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TITAN III-C Fact Sheet
Written and Edited by Cliff Lethbridge

An improved version of the Titan III-A, the Titan III-C was introduced in 1965. The most striking modification over the Titan III-A was the addition of two huge strap-on solid rocket boosters.

The United Technologies solid rocket boosters were each 85 feet tall and 10 feet wide and were comprised of five individual segments. Each could produce a remarkable 1,174,600-pound thrust. The boosters burned Powered Aluminum/Ammonium Perchlorate solid fuel.

The Aerojet dual chamber first stage engine could produce a total thrust of 532,000 pounds. An Aerojet second stage engine could produce a 101,000-pound thrust. Both engines burned Aerozine 50/Nitrogen Tetroxide liquid fuel.

The Titan III-C Transtage third stage Aerojet engine also burned Aerozine 50/Nitrogen Tetroxide liquid fuel and could produce a thrust of 16,000 pounds.

With the significant performance improvements which resulted from introducing twin solid rocket boosters, the Titan III-C was able to carry a 29,600-pound payload to low-Earth orbit or a 3,600-pound payload to geostationary transfer orbit.

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© Copyright 1998 by Clifford J. Lethbridge