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| Titan I | ||
|---|---|---|
| Stages | 2 | |
| 1 | Engines | 1 × LR87-AJ-3 |
| Thrust | 1,334 kN | |
| Burn time | 140 s | |
| Fuels | RP-1/LOX | |
| 2 | Engines | 1 × LR91-AJ-3 |
| Thrust | 356 kN | |
| Burn time | 155 s | |
| Fuels | RP-1/LOX | |
| Payload to LEO | 1816 kg | |
| Payload to GTO | ||
The Titan I was the United States' first true multistage ICBM. It was the first in a series of Titan rockets, but was unique from them in that it used LOX and RP-1 as its fuels, while the later versions all used storable fuels instead.
The program began in January 1955 and took shape in parallel with the Atlas (SM-65/HGM-25) intercontinental ballistic missile (ICBM). The Air Force's goal in launching the Titan program was twofold: one, to serve as a backup should Atlas fail; and two, to develop a large, two-stage missile with a longer range and bigger payload that also could serve as a booster for space flights.
Produced by the Glenn L. Martin Company, Titan I was a two-stage, liquid-fueled missile. The first stage delivered 300,000 pound (1,334 kN) of thrust; the second stage 80,000 pound (356 kN). Like Atlas, it burned RP-1 and LOX, which was a severe drawback.
The missile utilized both radio and all-inertial guidance. Deployed in a "hard" underground silo, it had to be raised to surface by a special launcher for firing. The Titan I had an effective range of 5,500 nautical miles. As each stage was fired, its engines and fuel tanks dropped away, thereby decreasing the weight and mass of the vehicle. That made for a more efficient missile, which resulted in increased range and a larger payload.
When the storable fueled Titan II and the solid fueled Minuteman I were deployed in 1963, the Titan I and Atlas missiles became obsolete. They were retired from service as ICBMs in early 1965. The Titan II remained in service until the 1980s however, as it carried a much larger payload that could be used as an effective "city buster".
Titan 1 Specifications
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