Browse Items · UAH Archives, Special Collections, and Digital Initiatives

Source credibility and personal influence in three contexts : a study of dyadic communication in a complex aerospace organization.

Abstract to "A thesis submitted to the faculty of Purdue University fo Gary Marshall Richetto in partial fulfillment of the requirements for the degree of Doctor of Philosophy, January 1969".; Handwritten note on front page: Return to Internal Communication, Room 223, 4202.

Meteorites and ballistics.

Technical Report surrounding meteorites and their ballistics.

theeasofimpofthesafproatthemarspaflicen_071107091611.pdf

"The ease (E's) of implementation of the Safety Program at the Marshall Space Flight Center."

Presented at the 19th Annual Federal Safety Conference, National Safety Congress, Chicago, Illinois. A rundown of the new safety protocols, chiefly favoring the letter 'E.'

thedevofaboncombulforsat_090707133327.pdf

"The development of a bonded common bulkhead for Saturn."

A Part of the development of the Saturn S-IV/S-IVB stage the Douglas Aircraft Company has pioneered in the development of the cryogenic common bulkhead. The term common bulkhead is derived from the design function of the bulkhead, which is to separate the two cryogenics, liquid hydrogen and liquid oxygen, in a single tank, thereby shortening the stage and eliminating the necessity for two separate bulkheads and the associated interstage structure. The common bulkhead is structurally adequate to withstand both the thermal and the pressure loads from both the hydrogen and the oxygen tanks, and it has sufficient insulation properties to prevent the liquid hydrogen from freezing the liquid oxygen. Another benefit from the common bulkhead is that it permits a reduction in the total length of the vehicle, thereby reducing the bending moments.

devandutiofcomtesproforcheofspaveh_110907133554.pdf

"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.

telesystforsatus-istagdeve_032107081755.pdf

"Telemetry system for Saturn S-I stage development."

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.

"Some computer applications in Saturn stage checkout."

This paper discusses a number of interesting applications of digital computers in the checkout of individual Saturn stages and in the prelaunch checkout of the complete Saturn vehicle. It discusses the concepts of automation in Saturn checkout, the unique two-computer mode of operation at the launch site and the operations of the high speed data link connecting the two computers. Also discussed are the functions of the computer while propellants are loaded automatically on one of the stages; the functions of the display computer in the newest and largest Saturn display system, and operations and utilization of the Digital Events Evaluator, the main recording device utilized during stage checkout.

"S-IVB Saturn high energy upper stage and its development."

The development of carrier rockets For manned space missions has been one of the major activities in the aerospace field during the past decade. The early space efforts were made possible by the existence of large ballistics missiles. It soon became obvious that the delivery of weapons and the launch of large spacecraft could not be combined into one operational system in an efficient way; therefore, a family of spacecraft boosters had to be created.

"The role of the S-IVB in the Apollo and past Apollo programs."

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.

proincrypumdesforspaapp_031808115456.pdf

"Problems in cryogenic pump design for space application."

Report detailing the problems surrounding cryogenic pump design for space travel and missions.

"The program manager's problem"

Included in "First Annual Logistics Management Symposium," Huntsville, Alabama; Archive copy is a poor photocopy. Describes the stages of rocket-development/launch and the logistical problems with each.

telmesinsreqforsII1andsII2_020408135342.pdf

"Telegraphic message : inspection requirements for S-II-1 and S-II-2 at KSC."

Photocopy of an inspection list requirements for S-II-1 and S-II-2.

"Recoverable S-IB."

The paper deals with the selection of a simple recovery system for the Saturn IB first stage. As an introduction to the discussion on recovery system objectives, a plot of the expected trajectory is presented. This is followed by a statement which lists the necessary steps which must be followed to develop a recovery program.

"Appendix to Chapter II of a Survey of Various Vehicle Systems for the Manned Lunar Landing Mission."

This appendix includes various diagrams of orbital launch vehicles, graphs of propellant and tankweight, returnpayload, and lift-off requirements, velocity requirements for a manned lunar mission, multiple drawings for the Saturn C-3 vehicles, lunar mission payloads, information of vehicle size, and a summary of the Saturn C-3 lunar mission.

"Memorandum, routing slip, and letter by Harold G. Russell, Colonel, USAF, concerning the Business Week article 'North American tries to advance under fire.'"

This document also contains part of the Business Week article "North American tries to advance under fire", (June 3, 1967) pages 154 to 162. The complete article can be found at the UAH Library in microfilm format.; The document has handwritten notes and is a poor photocopy.

theuseofwindsheainthedesiofaerovehi_103107103412.pdf

"The use of wind shears in the design of aerospace vehicles."

Prepared for presentation at the 23rd Meeting of the Structures and Materials Panel, AGARD, October 4-11,1966, ONERA, Paris, France.; ABSTRACT: The relative influence of various wind profile properties and disturbances on launch vehicle flight dynamic response is studied. Particular emphasis is placed on the influence of wind shears and turbulence on dynamic response during the boost phase of the flight. Four hundred and seven individual detailed (Jimsphere) wind profiles are the primary wind inputs for this analysis. Time response of the vehicle to each profile is computed and a statistical evaluation of the results made. Results are obtained for the Saturn V space vehicle and conclusions drawn as to the relative influence of wind shears and turbulence vs the degree of refinement of the dynamic model of the space vehicle.

"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.

dynloaofalauvehduetoinfwin_121307141031.pdf

"Dynamic Loads of a Launch Vehicle Due to Inflight Winds."

Analysis of the stability and dynamic load environment of a launch vehicle resulting from atmospheric disturbances is a very complex problem. To determine the dynamic load environment of the vehicle requires an adequate description of the wind field, vehicle dynamics and control system. The essential of such a study, namely methods of analysis, wind field specification and representative vehicle response parameters for evaluation, are of equal importance. This paper is concerned with the mathematical foundations of the vehicle model and method of analysis.

Technical information Summary Apollo-11 (AS-506) Apollo Saturn V Space Vehicle.

The document's mission summary states "This documet is perpared jointly by the Marshall Sapce Fligh Center Laboratories S&E-ASTR-S, S&E-AERO-P, and S&E-ASTN-ESD. The document presents a brief and concise description of the AS-506 Apollo Saturn Space Vehicle and the AS-506 mission. Where necessary, for clarification, additional related information has been included. It is not intended that this document completely define the Space Vehicle, its sytems or subsystems in detail. The information presented herein by text and sketches, describe launch preparation, ground support activities, and the space vehicle. This information permits the reader to follow the sequence of events beginning a few hours before liftoff to mission completion."

drafinfoworkpaptechhistsaturn_031607103330.pdf

"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.

"Systems applications in orbital launch operations."

The objective is to examine the technical requirements and feasibility of conducting orbital launch operations with systems now in the development phase. In order to maintain realistic constraints on the analysis, the Saturn S-IVB stage has been used as an example of present stage technology. The requirements, procedures and complexity of operations for orbital assembly and launch are discussed. The primary design requirement for orbital assembly and launch operations is increased orbital stay time (from hours to days or weeks).

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.

"Report to the administrator, NASA on the Saturn development plan."

In anticipation of this transfer, the NASA and Department of Defense have established, an interim working agreement that provides for immediate assumption by NASA of responsibilities fortechnical management of the Saturn vehicle development.

"Apollo Logistic Support Systems."

According to an abstract found on the page following the title page, this paper includes "one possible conceptual definition of an early Apollo Logistics Support Systems (ALSS) is presented and various payloads for the system are briefly discussed. " It also discusses the Lunar Mobile Laboratory (MOLAB) and other considerations for a lunar scientific mission.

"Letter to Mr. Kurt R. Stehling."

Letter to Kurt R. Stehling from Julian Scheer answering on behalf of "Mr. Webb," stating that Kurt's "idea" was interesting and is to be given careful consideration.

"Memorandum to Dr. Emme - EH through Mr. Shafter - G from Julian Scheer, Assistant Administrator for Public Affairs, National Aeronautics and Space Administration."

This attached correspondence indicates a great deal of confusion and that a number of people are in the act. The matter before the house is whether we will (Dr. von Braun is asked) to allow Logsdon to have a copy of the Von Braun memo to the Vice President on space goals.

Survey of Automatic Checkout Systems for Saturn V Stages.

The Abstract states "The four checkout systems developed and utilized by the National Aeronautics and Space Administration (NASA) for acceptance checkout of the Saturn V launch vehicle stages and instrument unit are described. The vehicle's characteristics, test policies, equipment design criteria, and operational factors are reviewed. Following a general description of each checkout system, this paper presents a brief definitive description of each major subsystem test station. These test systems are used for post-manufacturing and post-static firing acceptance checkout. The section related to the S-II stage includes several representative flow diagrams and descriptions of automatic tests. To present in detail the large volume of information describing these four checkout systems would require the writing of four papers."

staproforusiuniofmasweiforpresandacc_031207095943.pdf

"Standard procedure for using units of mass, weight, force, pressure and acceleration."

Report No. DT-TM-1-60. ; FORWARD: The field of missiles and rockets deals with quantities of matter at various locations with different accelerations of gravity. The weight of these masses changes with gravity and the measurements of liftoff weight, fuel weight, etc., result in different values, depending on whether mass or weight units are used. Pressure and thrust are independent of the acceleration of gravity, but the instruments for measuring these values are calibrated with standard masses, producing different weight forces and calibration curves at different locations. Most sections of ABMA and other agencies or companies use pounds or kilograms as units of mass, weight or force, and the influences of different accelerations of gravity are often disregarded or treated incorrectly. These discrepancies become increasingly unacceptable with larger missiles and greater distances between operation sites. Therefore, the following Standard Procedure has been prepared to insure consistent and uniform terms and units of mass, weight, force, pressure and acceleration. All sections and individuals concerned are urged to use these units andprocedures. This is signed by Dr. Wernher von Braun, Director Development Operations Division.

"The role of weighing in the development and firing of missile and spaceships."

Speech regarding the importance of developing and upgrading space ships and space technology.

"Automatic Pressure Transducer Calibration System."

The abstract notes, "The development of an automatic pressure transducer calibration system is discussed in this report. Evolution from past practices and systems into an automatic calibration system with computerized data handling is described."

"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.

"Lunar Applications of a Spent S-IVB/IU stage (LASS)."

Support of lunar exploration missions is a major consideration in future space program planning. The spent Saturn v/S-IVB/IU can support both lunar - orbit and lunar -landing operations. This paper investigates lunar applications of the spent stage, and incorporates data generated during Company-funded studies. Investigated here is the feasibility of using a launch vehicle employing standard S-IC and S-I1 boost stages to deliver a modified S-IVB/IU and large discretionary payloads to a lunar orbit (LASSO) and/or the lunar surface (LASS). Operations in Earth orbit and direct-ascent trajectories are examined, and consideration is given to the use of the spent stage as a shelter in a manner similar to the presently planned Earth orbital workshop operations. Both the LASSO and LASS concepts are recommended for consideration in future lunar exploration plans. These concepts are capable of placing a gross wet weight of 101,400 lb in lunar orbit or landing 63,580 lb on the lunar surface respectively. The effective payload capability can be enhanced by proper integration of translunar mission subsystems with the subsystems required for lunar orbit or surface operations. The vehicles can be available within 3 years, with current-technology hardware sufficient for performing the missions described.; Douglas Paper No. 4256.

Browse Items (970 total)