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Titan I

Launch of a Titan I ICBM from Cape Canaveral</center>
Fact sheet
Function	ICBM
Manufacturer	Martin Company
Country of origin	USA
Cost per Launch (1962)<td>$1.5m (USD)
Size
Height	31 m
Diameter	3.05 m
Mass	105,140 kg
Stages	2
<td colspan="2">Capacity <tr>	Payload to LEO<td>1800 (Never used as a launch vehicle) <tr> <td> <tr> <td> <tr> <td>
Launch History
Status	Retired
Launch Sites	Cape Canaveral LC-15, LC-16, LC-19 & LC-20 Vandenberg AFB OSTF SLTF LC-395
Total launches <td>70
Successes <td>53
Failures <td>17
Maiden flight <td>6 February 1959
Last flight <td>5 March 1965
First Stage
Engines	2 LR-87
Thrust	1,900 kN (430,000 lbf)
Specific Impulse<td> 290 sec
Burn time	140 seconds
Fuel	RP-1/LOX
Second Stage <tr> <td>Engines<td>1 LR-91 <tr> <td>Thrust<td>356 kN (80,000 lbf) <tr> <td>Specific Impulse <td> 308 sec <tr> <td>Burn time<td>155 seconds <tr> <td>Fuel<td>RP-1/LOX

The Titan I was the United States' first true multistage ICBM. It was the first in a series of Titan rockets, but was unique among 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.

The Titan I was also called the SM-68, the -68 designation formerly applying to the XB-68, a stillborne jet bomber design by Martin which was cancelled before two prototypes and one test model were completed.

Produced by the Glenn L. Martin Company (which became "The Martin Company" in 1957), Titan I was a two-stage, liquid-fueled missile. The first stage delivered 300,000 pounds force (1,330 kN) of thrust, the second stage 80,000 pounds force (356 kN). The fact that Titan I, like Atlas, burned RP-1 and LOX was a severe drawback from the military point of view (as the LOX is a major logistic problem, being rather hard to store and handle), and it severely curtailed the operational flexibility/reaction times of the missile system.

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 (10,200 km). When the first stage had finished consuming its propellant, it dropped away, thereby decreasing the mass of the vehicle. That made for a more efficient missile, which resulted in increased range and enabled 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 (a multi-megaton hydrogen warhead) that could be used as an effective "city buster".

Contents 1 Titan 1 Specifications 2 Service history 3 External links 4 Related content

[edit] Titan 1 Specifications

• Liftoff thrust: 1,296 kN Total mass: 105,142 kg
• Core diameter: 3.1 m. Total length: 31.0 m
• Development cost: $1,643,300,000.00 in 1960 dollars.
• Flyaway cost: $1,500,000.00 each, in 1962 dollars.
• Total development missiles built: 47. Total missiles fired: 68.
• Total production missiles built: 108. Total deployed missiles: 54.

Titan 1 First Stage:

• Gross mass: 76,203 kg
• Empty mass: 4,000 kg
• Thrust (vac): 1,467 kN
• Isp (vac): 290 s (2.84 kN·s/kg)
• Isp (sea level): 256 s (2.51 kN·s/kg)
• Burn time: 138 s
• Diameter: 3.1 m
• Span: 3.1 m
• Length: 16.0 m
• Propellants: liquid oxygen (LOX)/kerosene
• Number of engines: Two - Aerojet LR-87-3

Titan 1 Second Stage:

• Gross mass: 28,939 kg
• Empty mass: 1,725 kg
• Thrust (vac):356 kN
• Isp (vac): 308 s (3.02 kN·s/kg)
• Isp (sea level): 210 s (2.06 kN·s/kg)
• Burn time: 225 s
• Diameter: 2.3 m
• Span: 2.3 m
• Length: 9.8 m
• Propellants: liquid oxygen (LOX)/kerosene
• Number of engines: One - Aerojet LR-91-3

[edit] Service history

The number of Titan I missiles in service, by year:

• 1961 - 1
• 1962 - 62
• 1963 - 63
• 1964 - 56

[edit] External links

• Titan 1 ICBM History site
• Titan 1A base environmental studies, USACE- Lincoln, CA
  • Info on "Northern California Triad" of Titan missile bases in Lincoln, CA; Chico, CA and Live Oak, CA (Sutter Buttes)

[edit] Related content

<h3>Designation sequence<h3>

AGM-22 - MIM-23 - RIM-24 - LGM-25 I/LGM-25 II - AIM-26 - UGM-27 - AGM-28
SM-65 - B-66 - GAM-67 - XB-68/SM-68 I/SM-68 II - RB-69 -	XB-70	-	SR-71
	IM-70	-	GAM-71

<h3>Related lists<h3>

• List of military aircraft of the United States
• List of missiles

<h3>See also<h3>

• Titan (rocket family)

pl:Titan I