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Saturn IB-INT-27
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.
Status: Study 1965. Payload: 40,000 kg (88,000 lb). Thrust: 65,813.00 kN (14,795,350 lbf). Gross mass: 3,068,800 kg (6,765,500 lb). Height: 67.00 m (219.00 ft). Diameter: 6.61 m (21.68 ft). Apogee: 185 km (114 mi).
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. Flyaway Unit Cost 1985$: 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, 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 IVB (S-IB), UA-156. 1964 May 28 - . LV Family: Saturn I, Saturn V. Launch Vehicle: Saturn INT-27, Saturn V-25(S)B, Saturn V-25(S)U.
- 156-inch solid-propellant rocket motor fired for the first time. - .
Lockheed Propulsion Company test fired a 156-inch diameter, solid-propellant rocket motor for the first time. The one-segment test motor (156-3-L), with tab jet thrust vector control, produced more than 900,000 pounds of thrust during its 110-second firing. The test was conducted as part of the Space Systems Division's Large Solid Rocket Motor research and development program (Program 623A).
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