Saturn V-23(L)

American orbital launch vehicle. Boeing study, 1967. 4 260 inch liquid propellant boosters (each with 2 F-1's!).; Saturn IC stretched 240 inches with 5.6 million pounds propellant and 5 F-1 engines; S-II strengthened but with standard 930,000 pounds propellant and 5 J-2 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2 engine.

LEO Payload: 262,670 kg (579,080 lb) to a 185 km orbit at 28.00 degrees. Payload: 99,850 kg (220,130 lb) to a translunar trajectory.

Stage Data - Saturn V-23(L)

• Stage 0. 4 x Saturn MS-LRB-23(L). Gross Mass: 874,100 kg (1,927,000 lb). Empty Mass: 18,100 kg (39,900 lb). Thrust (vac): 15,486.600 kN (3,481,526 lbf). Isp: 304 sec. Burn time: 162 sec. Isp(sl): 265 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 47.85 m (156.98 ft). Propellants: Lox/Kerosene. No Engines: 2. Engine: F-1. Status: Study Boeing 1967. Comments: Liquid rocket booster strap-ons using 2 F-1's.

• Stage 1. 1 x Saturn MS-IC-23(L). Gross Mass: 2,694,000 kg (5,939,000 lb). Empty Mass: 169,000 kg (372,000 lb). Thrust (vac): 38,703.160 kN (8,700,816 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: 48.15 m (157.97 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1. Status: Study NASA 1966. Comments: Basic Saturn IC stretched 240 inches with standard 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 MS-IVB-1A. Gross Mass: 179,200 kg (395,000 lb). Empty Mass: 20,400 kg (44,900 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 625 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 22.82 m (74.86 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Study Boeing 1967. Comments: S-IVB with 16.5 foot stretch, 350,000 pounds propellant, standard J-2 engine.