Titan IIIM

Titan IIIM

Titan IIIM proposal
Function Expendable launch system
Manufacturer Martin Marietta
Country of origin United States
Cost per launch US$22 million (1965)
Size
Height 39.0 m (128.0 ft)
Diameter 3.05 m (10.0 ft)
Mass 836,560 kg (1,844,300 lb)
Stages 2
Capacity
Payload to 185 km (115 mi) 17,000 kg (37,000 lb)
Associated rockets
Family Titan
Launch history
Status Cancelled
Launch sites Vandenberg AFB SLC-4E
Total launches 0
Boosters - UA1207
No. boosters 2
Length 34.14 m (112.0 ft)
Diameter 3.05 m (10.0 ft)
Empty mass 51,230 kg (112,940 lb)
Gross mass 319,330 kg (704,000 lb)
Thrust 7,116.999 kN (1,599,965 lbf)
Specific impulse 272 s (2.67 km/s)
Burn time 120 sec
Fuel Solid
First stage - Titan IIIB-1
Length 23.99 m (78.7 ft)
Diameter 3.05 m (10.0 ft)
Empty mass 7,000 kg (15,400 lb)
Gross mass 139,935 kg (308,504 lb)
Engines 2 × LR87-11
Thrust 2,413.191 kN (542,507 lbf)
Specific impulse 302 s (2.96 km/s)
Burn time 161 sec
Fuel A-50/N2O4
Second stage - Titan IIIB-2
Length 8.6 m (28.2 ft)
Diameter 3.05 m (10.0 ft)
Empty mass 2,900 kg (6,400 lb)
Gross mass 37,560 kg (82,810 lb)
Engines 1 × LR91-11
Thrust 460.314 kN (103,483 lbf)
Specific impulse 316 s (3.10 km/s)
Burn time 230 sec
Fuel A-50/N2O4

The Titan IIIM was a planned American expendable launch system, intended to launch the Manned Orbiting Laboratory and other payloads. Development was cancelled in 1969. The projected UA1207 solid booster rockets were eventually used on the Titan IV.[1][2]

Development

Planned flights

References

  1. 1 2 "Titan 3M". Astronautix.com. Retrieved 25 June 2016.
  2. ↑ Shayler, David J. (2002). "Military Gemini". Gemini: Steps to the Moon. Springer-Praxis. ISBN 1-85233-405-3.

Media related to Titan IIIM at Wikimedia Commons

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