Titan-II

		Orbital launches	Period	Last launch
Titan -2	Gemini	13	1964 - 1966	11.11.1966
Titan -23G		13	1988 - 2003	18.10.2003

The Titan-I (HGM-25A) ICBM was the first version of the Titan family of rockets. It was operational from early 1962 to mid-1965. Titan I was a two-stage, liquid-fueled missile. The first stage delivered 300,000 pounds (1,330 kN) of thrust, the second stage 80,000 pounds (356 kN). The fact that Titan I, like Atlas, burned RP-1 and LOX meant that the oxidizer had to be loaded into the missile just before launch from the underground storage tank, and the missile raised above ground on the enormous elevator system, exposing the missile for some time before launch. The first stage consists of two ground ignited Aerojet LR-87-AJ-3 liquid propellant rocket engines, while the second stage consists of an Aerojet LR-91-AJ-3 liquid propellant rocket engine.

The Titan-II (LGM-25C) ICBM was the successor to the Titan-I, and was operational between 1964 and 1984. It used storable propellants, which reduced the time to launch and permitted it to be launched from its silo. The Titan II used a hypergolic combination of Nitrogen Tetroxide and Aerozine 50 (a 50/50 mix of Hydrazine and UDMH) for its oxidizer and fuel. The first stage consists of two ground ignited Aerojet LR-87-AJ-5 liquid propellant rocket engines, while the second stage consists of an Aerojet LR-91-AJ-5 liquid propellant rocket engine.

	Titan-I (HGM-25A)	Titan-II (LGH-25C)
Length	29.9 m (98 ft)	31.4 m (103 ft)
Diameter	1st stage 3.05 m (10 ft) 2nd stage: 2.44 m (8 ft)	3.05 m (10ft)
Weight	99.7 tons (220000 lb)	149.5 tons (330000 lb)
Propulsion	1st stage: 2x Aerojet LR-87-AJ-3; 300,000 lb thrust s.l. 2nd stage: 1x Aerojet LR-91-AJ-3; 80,000 lb thrust vac	1st stage: 2x Aerojet LR-87-AJ-5; 430,000 lb thrust s.l. 2nd stage: 1x Aerojet LR-91-AJ-5; 100,000 lb thrust vac
Propellant	RP-1 /LOX	Aerozin 50 / N2O4

The decommissioned ICBM Titan-II was purpose-built as space launcher that have been refurbished and equipped with hardware required for use as space launch vehicle.
The first launcher, the Titan 2(G), was converted only for the Gemini program, NASA, and from 1964 to 1966 a total of 13 times started. The original engines of the Titan-II were replaced by the new combination LR-87-AJ-7 and LR-91-AJ-7.

The second launcher, the Titan 23G, was introduced in 1988 in limited numbers. The unit was recruited from remnants of USAF ICBM's and was converted by Martin Marietta. In contrast to the Gemini-Titan 2 was but the original engine combination LR-87-AJ-5 and LR-91-AJ-5 not replaced. To reinforce the overall thrust a third stage was added Thiokol Star 37 XFP. This motor into the fairing was placed. The fairing was acquired from the Titan 34D in three variants of 20 ft, 25 ft and 30 ft in length.The Titan 23G is used by the US Air Force government payloads to low polar orbits. The refurbished launchers were capable to place 2170 kg payloads into low-Earth orbit.