ATLAS C Fact Sheet
Written and Edited by Cliff Lethbridge

Designed for long-range guidance and nose cone tests, the Atlas C was configured very closely to what would become the operational Atlas ICBM.

It incorporated an improved booster/sustainer engine configuration and carried a recoverable nose cone data capsule, which carried instrumentation that recorded valuable in-flight test data.

The Atlas C carried two Rocketdyne booster engines, each with a thrust of 165,000 pounds. A single Rocketdyne sustainer engine produced a thrust of 57,000 pounds while two Rocketdyne vernier engines produced a thrust of 1,000 pounds each.

All of the engines were fed by liquid oxygen/RP-1 (kerosene) liquid propellant, and all engines were ignited at liftoff.

Like its predecessors, the Atlas C used a semi-inertial guidance system supported by radio commands from ground stations.

Considered a semi-operational training and test vehicle, an Atlas C was first launched from Cape Canaveral on December 23, 1958. The missile's flight data capsule was not recovered, but all other test objectives were met.

An Atlas C carried the first recoverable ablative technology nose cone. During the last Atlas C test on August 24, 1959, the missile's nose cone was recovered following a successful 6,000-mile, full-range flight.

Copyright © 1998 by Spaceline, Inc.