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Orbital launch vehicle. Year: 1988. Family: Titan. Country: USA. Status: Study 1988. Proposed Titan upgrade with cryogenic core as replacement for NLS. Manufacturer: Martin. Liftoff Thrust: 16,533.600 kN (3,716,901 lbf). Total Mass: 1,138,660 kg (2,510,310 lb). Core Diameter: 6.00 m (19.60 ft). Total Length: 72.00 m (236.00 ft). Flyaway Unit Cost $: 48.720 million. in: 1985 unit dollars.
Stage Data - Titan 5 - Stage Number: 0. 2 x Stage: 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.
- Stage Number: 1. 1 x Stage: Titan 5. Gross Mass: 500,000 kg (1,100,000 lb). Empty Mass: 45,000 kg (99,000 lb). Thrust (vac): 4,457.100 kN (1,001,996 lbf). Isp: 425 sec. Burn time: 420 sec. Isp(sl): 354 sec. Diameter: 6.00 m (19.60 ft). Span: 6.00 m (19.60 ft). Length: 60.00 m (196.00 ft). Propellants: Lox/LH2. No Engines: 1. Engine: PW 1000000 lb LH2. Status: Study 1988. Part of launch vehicle proposed by Martin as alternative to NLS. All figures estimated based on 1,000,000 lb thrust single engine.
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