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-18
Part of Saturn V
Saturn 2SL/120" SRB Saturn 2SL 120 inch strapons Credit: © Mark Wade |
North American study, 1966. Saturn variant with Titan UA1205 or 1207 motors as boosters, Saturn II stage as core, and Saturn IVB upper stage. Various combinations of numbers of strap-ons, propellant loading of the two core stages, and sea-level versus altitude ignition were studied.
Status: Study 1966. Payload: 66,590 kg (146,800 lb). Thrust: 25,642.10 kN (5,764,573 lbf). Gross mass: 1,966,810 kg (4,336,070 lb). Height: 51.00 m (167.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 185 km (114 mi).
Liftoff Mass - kg | Strapon
Motor Type | Number of Strapons | S-II Propellant - kg | S-IVB Propellant
- kg | Payload - kg |
1,132,000 | Titan UA1204 | 4 | 215,400 | 80,300 | 21,300 |
1,132,000 | Titan UA1204 | 4 | 215,400 | 78,500 | 23,100 |
1,030,400 | Titan UA1207 | 2 | 254,000 | 80,700 | 27,400 |
1,132,400 | Titan UA1207 | 2 | 349,200 | 79,800 | 35,400 |
1,083,000 | Titan UA1205 | 2 | 431,600 | 77,400 | 40,500 |
1,570,500 | Titan UA1205 | 4 | 440,400 | 74,400 | 51,700 |
1,895,200 | Titan UA1207 | 4 | 446,700 | 75,700 | 66,400 |
1,476,200 | Titan UA1205 | 4 | 446,700 | No
S-IVB | 39,000 |
1,779,600 | Titan UA1207 | 4 | 446,700 | No
S-IVB | 44,000 |
LEO Payload: 66,590 kg (146,800 lb) to a 185 km orbit at 28.00 degrees. Flyaway Unit Cost 1985$: 387.440 million.
Stage Data - Saturn INT-18
- Stage 0. 4 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 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 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.
Stages:
Saturn II,
Saturn IVB (S-IB),
UA1207.
Photo Gallery
| Saturn MLV 2-120-7 Credit: © Mark Wade |
| Saturn 2-120-5 Credit: © Mark Wade |
| Saturn 2-120-4 Credit: © Mark Wade |
Back to top of page
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
© 1997-2019 Mark Wade - Contact
© / Conditions for Use