V-25(S)U

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Status: Study 1968. Payload: 248,663 kg (548,208 lb). Thrust: 72,338.40 kN (16,262,319 lbf). Gross mass: 6,439,300 kg (14,196,200 lb). Height: 153.00 m (501.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 486 km (301 mi).

LEO Payload: 248,663 kg (548,208 lb) to a 486 km orbit at 28.00 degrees. Payload: 160,000 kg (350,000 lb) to a translunar trajectory. Flyaway Unit Cost 1985$: 174.000 million.

Stage Data - Saturn V-25(S)U

• Stage 0. 4 x UA 156 inch. Gross Mass: 544,311 kg (1,200,000 lb). Empty Mass: 37,195 kg (82,000 lb). Thrust (vac): 8,924.482 kN (2,006,303 lbf). Isp: 263 sec. Burn time: 157 sec. Isp(sl): 238 sec. Diameter: 3.96 m (12.99 ft). Span: 3.96 m (12.99 ft). Length: 34.00 m (111.00 ft). Propellants: Solid. No Engines: 1. Engine: UA-156. Status: Development 1965.

• Stage 1. 1 x Saturn MS-IC-25(S). Gross Mass: 3,223,800 kg (7,107,200 lb). Empty Mass: 211,900 kg (467,100 lb). Thrust (vac): 45,925.500 kN (10,324,463 lbf). Isp: 304 sec. Burn time: 192 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 54.70 m (179.40 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1A. Status: Study Boeing 1967. Comments: S-IC with 41.5 foot stretch, 6,640,0000 lbs propellant, uprated F-1 engines.

• Stage 2. 1 x Saturn MS-II-4(S)B. Gross Mass: 494,100 kg (1,089,300 lb). Empty Mass: 42,300 kg (93,200 lb). Thrust (vac): 5,169.000 kN (1,162,037 lbf). Isp: 421 sec. Burn time: 355 sec. Isp(sl): 200 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 24.84 m (81.49 ft). Propellants: Lox/LH2. No Engines: 5. Engine: J-2. Status: Study Boeing 1967. Comments: Standard S-II but with structural strength increased from 86% to 502% depending on station, resulting in 8.6% increase in empty weight.

• Stage 3. 1 x Saturn S-N V-25(S)U. Gross Mass: 245,760 kg (541,800 lb). Empty Mass: 71,190 kg (156,940 lb). Thrust (vac): 889.325 kN (199,928 lbf). Isp: 825 sec. Burn time: 1,500 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 48.17 m (158.03 ft). Propellants: Nuclear/LH2. No Engines: 1. Engine: Nerva. Status: Study 1969. Comments: Version of Nerva studied by Boeing for manned Mars expedition.

• 156-inch solid-propellant rocket motor fired for the first time. - .

  Lockheed Propulsion Company test fired a 156-inch diameter, solid-propellant rocket motor for the first time. The one-segment test motor (156-3-L), with tab jet thrust vector control, produced more than 900,000 pounds of thrust during its 110-second firing. The test was conducted as part of the Space Systems Division's Large Solid Rocket Motor research and development program (Program 623A).