Encyclopedia entry

Atlas LV-3B / Mercury

Launch vehicle · USA

Original archive entry. The text, images and links below are kept as they were written.

American orbital launch vehicle. Atlas D modified for use in Project Mercury.

LEO Payload: 1,360 kg (2,990 lb) to a 185 km orbit at 28.00 degrees.

Stage Data - Atlas LV-3B / Mercury

Stage 0. 1 x Atlas MA-2. Gross Mass: 3,050 kg (6,720 lb). Empty Mass: 3,050 kg (6,720 lb). Thrust (vac): 1,517.422 kN (341,130 lbf). Isp: 282 sec. Burn time: 135 sec. Isp(sl): 248 sec. Diameter: 4.90 m (16.00 ft). Span: 4.90 m (16.00 ft).Propellants: Lox/Kerosene. No Engines: 2. Engine: XLR-89-5. Status: Out of Production.

Stage 1. 1 x Atlas D. Gross Mass: 113,050 kg (249,230 lb). Empty Mass: 2,347 kg (5,174 lb). Thrust (vac): 363.218 kN (81,655 lbf). Isp: 309 sec. Burn time: 303 sec. Isp(sl): 215 sec. Diameter: 3.05 m (10.00 ft). Span: 4.90 m (16.00 ft). Length: 21.20 m (69.50 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: XLR-105-5. Status: Out of Production.

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