Titan 4

American orbital launch vehicle. Developed to handle military payloads designed for launch on Shuttle from Vandenberg before the USAF pulled out of the Shuttle program after the Challenger disaster. Further stretch of core from Titan 34, 7-segment solid rocket motors (developed for MOL but not used until 25 years later). Enlarged Centaur G used as upper stage (variant of stage designed for Shuttle but prohibited for flight safety reasons after Challenger). Completely revised electronics. All the changes resulted in major increase in cost of launch vehicle and launch operations.
Status: Out of production. Payload: 17,700 kg (39,000 lb). Thrust: 12,821.00 kN (2,882,275 lbf). Gross mass: 886,420 kg (1,954,220 lb). Height: 51.00 m (167.00 ft). Diameter: 4.33 m (14.20 ft). Apogee: 185 km (114 mi).

LEO Payload: 17,700 kg (39,000 lb) to a 185 km orbit. Payload: 6,350 kg (13,990 lb) to a GTO. Launch Price $: 400.000 million in 1985 dollars. Flyaway Unit Cost 1985$: 89.360 million in 1997 dollars.

Stage Data - Titan 4

Stage 0. 2 x 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. Status: In Production.

Stage 1. 1 x Titan 4-1. Gross Mass: 163,000 kg (359,000 lb). Empty Mass: 8,000 kg (17,600 lb). Thrust (vac): 2,428.312 kN (545,906 lbf). Isp: 302 sec. Burn time: 164 sec. Isp(sl): 250 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 26.37 m (86.51 ft). Propellants: N2O4/Aerozine-50. No Engines: 2. Engine: LR-87-11. Status: In Production.
Stage 2. 1 x Titan 4-2. Gross Mass: 39,500 kg (87,000 lb). Empty Mass: 4,500 kg (9,900 lb). Thrust (vac): 459.510 kN (103,302 lbf). Isp: 316 sec. Burn time: 223 sec. Isp(sl): 160 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 9.94 m (32.61 ft). Propellants: N2O4/Aerozine-50. No Engines: 1. Engine: LR-91-11. Status: In Production.
Stage 3. 1 x IUS-1. Gross Mass: 10,841 kg (23,900 lb). Empty Mass: 1,134 kg (2,500 lb). Thrust (vac): 181.501 kN (40,803 lbf). Isp: 296 sec. Burn time: 152 sec. Isp(sl): 220 sec. Diameter: 2.34 m (7.67 ft). Span: 2.34 m (7.67 ft). Length: 3.52 m (11.54 ft). Propellants: Solid. No Engines: 1. Engine: SRM-1. Other designations: Orbus 21D. Status: In Production.
Stage 3. 1 x Centaur G. Gross Mass: 23,880 kg (52,640 lb). Empty Mass: 2,775 kg (6,117 lb). Thrust (vac): 146.800 kN (33,002 lbf). Isp: 444 sec. Burn time: 625 sec. Diameter: 4.33 m (14.20 ft). Span: 4.33 m (14.20 ft). Length: 9.00 m (29.50 ft). Propellants: Lox/LH2. No Engines: 2. Engine: RL-10A-3A. Status: In Production. Comments: Centaur for Titan 4.
Stage 4. 1 x IUS-2. Gross Mass: 3,919 kg (8,639 lb). Empty Mass: 1,170 kg (2,570 lb). Thrust (vac): 78.413 kN (17,628 lbf). Isp: 304 sec. Burn time: 103 sec. Isp(sl): 200 sec. Diameter: 1.61 m (5.28 ft). Span: 1.61 m (5.28 ft). Length: 2.08 m (6.82 ft). Propellants: Solid. No Engines: 1. Engine: SRM-2. Other designations: TOS. Status: In Production.

From : Astronautix