Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z

---

Saturn V-B

---

Status: Study 1968. Payload: 22,600 kg (49,800 lb). Thrust: 33,737.70 kN (7,584,537 lbf). Gross mass: 2,313,320 kg (5,099,990 lb). Height: 50.00 m (164.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 185 km (114 mi).

LEO Payload: 22,600 kg (49,800 lb) to a 185 km orbit at 28.00 degrees.

Stage Data - Saturn V-B

• Stage 0. 1 x Saturn S-ID Booster. Gross Mass: 67,100 kg (147,900 lb). Empty Mass: 67,100 kg (147,900 lb). Thrust (vac): 30,962.500 kN (6,960,647 lbf). Isp: 304 sec. Burn time: 154 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.01 m (62.36 ft). Length: 42.07 m (138.02 ft). Propellants: Lox/Kerosene. No Engines: 4. Engine: F-1. Status: Study 1967. Comments: Boeing studies, 1967:'Stage and a half' S-1C with four outboard F-1's jettisoned and inboard F-1 functioning as sustainer as in Atlas. Booster half stage recoverable. Mass estimated based on double mass of four F-1's (based on Atlas example).

• Stage 1. 1 x Saturn S-ID Sustainer. Gross Mass: 2,219,100 kg (4,892,200 lb). Empty Mass: 68,100 kg (150,100 lb). Thrust (vac): 7,740.300 kN (1,740,089 lbf). Isp: 304 sec. Burn time: 315 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.01 m (62.36 ft). Length: 42.07 m (138.02 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: F-1. Status: Study 1967. Comments: Boeing studies, 1967:'Stage and a half' S-1C with four outboard F-1's jettisoned and inboard F-1 functioning as sustainer as in Atlas. Booster half stage burns 124 seconds in this configuration.