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"A 'Zero Stage' for the Saturn IB Launch Vehicle."
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. -
"A comparison of four control systems proposed for Saturn V launch vehicles."
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 . -
"A Description of the ST 124-M Inertial Stabilized Platform and its Application to the Saturn V Launch Vehicle."
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. -
"A description of the ST-124M inertial stabilized platform and its application to the Saturn V launch vehicle."
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. -
"A Hybrid Simulation for Dynamic Verification of Saturn Guidance and Control Subsystems."
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. -
"A Practical Approach to the Optimization of the Saturn V Space Vehicle Control System Under Aerodynamic Loads."
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. -
"A Prime Contractor's Reliability Program for Components/Parts for the Douglas S-IVB Stage Project."
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. -
"A real time operating system for the Saturn V launch computer system."
Presentation aimed to encourage a final check on the Saturn V project before its first launch to ensure safety and success. -
"All Digital Simulation of Saturn I, IB, and V: Boost Vehicle and Guidance Control Systems."
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." -
"Analog Simulation of Saturn S-IB Stage Propulsion System Dynamic Characteristics."
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." -
"Annual progress report :1966-1967."
The Annual Progress Report from July 1st, 1966 through June 30thm 1967. -
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"Apollo 4 Pre-Launch Press Conference."
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. -
"Apollo 4 press kit."
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. -
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"Apollo 6 Pre-Launch Press Conference."
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. -
"Apollo 8 Mission (AS-503) : memorandum to A/Acting Administrator from MA/Apollo Program Director."
Memorandum discussing the first manned Saturn V flight, its purpose and when/where the launch will take place. -
"Apollo 9 carries lunar module."
Press release surrounding the Apollo 9 rocket and its crew prior to launch. -
"APOLLO APPLICATION PROGRAM VEHICLES."
This image depicts various Apollo launch vehicles. -
"Apollo/Saturn consolidated instrumentation plan for AS-204/LM-1."
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. -
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"Application of Saturn Systems to Orbit Launch Operations."
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. -
"Approach in Achieving High Reliability for Saturn Class Vehicles."
This paper focuses on an approach for achieving high reliability within the Navigation, Guidance, and Control systems of the Saturn class launch vehicles. -
"AS-203 Technical Information Summary."
"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." -
"Assurance and Measurement of Space Vehicle Alignment."
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. -
"Automatic Saturn V Page Test System."
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." -
"Component Failure Effect on Systems: An Analytical Model".
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. -
"Computer Controlled Power Application for the Saturn Launch Vehicle".
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. -
"Crew Briefing : Instrument Unit Stage Presentation".
Document outlining different slides of a presentation containing numerous organizational charts, diagrams and bullet-list points. -
"Crew Briefing : Instrument Unit Stage Presentation".
Document outlining different slides of a presentation containing numerous organizational charts, diagrams and bullet-list points. -
"Development and Utilization of Computer and Test Programs for Checkout of Space Vehicles."
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. -
"Development of LOX/RP-1 Engines for Saturn/Apollo Launch Vehicles."
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. -
"Development of Separable Connectors for the Saturn S-IV Stage."
The purpose of this paper is to present information, in the area of separable connectors as they pertain to the Saturn S-IV Program. -
"Development of the NASA/Grumman Lunar Module."
Paper regarding the actions and achievement of the Grumman Aerospace Corporation. -
"Development Status for Arc Guidance, Weld Observation Systems, and a Review of Process Control Parameters."
Letter to David L. Christiensen from W. A. Wall, enclosing requested documents. -
"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. -
"First Hundred Seconds."
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. -
"Flight Control Computer for Saturn Space Vehicles."
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. -
"Flight Evaluation of the Command and Communication System Aboard AS-501."
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. -
"Future Projects Office."
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.