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"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. -
"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. -
"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. -
Saturn AS-501 evaluation bulletin No. 1, November 14, 1967.
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. -
"Saturn V derivatives."
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. -
"Saturn V semi-annual progress report July-December, 1966."
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. -
"The Case for Compatibility."
"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." -
"Practicalities in automated manufacturing checkout."
This paper presents a number of solutions to a number of unanswered questions regarding the Saturn projects. -
"Saturn I flight test evaluation."
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. -
"Space flight projects - today and tomorrow."
NASA symposium on scientific and technical Information. -
"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 . -
"Saturn technical information handbook. Volume III of four volumes : SA-203."
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. -
A Saturn rocket stage is loaded onto a barge on the Tennessee River.
The stage is being transported to the Mississippi Test Facility. -
A Saturn rocket stage is loaded onto a barge on the Tennessee River.
The stage is being transported to the Mississippi Test Facility. -
A Saturn rocket stage is loaded onto a barge on the Tennessee River.
The stage is being transported to the Mississippi Test Facility. -
A Saturn rocket stage is loaded onto a barge on the Tennessee River.
The stage is being transported to the Mississippi Test Facility. -
A Saturn rocket stage is loaded onto a barge on the Tennessee River.
The stage is being transported to the Mississippi Test Facility. -
"Annual progress report :1966-1967."
The Annual Progress Report from July 1st, 1966 through June 30thm 1967. -
"System description for Saturn vehicle (SA-1 through SA-4)."
Missing pages iv, 3, 6 to 8. Photocopy of files containing sections of the project. -
"Saturn system study II."
Study regarding the three-stage carrier vehicle E-1 engines. -
"Preliminary study of an unmanned lunar soft landing vehicle (Scientific Application)."
Report to the National Aeronautics and Space Administration Working Group on Lunar and Planetary Surfaces. -
Apollo 10 press kit.
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. -
"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. -
"Saturn IB news reference."
Images, decriptions, graphics and explanations of the various Saturn rockets. -
"Manned space flight schedules. Vol. III, launch vehicles : book 2, Saturn IB."
OMSF program status review October 1965.; Edition "A". -
"Manned space flight schedules. Vol. III, launch vehicles : book 3, Saturn V."
OMSF Program Status Review October 1965.; Edition "A". -
"APOLLO APPLICATION PROGRAM VEHICLES."
This image depicts various Apollo launch vehicles. -
"skylab 3 SCIENCE & ENGINEERING IN ORBIT" brochure.
This brochure describes the duties and responsibilities of the Skylab 3 crew, including experiments and repairs. -
"SKYLAB WORKING ON A NEW FRONTIER."
This article describes the technical aspects of all of the Skylab missions, with a focus on readability for the public. -
"SL II MC 1/1 Time: 6:32 a.m. CDT, T-01:25:00 GET 5/25/73" - "SL-II MC-11/3 Time: 08:01 A.M. CDT, T-1 minute Get 5/25/73."
This mission commentary depicts the Skylab 1 launch. -
"SL-III MC-1/1 Time: 05:01 CDT 09:10 GMT 7/28/73" - "SL-III MC-10/4 Time:06:08 CDT 09:11:08 GMT 7/8/73."
This mission commentary describes the Skylab 3 launch. -
Apollo 5 press kit.
For release Thursday P.M., January 11, 1968. -
"Manned space flight schedules. Vol. III, launch vehicles : book 2, Saturn IB."
OMSF Program Status Review August 1965.; Edition "A" -
Saturn V history team at the Apollo 10 launch.
Shown left to right: David Christensen, Melvin Kranzberg, Irving B. Holley, Jr., Rudolf Hermann, and Fred Ordway. -
"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.