Select... For release Thursday P.M., January 11, 1968. "The Case for Compatibility" is a paper by Robert L. Smith, Jr., who worked in Quality and Reliability Assurance Laboratory at George C. Marshall Space Flight Center. The summary states, "Ever since the use of missiles and space launch vehicles began, questions have existed in every program regarding the similarity between upstream (e.g., manufacturing, static firing ) and launch site checkout equipment. Programs have existed which utilized nearly identical equipment for both uses; other programs have existed in which any resemblance of the equipment was probably coincidental. Many factors have entered the final decisions, not the least of which were economic and schedule considerations, and, in some instances, the organizational structure of the developer." "This report outlines, through a series of sketches with accompanying text, the general features of the SA-203 Launch Vehicle and information on launch preparation, the launch facility and mission peculiar experiments." 8 x 10 inch black and white diagram of the Saturn booster engines. 8 x 10 inch black and white diagram of the JII engine and the Saturn IV. 8 x 10 inch black and white diagram of the Saturn II engines. A basic description of the Saturn rockets alongside diagrams for context. A computer system was designed to allow test engineers to progressively employ automation in the checkout of the Uprated Saturn I and Saturn V space vehicle programs and still allow manual control of the checkout process. A two-computer system was selected by National Aeronautics and Space Administration, and the International Business Machines Corporation was chosen to provide the programming engineering necessary to implement these objectives. Space vehicle checkout, prior to launch, may be characterized by controlling, monitoring, and testing the vehicle and its subsystems through the use of ground support equipment (GSE).; IBM Huntsville Library.; Presented at AIAA Conference, XVIIth International Astronautical Congress, Madrid, Spain, October 10-15, 1966 by Edward A. Robin, Manager, Vehicle Test Programming Department. A list of images with detailed descriptions of what they are and their histories. a press release which focuses around the Apollo 9 flight and what role the ST-124-M inertial guidance platform has in it. According to the preface, "This handbook provides KSC management personnel with general information relative to the Apollo-Saturn program. Emphasis is placed on Saturn launch facilities and related support equipment. Saturn vehicle parameters are included for general information. According to the summary found on page 1, this document "presents a brief and concise description of the AS-204/LM-1 Apollo Saturn Space Vehicle." The information within the document allows readers to follow the timeline of the space vehicle's lift-off and journey to space. Aerospace Workshop, University of Hawaii.; Includes references to slides. Article aimed at improving the NASA's ability to complete its projects." Article explores the outer layer of the Saturn S-II along side its benefits and complications. Contains poorly rendered images displaying the process. As this paper is being written, the Saturn I flight test program includes five flights launched between October, 1961 and January, 1964. All five fiights were complete successes, both in achieving all major test missions and in obtaining an unprecedented volume of system performance data for flight analysis. Diagram displaying the internal rooms, pieces and functions of the Saturn V as well as the space-suits of the astronauts. Diagram displaying the launch escape system flight separation in progress. Diagram explaining the process of a lunar mission from liftoff to recovery. Diagram that displays the Saturn V rocket with a page beneath detailing the function of each stage. Document detailing the history of the saturn project between April, 1957 through November, 1962. Document outlining different slides of a presentation containing numerous organizational charts, diagrams and bullet-list points. Douglas Paper No. 4396.; Prepared by Ludwig Roth, Director, Saturn/Apollo Program Extension, Douglas Aircraft Company.; Presented to 16th Annual Conference of the Hermann Oberth Society. Discusses the role of the Apollo rocket after the Apollo program has concluded. Draft of working paper. Typed with handwritten notes (title and author) and pages. Copy in MSFC files noted on first page. Drawn by Don Sprague at the Huntsville Engineering section of Boeing. General O'Connor's presentation to the American Institute of Aeronautics and Astronautics. Centers around saturn space vehicles and makes references to slides. Handwritten names and phone numbers on the first page. Apollo / Saturn Team. Huntsville, Ala. -- NASA Marshall Space Flight Center engineers and scientists will soon begin using a giant Saturn V booster simulator in making various tests of equipment and facilities here and at Michoud Operations, Mississippi Test Operations and Cape Kennedy. Images, decriptions, graphics and explanations of the various Saturn rockets. Includes carbon copy of letter sent to David L. Christensen from Ernst Lange regarding the Part Analysis program. Includes change pages. Contract NAS8-14000. Second revised edition. V66-15610. NASA-CR71607. The introduction notes, "This second revised edition of the Astrionics System Handbook has been developed under the direction and overall supervision of Dr. Rudolf Decher of the Astrionics Systems Engineering Office. This description of the Saturn Astrionics System has been generated by personnel of the Astrionics Laboratory, the staff of the Astrionics Systems Engineering Office, and by personnel of the International Business Machines Corporation working under Contract NAS8- 14000. The handbook will be updated and expanded as it becomes necessary due to changes or refinements in the system concept and hardware. Sections not contained in the first release of this document will be made available within three months." Signed by Ludie G. Richard, Chief, Systems Engineering Office, Astrionics Laboratory. The document is missing pages in the following locations: Chapters 8, 9, 12. Sections 15.2, 15.3, 15.4-1 thru 15.4-16, 15.5-1 thru 15.5-2, 15.5-5 thru 15.5-8. 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. Keynote address at National Aeronautics and Space Administration to the American Rocket Society Conference on Launch Vehicle Structures and Materials. Speech focuses on problems facing the structure of Saturn rockets and other space vehicles. Letter to David L. Christiensen from W. A. Wall, enclosing requested documents. Letter to Wernher von Braun from NASA headquarters regarding Project Highwater and how it was withheld. Lists of different parts of rockets. MA-001-00202H.; MPR-SAT V 66-3.; ABSTRACT: This Saturn V Semi-Annual Progress report describes progress and major achievements from July 1, 1966, through December 31, 1966, in the Saturn V Program. Memo sent to Major General D. M. Jones - NASA/ML. Memorandum discussing the first manned Saturn V flight, its purpose and when/where the launch will take place. Memorandum discussing the priorization of various nlunar landing vehicle projects. Missing pages iv, 3, 6 to 8. Photocopy of files containing sections of the project. NASA symposium on scientific and technical Information. OMSF Program Status Review August 1965.; Edition "A" OMSF program status review October 1965.; Edition "A". Paper given at the AIAA Guidance and Control Conference, August 12-14, 1963, Massachusetts Institute of Technology, Cambridge, Massachusetts. Paper regarding the actions and achievement of the Grumman Aerospace Corporation. 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. Photocopy of an inspection list requirements for S-II-1 and S-II-2. Photograph of a liquid hydrogen rocket engine. Plan for the development and construction of the Saturn C-1 vehicle. Prepared by A. W. Dryden, Quality Engineer, Quality Engineering, Reliability Assurance, Space Systems Center, Douglas Aircraft Company, Inc., Huntington Beach, California. Presented to the 21st Annual Technical Conference for the American Society for Quality Control, Chicago, Illinois. 30 May to 2 June 1967. Prepared by R. L. Parkhill, Section Chief, Saturn S-IVB Reliability Analysis and J. Pauperas JR., Asst. Section Chief, Saturn S-IV Reliability Analysis. Presented to the 4th Annual Seminar on Reliability for Space Vehicles, Los Angeles, California, December 6, 1963. This paper presents techniques originated by Douglas Engineering working under NASA contract NAS7-1. Prepared as a record of the study conducted for the Administrative Engineer on the Department Overhead Account No. 9703.; SUMMARY: In today's complex systems, such as Saturn, many traditional reliability analysis concepts are not acceptable. Because of time and budget restrictions, and the requirement to provide a "man rated" space vehicle, the Douglas Saturn Engineering Reliability Section has developed a new analytical approach; it is called "criticality ranking". It is a "totem pole" of components whose single failure may lead to system loss. "Criticality ranking" is one of the results of an analytical model which encompasses failure effect and reliability prediction. This paper describes this analytical model, discusses some of the techniques and ground rules, and presents examples. A discussion of the application of the results is also included. Prepared by the Lunar Surface Operations Office, Mission Operations Branch, Flight Crew Support Division. Prepared through joint efforts of Personnel Department, Education and Development Branch, Systems Training Unit, Michoud Operations and Engineering Communications Department, Technical Information Branch, Applied Communications Engineering Section, Huntsville Operations.; This publication presents a brief descriptive summary of the Saturn IB vehicle and Chrysler's Corporation's accomplishments in the missiles and space field. The Saturn IB information presented herein is based on current plans for each of the stages. Although there may be design changes from vehicle to vehicle, the basic components, systems, and operating principles will remain similar to previous models. Presentation aimed to encourage a final check on the Saturn V project before its first launch to ensure safety and success. Presentation focusing on empahsising the importance of space programs such as Saturn. Presentation focusing on the history of Saturn V's engineering history and crew. Presentation from Harper, discussing the Saturn Project's then-status, background and plans. Presentation Raymond Pisani to the East-West Bank Chamber of Commerce regarding the Saturn project's roll in space exploration and what contrabutions the East-West Bank can make in that area. Presented are the results of a study comparing four proposed control systems for the first stage flight of Saturn V launch vehicles. The primary basis of comparison is the effect on structural loads, using the bending moments at three stations as load indicators. Two of the systems sense only the vehicle attitude and attitude rate, while the other two systems also sense the lateral acceleration. A yaw plane wind response analysis, including rigid body translation, rigid body rotation, four bending modes, five slosh modes, and a non ideal control system, was performed. The winds used in the study were the Marshall synthetic profile and three selected Jimsphere-measured real wind profiles. Load relief obtained from the addition of accelerometer feedback in the control loop amounted to about 10 percent at maximum bending moment station. In view of predicted structural capabilities of the vehicle, this reduction in loads was not considered sufficient to offset the added complexity and the slight reduction in rigid body stability . Presented at the AIAA/AAS Stepping Stones to Mars Meeting, this paper compares the "payload velocity spectrum for existing and future missions" with Saturn V capabilities. Presented by Olen P. Ely, National Aeronautics and Space Administration, Marshall Space Flight Center, Huntsville, Alabama and R. W. Hockenberger, International Business Machines. Paper that explores the effects of rocket-engine exhaust on radio-signals. Presented on September 21, 1962, at the Eleventh Tagung Der Deutchen Raketen - Gesellschaft, Koblenz, West Germany. Instrumentation sf the Saturn space vehicle represents a considerable effort during the development phase, for proper design evaluatian of this new configuration, its propulsion system, and its structure and control characteristics, an unprecedented number of measurements are required to be carried onboard and to be recovered, These measurements are expected to work properly and to furnish the design engineer with information that is not available by ground testing, Presented to ACHEMA Congress and European Meeting of Chemical Engineering 1967, Frankfurt, Germany, June 21, 1967 by Dr. Eberhard Rees.; Includes slide numbers. Press release detailing how a rocket is the top stage of both the Saturn IB and Saturn V launch vehicles. Press release detailing the firing of the Saturn S-IV in California. Press release exploring the rockets and projects of the Saturn project. Press release surrounding the Apollo 9 rocket and its crew prior to launch. Quarterly progress report for the months of January - March, 1966. Report detailing the progress of the Saturn V's construction, focusing on the individual parts. Report to the National Aeronautics and Space Administration Working Group on Lunar and Planetary Surfaces. Shown left to right: David Christensen, Melvin Kranzberg, Irving B. Holley, Jr., Rudolf Hermann, and Fred Ordway. Speech by H.D. Lowrey, SAE Meeting, Detroit, Michigan. Focuses on the Apollo project, the technology involved and what the goals of the project are. Speech by K.K. Dannenberg at American Society of Civil Engineers, Huntsville, November 2.; Projectionist's copy (photocopy) - slide numbers are included. Speech containing information regarding Crystler's role in the Saturn Project as contracted builders of the stages of three space vehicles. Speech to be presented by C. L. Bradshaw, Deputy Director, Computation Division at Supervisor's Club, Knoxville Utilities Board. Speech praising the progress of space-based technologies and advancements. Study regarding the three-stage carrier vehicle E-1 engines. The "Saturn Technical Information Handbook" provides up-to-date reference material to the Launch Operations Center personnel. This material shows the assembly and operation of the Saturn Vehicle components for systems analysis.; Volume II is available on the NASA Technical Reports Server (NTRS) as a PDF. The abstract notes, "This paper describes the Automatic Saturn V Page Test System. The system is used to evaluate microminiature Unit Logic Device (ULD) circuits. A page is an assembly consisting of a magnesium- lithium frame, an input-output connector, test points, and multilateral printed circuit boards that interconnect the IUDs into logic circuits. The test system automatically performs tests for shorted voltages and shorted diodes, static logic function, and pulse function." The actuation system for the Saturn V S-IC stage is described and compared to the Saturn I system. The use of mechanical feedback actuators that result in a significant increase in system reliability and the damping of load resonance is discussed. The unprecedented component sizes and system requirements are cited. The Annual Progress Report from July 1st, 1966 through June 30thm 1967. 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. The chart includes diagrams, mission statistics, crew, and notes. There is an additional copy in the David Christensen Collection. The concept on Saturn V was to "budget" an amount for the dynamic portion of the wind load as a factor on the steady state drag. Wind tunnel tests paralleled the development and fabrication phases. The results indicated that the system was unable to withstand the design winds; thus, a decision was made to implement a viscous damper "fix" on the facility vehicle at the Kennedy Space Center. Damping tests in the Vertical Assembly Building (VAB) will have been completed and response tests on the pad will be in progress at the time of this symposium. This paper will present the history and status of this program to date. The development of liquid rocket engines follow similar patterns regardless of engine size. During the development of the H-1 and F-1 engines, many problems were encountered. Methods of solving the combustion instability problem are discussed. A description is given of the major components of each engine, outlining their unique features. The requirements for an insulation cocoon are discussed. Problems associated with materials substitution are provided; also highlighted is the fact that problems occur after engine deliveries and require continued development support. Safety features incorporated on the engines are mentioned. Solution to problems encountered in flight are discussed. Upratings of both engines systems are presented graphically.; On the NASA Technical Reports Server (NTRS) unclassified. Can also be found on AIAA. The development of liquid rocket engines follow similar patterns regardless of engine size. During the development of the H-1 and F-1 engines, may problems were encountered. Mehtods of solving the combustion instability problem are discussed.; AIAA 4th Propulsion Joint Specialist Conference, Cleveland, Ohio, June 10-14, 1968.; Also available on NASA Technical Reports Server (NTRS) as unclassified. Can be ordered. Also on AIAA. The document is a booklet created as part of the NASA/Chrysler Corporation Space Division manned flight awareness program. It discusses Chrysler's role in manufacturing and testing the Saturn and includes photographs and diagrams of Saturn stages, operations at Michoud, testing, and future missions. The section headings included in this booklet are "Chrysler and the Saturn," "Saturn at Michoud," "The Voyage of Saturn," "Saturn Firings," and "Saturn's Missions." The findings herein are the results of the combined evaluation efforts of the various Laboratories of Research and Development Operations at MFSC, The Boeing Company, North American Rockwell/Space Division, Douglas Aircraft Company, International Business Machines, and Rocketdyne. The first test of the command and communications system, a unified frequency S-band system, aboard AS-501 was successful. Compatibility of this system with the MSFN/USB sites was established. The onboard transponder and antenna system including antenna switching performed as predicted. The command performance was excellent with 5747 valid commands received onboard out of 5748 commands transmitted. Data reduction problems prevented a complete analysis of the tracking data. Telemetry system performance was satisfactory with a measured bit-error-rate of 4 x10-5 while over the Ascension Island station. This flight provided valuable data which can be used to define vehicle to-ground-station interfaces, to establish attitude constraints during translunar injection, and to improve operational procedures. One more test as successful as the AS-501 test would qualify the system as operational.; May 3,1968. The flight control computer for Saturn receives attitude signals from the stable platform, rate signals from rate gyros or lead networks, and angle-of-attack information from body-fixed accelerometers or other sensors. The flrst flight test of the Apollo/Saturn V space vehicle is scheduled for launch from the Natlonal Aeronautics and Space Administration's John F, Kennedy Space Center, Fla., no earlier than Nov. 7. The mission is designated Apollo 4. The functions, authority, management relationships, and responsibilities of the Launch Vehicle Ground Support Equipment Project Office are described. Functions and examples of non-stage procured Launch Vehicle Ground Support Equipment (LVGSE) are described and illustrated. The history of man might be considered as an ever increasing quantity and quality of measurements. Measurements related to space have been made by early astronomers, modern astronomers, and now by aerospace technologists. The manned lunar landing, a major national goal, has given us the means to measure in space. The space vehicle development itself has made heavy demands on instrumentation; this is discussed in some detail in this paper. The advantages of the International System of Units are mentioned. Some examples are used to illustrate the future of space measurement. The hydraulic systems for the two-stage block II Saturn I vehicle are described with the evolution of their development. 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. The introduction notes, "The Saturn V launch vehicle is being developed by the National Aeronautics and Space Administration's George C. Marshall Space Flight Center for Project Apollo; Saturn I and Saturn IB vehicles are providing the early testing and support for Project Apollo. The nerve center of the Saturn is its guidance and control system. An airborne digital computer provides the link which closes both the guidance and control loops,making verification of the flight computer program of vital importance. During a powered flight this onboard digital computer program can be divided into four major parts:a) guidance, including navigation, b) control, c) vehicle sequencing, and d) computer telemetry." 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. The pamphlet uses a cartoon character named "D. B. Noyes" to explain to the public "the nature and effects of the noise which Saturn makes during static firing tests." The press conference was given at Cape Royal News Center in Cocoa Beach, Florida, on Wednesday, April 3, 1968, at 3:30 PM. Participants: William C. Schneider, Apollo Mission Director, NASA; George M. Low, Apollo Spacecraft Manager, NASA; Clifford Charlesworth, Apollo 6 Flight Director, Manned Spacecraft Center, NASA; Dr. Arthur Rudolph, Saturn V Program Office, Marshall Space Flight Center, NASA; Rocco A. Petrone, Apollo 6 Launch Director, Kennedy Space Center, NASA; Col. Royce Olson, USAF, Director DOD Manned Spaceflight Support Office, Patrick AFB; Chris Kraft, Director of Flight Operations, Manned Spacecraft Center. The press kit includes documentation on the Command and Service Module, Lunar Module, Saturn V launch vehicle, astronauts, and mission descriptions. Release No. 69-68. The primary considerations in the design and development of a recovery system applicable to present expendable first stage launch vehicles are discussed. The general requirements that define the essential characteristics of a feasible recovery system are derived from three critical phases during flight. The degree of criticalness is primarily influenced by the conditions at stage cutoff and separation. The three critical phses of flight are broken down into the following: (1) conditions and requirements between stage separation to re-entry; (2) re-entry; and (3) terminal descent and landing. The program includes "Marshall Center Highlights" from the Center's first year, a message from director Wernher von Braun, a photograph of the Space Queen and Princesses, and a guide to the Center's buildings. The purpose of the Saturn V Specification Cross Reference Index is to Supplement CM-004-001-2H, the Saturn V Specification Index. It is intended to provide a convenient means of finding the specifications by specification number which is cross referenced to Specification Matrix Number and contract end item number. More complete information on specifications including preparation, approval, and contractual status as well as all effective Specification Change Notices (SCN's) can be obtained from CM-004-001-2H, the Saturn V Specification Index which contains the master listing of the same specifications arranged in logical management and functional groupings and listed in Specification Matrix number order. More complete information on hardware can be obtained from various Saturn V Configuration Accounting Indices which list items by in contract end item (CEI) number order.; This document supplements the Saturn V specification index CM -004-001-2H of the same issued date. The purpose of the'saturn V Specification Index is to provide the official detailed record of all specifications and specification changes required for configuration management of the Saturn V Program and to report specification submittal and approval status. The purpose of this brochure is to give interested readers, outside as well as within the agencies of the U.S. Government, information on the mission and activities of the Future Projects Office, George C. Marshall Space. The purpose of this document is to define the flight sequence events, time bases, stage switch selector channel assignments, LVDA Discrete Outputs, Inputs and Interrupts for the Saturn SA-507 & Subs vehicles. Special requirements and restrictions defined in this document will be imposed on the Marshall Space Flight Center and its contractors as applicable, to insure the proper functioning of the equipment in the various stages for required vehicle timing and sequencing to occur as outlined in this Interface Control Document (ICD). The purpose of this paper is to present information, in the area of separable connectors as they pertain to the Saturn S-IV Program. The purpose of this report is to present the shipping and recovery procedures for the Saturn booster. The report covers June 30, 1967 through June 27, 1968: Contract NAS8-5608, Schedules 1 and 1A, July 27, 1968. Prepared by J. P. Delaloye, Management Reporting and Analysis; Supervised by D. G. Valentine, Management Reporting and Analysis; Approved by R. F. Terry, Program Reports; D. H. Creim, Michoud, Program Planning and Reporting Manager; E. K. Cooper, S-IC Program Executive. The S-II is the second stage of NASA's Apollo moon-landing rocket - the giant Saturn V. The most powerful hydrogen-fueled booster under production, the S-II is destined for Apollo manned lunar missions and will help power three Americans to the moon. The S-II is being developed and manufactured at Seal Beach, Calif., by North American's Space and Information Systems Division, Downey, Calif., under the technical direction of NASA's Marshall Space Flight Center, Huntsville, Ala. The Saturn C-1 space vehicle system is being developed by government agencies at industrial firms under the direction of the National Aeronotics and Space Division The Saturn S-IVB stage has a requirement for orbiting around the earth for up to 4.5 hours with approximately 60 percent of its initial propellant remaining at the end of the coast (prior to restart) . Extensive analyses must be performed to insure that this requirement is met. Both the maximum and minimum heat transfer rates are important because the maximum rates affect the hydrogen boiloff losses and thus the initial propellant loading requirements. The minimum rates are important because the boil off gases are used to maintain a minimum axial thrust level by venting the gases continuously through aft facing nozzles. This provides for a settling of the propellant throughout the orbital coast and alleviates the need for periodically venting the tank under zero gravity. The stage is being transported to the Mississippi Test Facility. The stage is being transported to the Mississippi Test Facility. The summary notes, "In 1960, research work was begun to develop new guidance concepts for the Saturn space vehicles. [...] This paper presents the basics of the Iterative Guidance Law developed for Saturn launch vehicles to meet these new requirements of space age guidance. The development of the Iterative Guidance Law and the results and ideas presented in this paper are due primarily to Mr. Helmut J. Horn and his associates in the Dynamics Analysis and Flight Mechanics Division of the Aero-Astrodynamics Laboratory." Marked "Research Review, OK" in the upper right corner of the first page. The document includes corrections and additions to the text in red pencil. The telemetry system used on the Saturn S-I stage for the transmission of vehicle test data is described. Multiplex and modulationtechniques such as PAM/FM/FM, SS/FM and PGM are used in the system. The diverse data requirements for developing the eight-engineliquid-fueled stage necessitated the use of a combination of severalmodulation techniques to efficiently handle the data. A cursory comparisonis made of the merits of each technique. Physical and electricalrequirements and characteristics of the system are outlined. 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. This artist's rendering of the RL10-powered Saturn S-IV stage is depicted as heading toward deep space after separation from the booster. The drawing is accompanied with a brief description of the Saturn S-IV. This booklet has been prepared to provide a quick reference to Saturn V stage peculiar ground support equipment. It consists of visual presentations and a brief description of each major component. It is intended to quickly familiarize concerned elements with the over-all MSFC launch vehicle ground support equipment and is not intended for design usage. The booklet has been prepared in five sections. Section I contains the introductory material and a description of the Saturn V mobile launcher (ML). Section II contains information on the umbilical equipment. Section III contains information on the servicing equipment, both fixed and mobile. Section IV contains information on the access equipment. Section V contains information on the handling and auxiliary equipment. This brochure provides some basic, general information about the lnstrument Unit, a very important part of the Saturn IB and Saturn V launch vehicles. These launch vehicles are being developed primarily for the Apollo program for manned lunar exploration but will also be used for future space missions. This copy has handwritten notes that change the title to read, "Analog Simulation of Uprated Saturn I Stage Propulsion System Dynamic Characteristics." The abstract notes, "The purpose of this paper is to present the techniques and logic employed in the development of an analog computer model to simulate Saturn IV first stage propulsion system dynamic characteristics. Restraints, problem areas, and major assumptions are included." This document contains a transcription of the pre-launch press conference for Apollo 4. It includes the questions asked and answers given by participants Dr. Robert C. Seamans, Dr. George E. Mueller, Major General Samuel C. Phillips, Dr. Kurt H. Debus, and Dr. Wernher von Braun. This document contains copies of management charts maintained in the Managerial Data Center of the executive Staff on the Saturn V project. To facilitate use of this document, all Saturn V classified data has been removed and will be published in Volume XI. A list of these charts are shown on the "Table of Contents". Information on other MSFC activities will be published in separate volumes as indicated on the "Schedule for Publication of Data Bank Charts" contained in this volume. This memorandum outlines, through a series of sketches with accompanying text, the general features of the sixth SATURN I launch vehicle. The sketches are devoted primarily to the launch vehicle but also presents limited information on the spacecraft, the launch facility and launch preparations. The information presented in this summary was compiled through the efforts of R&DO personnel from P&VE, AERO and ASTR. This message for the Apollo Program Director contains a report of the Apollo launch vehicles, problem that occurred, and actions required. The photocopy is difficult to read. This paper desciibes an evolutionary family concept of !h turn V derivative launch vehicle systems, discusses their performance capabilities, and outlines their ability to perform orbital and hlgh-energy missions at minimum total program cost. This paper describes a real-time digital computer program that controls the application of electrical power to the S-IVB stage of the Saturn vehicle at Cape Kennedy, Florida. Douglas Aircraft Company, the S-IVB stage manufacturer, provided NASA with the program requirements relative to the energizing sequence, voltage and current measurement tolerances, and vehicle system operational tests. International Business Machines Corporation provided NASA with the computer program to satisfy the task requirements. The program conjoined the components of the Electrical Support Equipment (two RCA 110A computers and control and instrumentation devices) into a closed loop system. The supporting operating system program by IBM is described. This paper focuses on an approach for achieving high reliability within the Navigation, Guidance, and Control systems of the Saturn class launch vehicles. This paper identifies the methods and equipment through which automation is becoming a major factor in testing and launching Saturn IB space vehicles. The merits of a digital guidance computer and its impact in extending automated checkout are stressed; also a logical basis is established for computer and manual test control. Hardware and software elements of the automated system are described, and details pertaining to reliability are emphasized. A concluding appraisal suggests that automation will play an expanding role in future test and launch operations. This paper includes the equations for the bending moment of a launch vehicle with the effects of bending and sloshing dynamics. It also includes a comparison between the bending moment response envelope of the measure winds and the bending moment response of the MSFC synthetic wind profile. This paper presents a discussion of a hybrid simulation used to dynamically verify the Saturn Guidance and Control subsystems. First, the Saturn vehicle is briefly described to provide background information. The Instrument Unit (IU) is considered in more detail to give a proper setting for the Guidance and Flight Control (G and FC) discussion that follows. After a brief description of the actual G and FC System operation, simulation models of the G and FC components are considered in detail. This is followed by a discussion of the model assignment to a particular computer (digital or analog) and justification for making that assignment. Finally, results of the AS-204/LM1 hybrid simulation studies are briefly considered with mention of the actual flight data. This paper presents a number of solutions to a number of unanswered questions regarding the Saturn projects. This paper presents representative examples of vibration and acoustic data from flights of the Saturn V launch vehicle and static firings of Saturn V launch vehicle stages. The purpose of the paper is to provide vibration and acoustic environment characteristics which are pertinent to the design of launch vehicles This paper, presented at the fifth annual Reliability and Maintainability Conference in New York City, contains a "prime contractor's reliability program for components/parts for the Douglas S-IVB stage project." These parts include special flight critical items and their complementary reliability engineering program plan is outlined in this paper. This report determines the maximum and minimum solar and terrestrial thermal energy incident and absorbed by Saturn IB/V vehicles in earth orbit and translunar travel. The influence' of this external energy on the Instrument Unit Thermal Conditioning System performance, and consequently its adequacy to maintain the electronic packages at acceptable temperature limits is ascertained. Conclusions are: a) Methanol/water coolant temperature will deviate from 111 specifications only during translunar cold flights. However, adequate thermal conditioning of the electronic equipment would still be maintained. b) Instrument Unit missions exceeding 6 1/2 hours, or electronic packages heat dissipation magnitudes lower than 3 kw or higher than 8.5 kw, should be reviewed to ascertain thermal compatibility. This report is a description of the ST-124M inertial stabilized platform system and its application to the Saturn V launch vehicle. It is a summary report providing the system concept, and not a theoretical presentation. Mathematical equations were included only where necessary to describe the equipment; however, the detailed derivations supporting these equations were not presented since this was not the theme of the paper. This report is a description of the ST124-M inertial stabilized platform system and its application to the Saturn V launch vehicle. It is a summary report providing the system concept and not a theoretical presentation. Mathematical equations were included only where necessary to describe the equipment; however, the detail derivations supporting these equations were not presented since this was not the theme of the paper. This report is the consolidation of D5-11994, "Quarterly Technical Progress Report," for the fourth fiscal quarter and the fiscal year 1966 Annual Progress Report and places special emphasis on activities on the fourth fiscal quarter. This report represents the consolidated instrumentation plan for employing optical and electronic data acquisition systems to monitor the performance and trajectory of the Apollo/Saturn 1B vehicle, AS-2 04/LM-1, during powered flight. Telemetry and electronic tracking equipment on board the vehicle, and data acquisition systems monitoring the flight are discussed. Flight safety instrumentation and vehicle data transmission are described, and geophysical information is provided. This plan reflects the general instrumentation coverage requirements set forth in the NASA Program Support Requirements Document (PSRD) for Apollo/Saturn 16, and the commitments of Eastern Test Range (ETR) Operations Directive (OD) No. 4206,dated 15 August 1967. This plan is not intended to conflict with or to supersede either document. The information presented in this document reflects planning concepts developed prior to October 1, 1967. This Saturn V Semi-Annual Progress Report describes progress and major achievements from July 1, 1967 in the Saturn V Program. This security classification guide is a compilation of previous individual classification assignments. Consideration of international affairs, the use and development of advanced technological information, and requirements of flight safety have influenced these assignments. This updated edition of the Astrionics System Handbook instructs, "The enclosed pages change, delete, or supplement the information in the Astrionics System Handbook (1 August 1965). Insert these pages and destroy the pages they replace." 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 burn-out and separation of the solid propellant motors. The term "Zero Stage" is applied to this added stage. Transcription of a confrence aiming to propose ideas for new rocket designs. Includes references to slides. Transcription of a presentation from Wernher von Braun discussing the roles of the space vehicles in the Apollo project. Very poor photocopy. Memorandum requesting additional information regarding a file attached to this one. With the advent of the first large space vehicle, the SATURN, the ground support equipment and launch facility designer is faced with the necessity of conceiving and building an unprecedented launch system concurrent with the vehicle development. The paper intends to present a comprehensive picture of the problems involved and how they are solved. It follows the SATURN through the various modes of operation such as transportation over land and water, checkout, handling and erection, propellant loading, and describes the facilities at the launch site.
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