Browse Items (165 total)

• 

  "Design Concepts of Ground DDAS in Saturn 1B/V ESE."

  In the Saturn IB/V programs the sheer quantity of data required for computer processing and ESE display makes it necessary to provide an efficient data acquisition system. For much of the data originating in the launcher this requirement is satisfied by the Ground Digital Data Acquisition System (DDAS). This paper provides a technical description of the Ground DDAS with emphasis placed on the unique design concepts of this telemetry system.
• 

  "Saturn Vehicle Cryogenic Programs."

  Paper from the 1965 Cryogenic Engineering Conference at Rice University, Houston, Texas, paper K-4. The abstract states, "This paper covers the cryogenic propellant and gaseous application to the George C. Marshall Space Flight Center Saturn Programs. Emphasis is placed on the overall application and the resultant logistic considerations. The planning of facilities, storage, and transportation required to ensure an adequate supply of cryogenic fluids when needed is traced from the engine and stage requirements. The entire cycle of technical requirements, estimating the quantities required from production and management of the program is developed, spacecraft application and other trends that affect cryogenic production are reviewed."
• 

  "Effects of High-Pressure Hydrogen on Steels."

  Hydrogen embrittlement of steels is hardly a new subject, but the effects of high-pressure hydrogen have been treated in detail only more recently and to a much more limited extent. Thus, most investigations of hydrogen embrittlement have been concerned with hydrogen in metals, while for the high-pressure hydrogen problem, we are more concerned with metals in(in contact with) hydrogen. I believe there is a difference and, certainly,different mechanisms of embrittlement are at least possible.; Presented at the Central Florid Section, American Welding Society, Orlando, Florida, 14 November 1967 and North Alabama Chapter, American Society for Metals, Huntsville, Alabama, 16 November 1967.
• 

  "Dynamic Environments of the S-IV and S-IVB Saturn Vehicles."

  The vibration and acoustic environments of the S-IV and S-IVB Stages of the Saturn vehicle are summarized. A brief review of techniques used to predict the dynamic environments of the S-IV and S-IVB vehicles is presented. This review includes discussions on the prediction of rocket exhaust noise, boundary layer noise, sinusoidal vibrations, and random vibrations for the S-IV and S-IVB vehicles. In addition, sine-random vibration conversions are given.
• 

  "Technical History of Saturn."

  Draft of working paper. Typed with handwritten notes (title and author) and pages. Copy in MSFC files noted on first page.
• 

  "Digital Transducers."

  This paper outlines the major advantages of digital transducers and describes the principles and features (1) direct digital transducers, (2) indirect digital transducers, (3) quasi-digital transducers, and (4) A to D transducers.
• 

  "Digest of FY-64 Funded Advanced Studies: August 1966."

  This paper outlines the major advantages of digital transducers and describes the principles and features (1) direct digital transducers, (2) indirect digital transducers, (3) quasi-digital transducers, and (4) A to D transducers. The mutual effect of transducers and systems will be discussed briefly, and some trends of transducer research and development will be presented.
• 

  "Fabricating the Saturn S-IC Booster."

  AIAA Second Annual Meeting, San Francisco, California. Discusses the fabrication process of the Saturn S-IC booster.
• 

  "Extensions of Saturn."

  This paper discusses the possible applications of Saturn vehicles to future space exploration. Potential missions utilizing Apollo derived hardware are examined. Research, development, and operations in earth orbit as well as lunar exploration, unmanned and manned interplanetary exploration are reviewed. These hypothetical missions are discussed in the context of the present and potential capability of three configurations of the Saturn vehicle; an uprated Saturn I, a three-stage Saturn V and a four-stage Saturn V. NOTE: Work presented herein was conducted by the Douglas Missiles and Space Systems Division under company-sponsored research and development funds. Therefore, the concepts and objectives described within this paper reflect the opinions of the authors and do not necessarily constitute endorsement by NASA, the Air Force, or any other U.S. Government organization. The nominal performance numbers presented are typical of the current configurations and possible future vehicle configurations.
• 

  "Engineering Safety Into Missile-Space Systems."

  Safety Engineering, as applied to complex missile and space systems, has developed a new methodology referred to as "System Safety Engineering." The requirement for a comprehensive approach to safety which is included as a contractually covered adjunct to the design, development, and operational phases of a systems life cycle has become apparent from costly missile mishap experience. The general concepts and accomplishments of this new engineering discipline are described along with possible beneficial relationships with Reliability and other recognized organizational elements engaged in safety related activities.
• 

  "History of MSFC Reliability Philosophy."

  Paper given to North East Chapter , Mississippi Society of Professional Engineers. Essay discussing the history of the MSFC Reliability Philosophy.
• 

  "High Energy Missions for Saturn."

  Presented to Society of Automotive Engineers, Advanced Launch Vehicle & Propulsion Systems. When the Apollo lunar landing project is complete, the Saturn and Apollo hardware will only have begun to realize their ultimate potential for space exploration. The immense reserve of Apollo technology, facilities, and booster capability can then be directed to the achievement of national goals which lie far beyond the initial lunar landing. In achieving the Apollo lunar objectives, large investments will have been made in launch facilities, tracking systems, propulsion techniques, reentry systems, lunar landing systems and rendezvous technologies. Although developnent in these specialized areas has been tailored to the needs of Apollo, numerous studies by NASA and industry have demonstrated the feasibility of using the spacecraft, launch vehicles, and operating techniques for missions far more complex than lunar landings. Amortization of this hardware will prove cost-effective for missions of more sophisticated applications.
• 

  "Helium Utilization in the Apollo/Saturn V Vehicle."

  Helium is used extensively throughout the Apollo/Saturn V space vehicle for a number of applications. The welding use is not discussed since it is a special topic. In the first stage (S-IC), helium is used for liquid oxygen tank pressurization during vehicle checkout and launch.
• 

  "Government Grants & Contracts."

  The Army medical contract, grant, and research interest in the bio-science area.
• 

  "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.
• 

  "Flight Software Development Laboratory."

  A man-in-the-loop computer facility has been created using a digital computer, display terminal,and space vehicle flight computer to enable programmers to check out flight programs in a simulated space flight environment. The simulation requires a real time multi-programmed environment, which is supplied by a control system capable of scheduling programs on 32 levels of priority interrupt as well as answering demands for service at the display terminal. A special interface device permits visibility and control of the flight program as it executes in the flight computer. On-line inputs from the programmer at the display terminal and outputs from data collection and reduction routines to the display screen are executed in real time. The Flight Software Development Laboratory has proved to be very useful in reducing program preparation time and increasing flight program confidence.
• 

  "Instrumentation Programming for Computer Controlled Digital Data Processing."

  A number of considerations are necessary in instrumentation programming, many of which are either not applicable or applicable to a lesser degree in other types of programming. This paper discusses these problems in general terms and illustrates how they have been dealt with specifically. The latter is done by describing the programming and operation of a data reduction system.
• 

  "The Influence of Apollo/Saturn V Launch Operations on Lunar Site Selection: Case 330."

  This paper presents some relationships between Apollo/Saturn V launch operations and multiple lunar landing sites, including the means by which site selection could facilitate launch operations.
• 

  "Improving the Uprated Saturn I."

  This paper discusses five improved versions of the Uprated Saturn I that were studied by the Chrysler Corporation Space Division, supported by the Douglas Aircraft Corporation.
• 

  "Manned Launch Vehicle Development."

  Includes handwritten notes. Includes references to slides. Essay remarking on how space vehicles will interact on the moon's surface.
• 

  "Man, Machine, and Automatic Test Operations."

  Essay detailing the relationship between men and machines."
• 

  "Liquid Rocket Propellant Compatibility Testing."

  Material-propellant compatibility as related to liquid rocket propulsion system design criteria is discussed and applicable test methods to derive usable design data are presented. Test methods, with emphasis on metallic materials, are discussed and the shortcomings of a number of these test methods are pointed out. These tests include static immersion tests, stress-corrosion tests, flow tests, impact tests, and tests to determine the effect of cracks and notches in metals on compatibility. A general outline for the evaluation of metallic and nonmetallic materials with respect to propellant compatibility is presented.
• 

  "Liquid Rocket Engines."

  This paper presents a discussion on liquid propellant rocket engines. The first part contains a discussion on liquid propellants, including a description of various propellant types such as cryogenic, storable,bipropellant, and monopropellant. This part also points out desirable physical properties and includes a section on performance outlining the methods by which performance is calculated and shows performance for various liquid rocket propellant combinations.
• 

  "Manufacturing welding control by E. R. Seay, Group Engineer, Lockheed-Georgia Company."

  Paper given at the American Ordnance Association Welding Section Panel. Focuses on the process of welding and development programs.
• 

  "Manufacturing history - LM-5."

  Essay that focuses on the achievements of the Grumman Aerospace Corporation.
• 

  "Manufacturing problems with printed circuit boards and how to avoid them."

  To be presented at the NASA / Rocketdyne Manufacturing Technology Review. Focuses on how best to avoid printed circuit boards.
• 

  "Management problems faced in making future manned space exploration decisions."

  This paper presents in synoptic form, an analysis of the management problems being faced in making fuhlre manned spaceflight decisions. It is an attempt to view the manned space program in total perspective - its relationship to other scientific research, other national programs, the role of Congress, the President's role, industry's role, and then show their relative influence and impact on decisior, making for the Post-Apollo period.
• 

  "Manned Lunar Landing via Rendezvous."

  Paper to be presented at the IAS National Meeting on Manned Space Flight. Focuses on operations leading to injection of the space craft into the lunar transfer trajectory.
• 

  "Minimax control of large launch boosters."

  Keith D. Graham is principal mathematician, Systems and Research Center, Honeywell, Inc., 2345 Walnut Street, St. Paul, Minnesota.; Work done under NASA contract NAS 8-11206 from the George C. Marshall Space Flight Center.; ABSTRACT: A method of specifying the gains of a linear controller for a large launch booster using a new application of optimal control theory is described in this paper. Results for a specific example are included. An important control requirement is to maintain cost variables (such as bending moment, engine gimbal deflection, and lateral deviation from desired trajectory) within specified limits in the presence of load disturbances. This requirement is met by using a performance index which depends explicitly on maximum achievable values of the cost variables in a finite time interval.
• 

  "MSC/Apollo program management"

  The purpose of this document is to describe how the Manned Spacecraft Center is managing its responsibilities in the Apollo Program The organization, procedures, and management philosophy described herein, represent the accumulated knowledge gained from our experience with the Mercury, Gemini, and Apollo Programs. It should be remembered, however, that managing a research and development program of Apollo's size and complexity, is an experimental "R&D" process in itself.
• 

  "Organization of a countdown"

  The Organization of a Countdown was developed over 8 years of missiles and space systems testing at the Douglas Aircraft Company, Sacramento test Center. The experience on which this study was based includes the Thor development and acceptance testing, Titan I second stage engine development testing, Development of liquid hydrogen handling techniques, Saturn S-IV and S-IVB development and acceptance testing. The intent of this paper is to examine the static test countdown organization and discuss the need for a systematic method to organize a countdown.
• 

  "Opportunities for European Payloads on the Saturn Vehicle."

  Prepared for presentation to the Eurospace Conference. In this paper, we will not deal with the first two questions, which must be of interest to every potential experimenter, but only with the last question of vehicle availability.
• 

  "Operational Experiences on the Saturn V S-IVB stage."

  This paper presents a light, but reverent, discussion of some of the Douglas operational experiences on the Saturn V/S-IVB stage. Certain relevant aspects of earlier work on the Thor intermediate range ballistic missile, the Saturn I S-IV stage, and the Uprated Saturn I S-IVB stage are also discussed.; Aeronautic and Space Engineering and Manufacturing Meeting, Los Angeles, Calif., Oct. 7 - 11, 1968.
• 

  "Problems associated with large scale high pressure testing."

  Paper detailing the problems identfified in high pressure testing.
• 

  "Practicalities in automated manufacturing checkout."

  This paper presents a number of solutions to a number of unanswered questions regarding the Saturn projects.
• 

  "Philosophy and practices of reliability as applied in the design of the Saturn Instrumentation System."

  The basic engineering approach used in the Saturn instrumentation system has evolved to provide a highly reliable design for short periods of operation. The airborne measuring and telemetry systems including preflight tests, inspection, documentation, and feedback between the users and designers are discussed. The apparent differences between the practice and theory of reliability are rationalized. Some consideration is given to new problems in designing systems that must operate in hostile environments for long periods. The potential contribution of redundancy as a design concept is discussed.; This paper is concerned with the airborne measuring and telemetry systems; it does not attempt to treat the entire Saturn instrumentation system which consists of tracking devices including optical, radar, and Doppler, plus television, film cameras, and a myriad of instruments connected with factory checkout, ground test, and launch.
• 

  "Reliability engineering program provisions for Space System contractors. Revision 2."

  This document was cited in the Saturn contracts before NPC-250-1 was written. The sense of this document is the backbone of NASA reliability today and has become a generally accepted element of engineering rationale.
• 

  "Reliability assessment of liquid rocket engines."

  Proposed for the 10th National Symposium on Reliability & Quality Control. This paper will deal with various techniques of treatment of such data and associated graphic displays.
• 

  "The reliability of the all-up concept."

  Prepared for George C. Marshall Space Flight Center, Huntsville, Alabama under contract NAS8-11087. Publication No. 294-02-12-440. Special Technical Report No. 13.; INTRODUCTION: The Saturn/Apollo Systems Office at the George C. Marshall Space Flight Center (MSFC) requested ARINC Research Corporation to make a brief study of the reliability aspects of the All-Up concept. Under the requirements of Task 294-02 of Contract NAS8-11087, the study included a comparison between the reliability of the first Saturn V vehicle if All-Up, and its reliability with dummy upper stages.
• 

  "Redundancy employing majority voting for a Saturn servoactuator."

  R-ASTR-NF.; ABSTRACT: The servoactuator was developed to improve the reliability of the Saturn S-IVB thrust vector control system by insuring continued system operation if single point failures occur. The selection of the majority voting technique is discussed. Its simplicity is cited along with the advantages of minimum weight, size, power consumption, and compatibility with existing control electronics. Operational features, design mechanization, and the analysis of test results are covered.