Adaptation of the Saturn S-II for Ground-Launch Stage 660442

Mission studies have indicated that a launch vehicle pay-load capability void exists between the Saturn IB and Saturn V vehicles. The S-II and S-IVB stages of the Saturn V were investigated to determine the feasibility of utilizing them to satisfy the capability void. To obtain low earth orbital payloads in the range of 75,000-150,000 lb, it is necessary to augment the S-II stage thrust. This paper discusses the application of Minuteman first-stage or Titan III-C type 120 in. strap-onsolid rocket motors to provide the additional thrust to the intermediate vehicle comprised of the S-II and S-IVB. Included is a definition of the candidate vehicle configurations utilizing these solid motors and a definition of the stage modifications. The payload performance and control characteristics of the intermediate vehicles are summarized. The impact of the intermediate vehicle of the total ground systems, including launch from KSC, is reviewed and utilized as the basis for developing cost efficiencies of the various configurations. The results presented in this paper were developed as an element of the company sponsored research of the growth and alternate applications of the Saturn S-II stage.


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