Technical Paper
Adaptation of the Saturn S-II for Ground-Launch Stage
1966-02-01
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.