Saturn V-Centaur (original) (raw)

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Saturn V-Centaur

Part of Saturn V

S-1C details

S-1C details
Credit: © Mark Wade

American orbital launch vehicle. MSFC study, 1968. S-ID stage-and-a-half first stage and Saturn IVB second stage. Centaur available as third stage for deep space missions. 30% performance improvement over Saturn V-A/Saturn INT-20 with standard Saturn IC first stage.

Status: Study 1968. Payload: 118,000 kg (260,000 lb). Thrust: 33,737.90 kN (7,584,582 lbf). Gross mass: 3,054,750 kg (6,734,570 lb). Height: 113.00 m (370.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 185 km (114 mi).

LEO Payload: 118,000 kg (260,000 lb) to a 185 km orbit at 28.00 degrees. Payload: 39,000 kg (85,000 lb) to a Mars flyby. Flyaway Unit Cost 1985$: 701.800 million.

Stage Data - Saturn V-Centaur

Stage 1. 1 x Saturn IC. Gross Mass: 2,286,217 kg (5,040,245 lb). Empty Mass: 135,218 kg (298,104 lb). Thrust (vac): 38,703.160 kN (8,700,816 lbf). Isp: 304 sec. Burn time: 161 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 42.06 m (137.99 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1. Status: Out of Production.
Stage 2. 1 x Saturn II. Gross Mass: 490,778 kg (1,081,980 lb). Empty Mass: 39,048 kg (86,086 lb). Thrust (vac): 5,165.790 kN (1,161,316 lbf). Isp: 421 sec. Burn time: 390 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: Out of Production.
Stage 3. 1 x Saturn IVB (S-V). Gross Mass: 119,900 kg (264,300 lb). Empty Mass: 13,300 kg (29,300 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: 17.80 m (58.30 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Out of Production. Comments: Saturn V version of S-IVB stage.
Stage 4. 1 x Centaur D/E. Gross Mass: 16,258 kg (35,842 lb). Empty Mass: 2,631 kg (5,800 lb). Thrust (vac): 131.222 kN (29,500 lbf). Isp: 444 sec. Burn time: 470 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 9.60 m (31.40 ft). Propellants: Lox/LH2. No Engines: 2. Engine: RL-10A-3. Status: Out of Production.

Family: orbital launch vehicle. People: von Braun. Country: USA. Engines: RL-10A-3. Stages: Saturn IC, Saturn II, Centaur D/E, Saturn IVB (S-V).

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