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 INT-13
Part of Saturn I Family
American orbital launch vehicle. Chrysler Studies, 1966: S-IB with 2 Titan UA1205 with standard length S-IB stage, S-IVB stage, or 2 Titan UA1207 strap-ons with 20-foot stretched S-IB stage, S-IVB stage. S-IB ignition at sea level at same time as strap-ons.

Status: Study 1966. Payload: 36,590 kg (80,660 lb). Thrust: 20,116.10 kN (4,522,279 lbf). Gross mass: 1,307,320 kg (2,882,140 lb). Height: 58.00 m (190.00 ft). Diameter: 6.61 m (21.68 ft). Apogee: 169 km (105 mi).

LEO Payload: 36,590 kg (80,660 lb) to a 169 km orbit at 28.00 degrees. Flyaway Unit Cost 1985$: 48.720 million.

Stage Data - Saturn INT-13

  • Stage 0. 2 x Titan UA1207. Gross Mass: 319,330 kg (704,000 lb). Empty Mass: 51,230 kg (112,940 lb). Thrust (vac): 7,116.999 kN (1,599,965 lbf). Isp: 272 sec. Burn time: 120 sec. Isp(sl): 245 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 34.14 m (112.00 ft). Propellants: Solid. No Engines: 1. Engine: UA1207. Status: In Production.
  • Stage 1. 1 x Saturn IB-11. Gross Mass: 505,953 kg (1,115,435 lb). Empty Mass: 48,545 kg (107,023 lb). Thrust (vac): 8,241.763 kN (1,852,822 lbf). Isp: 296 sec. Burn time: 153 sec. Isp(sl): 262 sec. Diameter: 6.52 m (21.39 ft). Span: 6.52 m (21.39 ft). Length: 30.48 m (99.99 ft). Propellants: Lox/Kerosene. No Engines: 8. Engine: H-1b. Status: Study 1966. Comments: 20 foot stretch of Saturn IB for use with UA1207 7 segment solid rocket strap-on units.
  • Stage 2. 1 x Saturn IVB (S-IB). Gross Mass: 118,800 kg (261,900 lb). Empty Mass: 12,900 kg (28,400 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 IB version of S-IVB stage. Due to lower payload, 300 kg saving in structure compared to Saturn V version. Due to deletion of restart requirement, 700 kg saving in propulsion system (primarily reduction in helium for restart).



Family: orbital launch vehicle. People: von Braun. Country: USA. Engines: H-1b. Stages: Saturn IB-11, Saturn IVB (S-IB), UA1207.

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
© 1997-2017 Mark Wade - Contact
© / Conditions for Use