Credit: © Mark Wade
American orbital launch vehicle. UA study, 1965. Saturn variant using various combinations of 156 inch rocket motors as first and second stages, with S-IVB upper stage.
|Number of Strapon Motors||4||3||2||2|
|Number of Core Stage Motors||1||1||1||0|
|Payload with 4 Segment Motors||79,000||68,000||54,000||36,000|
| Payload with 3 Segment Motors||70,000||59,000||45,000||29,000|
| Payload with 2 Segment Motors||57,000||47,000||36,000||24,000|
| Payload with 1 Segment Motors||45,000||39,000||27,000||18,000|
LEO Payload: 40,000 kg (88,000 lb) to a 185 km orbit at 28.00 degrees in 1985 dollars. Flyaway Unit Cost $: 200.000 million.
Stage Data - Saturn INT-27
- Stage 1. 4 x UA 156 inch 4 Segment. Gross Mass: 725,500 kg (1,599,400 lb). Empty Mass: 49,250 kg (108,570 lb). Thrust (vac): 18,181.000 kN (4,087,251 lbf). Isp: 263 sec. Burn time: 94 sec. Isp(sl): 238 sec. Diameter: 3.96 m (12.99 ft). Span: 3.96 m (12.99 ft). Length: 38.00 m (124.00 ft). Propellants: Solid. No Engines: 1. Engine: UA-156. Status: Development 1968. Comments: 4 Segment version of basic 3-segment UA 156 motor.
- 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 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).
Status: Study 1965.
More... - Chronology...
Gross mass: 3,068,800 kg (6,765,500 lb).
Payload: 40,000 kg (88,000 lb).
Height: 67.00 m (219.00 ft).
Diameter: 6.61 m (21.68 ft).
Thrust: 65,813.00 kN (14,795,350 lbf).
Apogee: 185 km (114 mi).
UA-156 CSD solid rocket engine. 8924.3 kN. Tested 1968. Isp=263s. Proposed as strap-on booster for Saturn INT-27, Saturn V-25(S)B, Saturn V-25(S)U. More...
Saturn V America's booster for the Apollo manned lunar landing. The design was frozen before a landing mode was selected; the Saturn V could be used for either Earth-Orbit-Rendezvous or Lunar-Orbit-Rendezvous methods. The vehicle ended up with the same payload capability as the 'too large' Nova. The basic diameter was dictated by the ceiling height at the Michoud factory selected for first stage manufacture. Despite the study of innumerable variants, production was ended after only 12 were built and America spent the next fifty years in a pointless slow-motion withdrawal from manned space exploration. More...
Saturn The Saturn launch vehicle was the penultimate expression of the Peenemuende Rocket Team's designs for manned exploration of the moon and Mars. Numerous designs and variants were studied, but in the end only three models - the Saturn I, IB, and V - were built in the 1960's, and then only used to support NASA's Apollo moon landing program. More...
Associated Manufacturers and Agencies
Von Braun American manufacturer of rockets and spacecraft. Von Braun, USA. More...
Saturn IVB (S-IB) Lox/LH2 propellant rocket stage. Loaded/empty mass 118,800/12,900 kg. Thrust 1,031.60 kN. Vacuum specific impulse 421 seconds. Saturn IB version of S-IVB stage. Due to lower payload 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). More...
UA 156 inch 4 Segment Solid propellant rocket stage. Loaded/empty mass 725,500/49,250 kg. Thrust 18,181.00 kN. Vacuum specific impulse 263 seconds. 4 Segment version of basic 3-segment UA 156 motor. More...
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