Saturn INT-17

North American study, 1966. Saturn variant with a modified S-II first stage with seven high-performance HG-3 engines; S-IVB second stage. Poor performance and cost-effectiveness and not studied further.

LEO Payload: 42,000 kg (92,000 lb) to a 185 km orbit at 28.00 degrees.

Stage Data - Saturn INT-17

• Stage 1. 1 x Saturn II-INT-17. Gross Mass: 495,000 kg (1,091,000 lb). Empty Mass: 48,000 kg (105,000 lb). Thrust (vac): 9,713.400 kN (2,183,659 lbf). Isp: 450 sec. Burn time: 200 sec. Isp(sl): 275 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: 7. Engine: HG-3-SL. Status: Study 1966. Comments: Saturn II modified with reduced expansion ratio HG-3 high pressure engines for use a first stage (sea level launch).

• 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).