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To meet the demands of increasing payload size and weight, and to fill the large payload gap between the Saturn IB and Saturn V, a number of methods of uprating the Saturn IB have been studied by NASA and Chrysler Corp. of providing increased payload capability is discussed in this paper. Four 120 in. United Technology Center UA-1205 solid propellant motors, originally developed for the Air Force Titan III program, are clustered around the S-IB first stage of the Saturn IB launch vehicle. These four solid propellant motors provide the total thrust for liftoff of the vehicle, with S-IB stage ignition occurring just prior to burnout and separation of the solid propellant motors. The term “Zero Stage” is applied to this added stage.

The uprated Saturn I (Saturn IB) Launch Vehicle is discussed, its mission capability described, and it is shown to be suitable for additional missions requiring increased payload weights falling within the payload gap between the uprated Saturn I and Saturn V launch vehicles. Several attractive methods of providing increased payload together with the various methods of vehicle uprating that have been studied by Chrysler Corporation Space Division and NASA are presented. These methods include propellant substitution, S-IB stage propellant tank extensions, and the addition of strap-on solid propellant rocket motors for thrust augmentation. Additional upper stages are discussed as potential uprating techniques. Combinations of solid rocket motors and additional upper stages are reviewed. The paper concludes with a discussion of the capability of the various uprated configurations.