Titan IIIM

Titan IIIM

File:Dorian 10.jpg Titan IIIM proposal
Function	Expendable launch system
	Martin Marietta
	United States
Cost per launch	US$22 million (1965)
Size
	39.0 m (128.0 ft)
	3.05 m (10.0 ft)
	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	CCAFS LC-40 Vandenberg AFB SLC-6
Total launches	0
Boosters – UA1207
No. boosters	2
	34.14 m (112.0 ft)
	3.05 m (10.0 ft)
Empty mass	51,230 kg (112,940 lb)
Gross mass	319,330 kg (704,000 lb)
	7,116.999 kN (1,599,965 lbf)
Specific impulse	272 s (2.67 km/s)
Burn time	120 s
Propellant	Solid
First stage – Titan IIIB-1
	23.99 m (78.7 ft)
	3.05 m (10.0 ft)
Empty mass	7,000 kg (15,400 lb)
Gross mass	139,935 kg (308,504 lb)
	2 × LR87-11
	2,413.191 kN (542,507 lbf)
Specific impulse	302 s (2.96 km/s)
Burn time	161 s
Propellant	A-50 / N2O4
Second stage – Titan IIIB-2
	8.6 m (28.2 ft)
	3.05 m (10.0 ft)
Empty mass	2,900 kg (6,400 lb)
Gross mass	37,560 kg (82,810 lb)
	1 × LR91-11
	460.314 kN (103,483 lbf)
Specific impulse	316 s (3.10 km/s)
Burn time	230 s
Propellant	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 stretched core stage was used on some versions of the Titan IIIB and the projected UA1207 solid booster rockets were eventually used on the Titan IV.

Development

• 1969 April 27 - First static test firing of Titan IIIM seven segment solid rocket booster motor. Firing took place at the United Technologies Coyote Canyon test site at the southern edge of San Jose, California, and generated 700,000 kgf (6,900,000 N; 1,500,000 lbf) for two minutes.

Planned flights

• 1970 - Uncrewed Gemini-B/Titan IIIM qualification flight
• 1971 - Uncrewed Gemini-B/Titan IIIM qualification flight

External links

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