Spaceline - Covering the Past, Present and Future of Cape Canaveral

 

spaceline.org

Contact Spaceline

Spaceline Home/Site Index

Launch Schedules

Spaceline Logo Cape Canaveral Florida

spaceline, inc.

About Spaceline

Spaceline Photo Gallery

Gift Shop


 

Titan I

 

 

TITAN I Fact Sheet
Written and Edited by Cliff Lethbridge

 

Classification: Inter-Continental Ballistic Missile

Length: 98 feet

Diameter: 10 feet

Range: 8,000 miles

 

 

Under Weapons System 107A-2 (WS-107A-2), a development contract for an ICBM surpassing the capabilities of the Atlas was granted to the Martin Company (later Martin Marietta) in October, 1955. The company subsequently built a virgin production facility in Denver, Colorado.

The missile received an initial designation of SM-68. The name "Titan" after the Greek mythological father of Zeus was recommended for SM-68 by Martin Company public relations man Joe Rowland.

A pre-production version of the Titan ICBM was called Titan J, while a version designed to be compatible with launch facilities at Vandenberg Air Force Base, California, became known as Titan V (the letter "V" as opposed to the Roman Numeral "V").

Of course, the version of the missile which was ultimately deployed by the U.S. Air Force carried the name Titan I.

Inertial guidance originally intended for use on the Titan I was transferred to the Atlas program. Instead, a redesigned radio controlled guidance system from Western Electric, Sperry and Remington Rand Univac was employed.

Remington Rand Univac built groundbreaking digital technology computer components for the Titan I guidance system.

First stage propulsion for the Titan I was provided by an Aerojet engine with twin-gimbaled chambers each capable of providing 150,000 pounds of thrust at launch. The first stage engine was fed by liquid oxygen/RP-1 (kerosene) liquid fuel.

The first test launch of a Titan I occurred on February 6, 1959. For this flight, only an operational first stage was employed. A dummy second stage was ballasted with water.

The Titan I second stage was powered by an Aerojet engine which could produce an 80,000-pound thrust. Like the first stage, the Titan I second stage burned liquid oxygen/RP-1 (kerosene) liquid fuel.

The total vehicle could carry a four-megaton warhead which was housed inside an Avco re-entry vehicle.

Operational launch complexes for the Titan I may best be described as huge underground cities. Underground areas were enormously enlarged and included sophisticated radar guidance and power stations. Reaction time to launch a Titan I was about 20 minutes.

Rapid propellant loading systems and a high-speed hoist were employed. Although the Titan I was designed to be lifted out of its silo prior to launch, a test launch from Vandenberg Air Force Base, California on May 3, 1961 demonstrated that in-silo launches were possible.

The Titan I became operational at Lowry Air Force Base, Colorado on April 18, 1962. With a numerical designation of HGM-25A, Titan I deployment was completed in early 1963.

A total of six Strategic Air Command (SAC) Titan I squadrons were activated. Each squadron supported nine missiles, providing SAC with a total fleet of 54.

Two Titan I squadrons were deployed at Lowry Air Force Base, Colorado. The remaining four Titan I squadrons were located at Beale Air Force Base, California, Mountain Home Air Force Base, Idaho, Ellsworth Air Force Base, South Dakota and Larson Air Force Base, Washington.

The Titan I fleet was deactivated by 1966 in the wake of improved ICBM technology. The Titan I was never modified for space flight.


Copyright 2012 Spaceline, Inc.