Browse Items (16 total)

• 

  "Contracts for Saturn Upper Stages S-IV and S-V".

  Details contracts for upper stages of Saturn IV and Saturn V and includes illustrative appendixes. Archive copy is a photocopy.
• 

  "Design of the Saturn S-IV Stage Propellant Utilization System."

  Describes the SIV vehicle and its components. Presented at: IRE International Convention.
• 

  Douglas Aircraft news release.

  ABSTRACT: Discusses intensive ground qualification testing program for S-IV stage.
• 

  "Evolutionary Steps in S-IVB Development."

  The injection stage of a multistage launch vehicle must be partially a velocity stage and partially a spacecraft; it must not only boost the payload, it must also perform cooperative mission operations with the payload after orbital insertion. These hybrid requirements result in intrinsic stage versatility which permits consideration of new and challenging missions for the stage which were unanticipated during initial design.; Prepared by T. J. Gordon, Director, Advance Space Stations and Planetary Systems, Space Systems Center, Douglas Aircraft Company, Huntington Beach, California.
• 

  "Fulfilling the Aerospace Engineer's Responsibility for Product Reliability."

  The management techniques described in the paper support the Saturn S-IVB Program which is being conducted for the National Aeronautics and Space Administration, Marshall Space Flight Center.
• 

  "Launch Information: Saturn S-IV and the RL10 Engine."

  The RL10, which powers the National Aeronautics and Space Administration' s Saturn S-IV, is the newest propulsion system to be put to work in advancing our nation's space effortr On November 27, 1963, a pair of RLlO's successfully powered a five-ton Centaur space vehicle in earth orbit in the first flight demonstration of the outer space powerplant which uses high-nenergy liquid hydrogen as fuel. A six-engine cluster of RLlO' s, generating a total of 90, 000 pounds of thrust, powers the Saturn S-IV stage. The 15, 000 pound-thrust engine was designed and developed for NASA's Mar shall Space Flight Center at Pratt & Whitney Aircraft's Florida Research and Development Center, 20 miles northwest of West Palm Beach.
• 

  "Press release 931A : Saturn S-IV first firing."

  Following is text of Douglas release on successful first firing of clustered P&W RL10 engines. Occurred at 11:12 A.M. PDT, August 17. Santa Monica, California.; "Sacramento, Calif,--Man's effort to reach the moon moved nearer reality today with the successful first firing here of the six liquid oxygen-liquid hydrogen fueled engines of the Saturn S-IV.
• 

  "Douglas Aircraft Company Press release."

  Press release covering the static firing of the S-IV rocket for a full seven minutes.
• 

  "Saturn stages S-II : July 7, 1961 : Minutes of the phase II pre-proposal conference for stage S-II procurement."

  Transcription of a confrence aiming to propose ideas for new rocket designs. Includes references to slides.
• 

  "Saturn S-IV cryogenic weigh system. Part II : weigh operations."

  Two basic methods for mass determination are: (1) direct measurement, (2) volume and density determination. Both methods or variations have been used to determine space vehicle propellant mass with varying degrees of success. Stringent propellant loading accuracy requirements of k0.5 percent for the Saturn S-IV Stage have led to the development of a Cryogenic Calibration Weigh System. The method employs accurate electronic force transducers and measuring systems as the standard and experimental weighings have verified achievement of better than the required accuracy.