Nasa Tech Brief

Total Page：16

File Type：pdf, Size：1020Kb

October 1967 Brief 67-10386 NASA TECH BRIEF "& NASA Tech Briefs are issued to summarize specific innovations derived from the U.S. space program, to encourage their commercial application. Copies are available to the public at 15 cents each from the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151. Continuous Wave Detector Has Wide Frequency Range A small, portable, battery-operated detector, de- Note: signed to monitor electronic equipment used in the Inquries concerning this circuit may be directed to: Saturn II program, indicates the presence of steady Technology Utilization Officer state signals exceeding a predetermined value over a Marshall Space Flight Center wide frequency range. The indication is provided by Huntsville, Alabama 35812 the closure of output relay contacts. The contact Reference: B67-10386 closure occurs and is maintained when the steady state input signal is within the frequency range from Patent status: 400 Hz to 500 MHz and the amplitude of this signal exceeds a preset threshold voltage within the dy- Inquiries about obtaining rights for the commercial namic range of 1.0 millivolt to 3.0 volts rms. The use of this invention may be made to NASA, Code threshold voltage is manually adjustable within the GP, Washington, D.C. 20546. dynamic range of the detector. The frequency range of Source: W. F. Deutsch, the detector is divided into two frequency bands: S. J. Jarminski, and C. E. Wheatley namely, an LF band extending from 400 Hz to 200 of North American Aviation, Inc. kHz and an HF band extending from 200 kHz to under contract to 500 MHz. Band selection is accomplished by a manu- Marshall Space Flight Center ally operated switch. (MFS- 1849) Category 01 This document was prepared under the sponsorship of the National Government assumes any liability resulting from the use of the Aeronautics and Space Administration. Neither the United States information contained in this document, or warrants that such use Government nor any person acting on behalf of the United States will be free from privately owned rights..

Copy Link

Recommended publications

Trade Studies Towards an Australian Indigenous Space Launch System
TRADE STUDIES TOWARDS AN AUSTRALIAN INDIGENOUS SPACE LAUNCH SYSTEM A thesis submitted for the degree of Master of Engineering by Gordon P. Briggs B.Sc. (Hons), M.Sc. (Astron) School of Engineering and Information Technology, University College, University of New South Wales, Australian Defence Force Academy January 2010 Abstract During the project Apollo moon landings of the mid 1970s the United States of America was the pre-eminent space faring nation followed closely by only the USSR. Since that time many other nations have realised the potential of spaceflight not only for immediate financial gain in areas such as communications and earth observation but also in the strategic areas of scientific discovery, industrial development and national prestige. Australia on the other hand has resolutely refused to participate by instituting its own space program. Successive Australian governments have preferred to obtain any required space hardware or services by purchasing off-the-shelf from foreign suppliers. This policy or attitude is a matter of frustration to those sections of the Australian technical community who believe that the nation should be participating in space technology. In particular the provision of an indigenous launch vehicle that would guarantee the nation independent access to the space frontier. It would therefore appear that any launch vehicle development in Australia will be left to non- government organisations to at least define the requirements for such a vehicle and to initiate development of long-lead items for such a project. It is therefore the aim of this thesis to attempt to define some of the requirements for a nascent Australian indigenous launch vehicle system.
[Show full text]
Spacewalk Database
Purchaser First Inscribed First ID Name Purchaser Last Name Name Inscribed Last Name Biographic_Infomation 01558 Beth / Forrest Goodwin Ron & Margo Borrup In 1957 CURTISS S. (ARMY) ARMSTRONG became a member of America's Space Team. His career began with the launch of Explorer I and Apollo programs. His tireless dedication has contributed to America's future. He is truly 00022 Cheryl Ann Armstrong Curtiss S. Armstrong an American Space Pioneer. Science teacher and aerospace educator since 00023 Thomas J. Sarko Thomas J. Sarko 1975. McDonnell Douglas 25 Years, AMF Board of 00024 Lowell Grissom Lowell Grissom Directors Joined KSC in 1962 in the Director's Protocol Office. Responsible for the meticulous details for the arrival, lodging, and banquets for Kings, Queens and other VIP worldwide and their comprehensive tours of KSC with top KSC 00025 Major Jay M. Viehman Jay Merle Viehman Personnel briefing at each poi WWII US Army Air Force 1st Lt. 1943-1946. US Civil Service 1946-1972 Engineer. US Army Ballistic Missile Launch Operations. Redstone, Jupiter, Pershing. 1st Satellite (US), Mercury 1st Flight Saturn, Lunar Landing. Retired 1972 from 00026 Robert F. Heiser Robert F. Heiser NASA John F. Kennedy S Involved in Air Force, NASA, National and Commercial Space Programs since 1959. Commander Air Force Space Division 1983 to 1986. Director Kennedy Space Center - 1986 to 1 Jan 1992. Vice President, Lockheed Martin 00027 Gen. Forrest S. McCartney Forrest S. McCartney Launch Operations. Involved in the operations of the first 41 manned missions. Twenty years with NASA. Ten years 00028 Paul C. Donnelly Paul C.
[Show full text]
National Register of Historic Places Continuation Sheet
NPS Form 10-900-a OMB Approval No. 1024-4018 (8-86) United States Department of the Interior National Park Service National Register of Historic Places Continuation Sheet Section number ——— Page ——— SUPPLEMENTARY LISTING RECORD NRIS Reference Number: 99001639 Date Listed: 01/21/00 Property Name: Launch Complex 39—Pad B County: Brevard State: FL Multiple Name: John F. Kennedy Space Center MPS This property is listed in the National Register of Historic Places in accordance with the attached nomination documentation subject to the following exceptions, exclusions, or amendments, notwithstanding the National Park Service certification included in the nomination documentation. .2000 / Signature ofrhe /Keeper Date of Action Amended Items in Nomination: On Section 5, p. 1 (list of contributing resources), Facility # J7-337 is given as Launch Pad 39A. An amendment is made to the nomination to change the facility number to Launch Pad 39B. This information was confirmed with Kenneth Kumor, NASA FPO. DISTRIBUTION: National Register property file Nominating Authority (without nomination attachment) NFS Form 10-900 0MB No. 10024-0018 (Oct. 1990) RECEIVE 2280 United States Department of the Interior National Park Service DEC _ 7 1999 National Register of Historic Places NAT pee Registration Form ''"'"'•' • i ; \.'X SERVICE v/co This form is for use in nominating or requesting for individual properties:ope~f1 : i e s ""anth a"ni±iit it riots. instructions in How to Complete the National Register of Historic Places Registration Form (National Register Bulletin 16A). Complete each item by Marking "x" in the appropriate box or by entering the information requested. If an item does not apply to the property being documented, enter "N/A" for "not applicable." For functions, architectural classification, materials, and areas of significance, enter only categories and subcategories from the instructions.
[Show full text]
ID Purchaser First Name Purchaser Last Name
ID Purchaser_First_Name Purchaser_Last_Name Inscribed_First_Name Inscribed_Last_Name Biographic_Infomation 2069 Suzy Tabor 07 Pine Crest Chaperones 1313 Lewis Maness Officers & Men of 47th INF 9th Division To the Officers and Men of the 2nd Battalion, 47th Infantry 9thDivision during WW II. This battalion captured, intact '8' GermanV-2 missiles. These missiles were shipped to the United States, where they were studied and thus played a great part in establishing the U.S. Missile Program and NASA. 1147 Eugene Abruzzo Eugene Abruzzo 1328 Carl F. Acker Carl F. Acker Contributor To: Lunar Module Program as Instrumentation and Calibration Engineer for vehicle and ground support equipment. Grumman Aerospace Corp. Cassini Mission to Saturn and Hubble Telescope Programs as Program Quality Assurance Manager for the reaction wheel and electronic assemblies and rate gyro assemblies Allied Signal Corp. 183 Trudy S. Adams Chuck Keith Adams The Space Program had a very special person in Chuck, who served with dedication, skill and the highest of standards as an Engineer with Lockheed. In this way he can always fell he is still a part of this exciting program. 1213 Sammi Adams Mac C. Adams Dr. Mac C. Adams played a major role in solving the problem ballistic missile reentry and helped to develop the theory which determines the type & amount of ablating material needed to protect spacecraft & ballistic missile heat shields. From 1965-1968,Dr. Adams was Associate Administrator, Advanced Research &Technology for the National Aeronautics & Space Administration in Washington D.C Received Exceptional Service Medal in 1968 1941 Your Family Loves You! Richard "Dick" Adams Mr. Richard "Dick" Adams is an extraordinary tour guide and has been since 1969.
[Show full text]
ORBITER Project Apollo Specification 1.0
ORBITER Project Apollo Specification 1.0 Robert Conley [email protected] http://www.alltel.net/~estar/orbiter.html Special Thanks to Dr. Martin Schweiger who made it all possible and fun http://www.orbitersim.com March 14th 2002 ORBITER.................................................................................................................. 1 Project Apollo Specification 1.0 ............................................................................ 1 1. INTRODUCTION ............................................................................................ 2 2. OVERVIEW...................................................................................................... 2 3. SCENARIOS.................................................................................................... 2 4. BREAKDOWNS .............................................................................................. 2 Little Joe II ........................................................................................................ 2 Saturn I.............................................................................................................. 2 Saturn IB ........................................................................................................... 2 Saturn V ............................................................................................................ 2 CSM................................................................................................................... 3 Lunar Module ..................................................................................................
[Show full text]
Space Launch Vehicle Design
Space Launch Vehicle Design Conceptual design of rocket powered, vertical takeoff, fully expendable and first stage boostback space launch vehicles David Woodward Department of Mechanical and Aerospace Engineering University of Texas at Arlington This dissertation is submitted for the degree of Masters of Science of Aerospace Engineering College of Engineering December 2017 i Declaration I hereby declare that except where specific reference is made to the work of others, this thesis is my own work and contains nothing which is the outcome of work done in collaboration with others, except as specified in the text and Acknowledgements. Of specific note is the MAE 4350/4351 Senior Design class that ran from January 2017 through August 2017 which was tasked with a similar project. The work presented in my thesis did not borrow from their work except for adapting their method for the estimating of the zero-lift drag coefficient of grid fins, which is referenced appropriately in the text. The methodology used to size first stage boostback launch vehicles and simulate a return-to-launch-site trajectory is of my own design and work. This thesis contains fewer than 51,000 words including appendices, bibliography, footnotes, tables and equations and has fewer than 90 figures. David Woodward January 2018 ii Acknowledgements To Dr. Chudoba, for first meeting with me back in my sophomore year and being a continual presence in my education ever since. The knowledge and skills I have developed from taking all of your classes and working in the AVD are indispensable, and I will be a far better engineer because of it.
[Show full text]
Crew and Space Transportation Systems Cost Model (CASTS) Richard Webb KAR Enterprises [email protected]
Presented at the 2016 ICEAA Professional Development & Training Workshop - www.iceaaonline.com/atlanta2016 Crew and Space Transportation Systems Cost Model (CASTS) Richard Webb KAR Enterprises [email protected] Abstract As part of the MSFC Engineering Cost Office’s new Program Cost Estimating Capability (PCEC) suite of cost estimating tools and capabilities, we are developing the Crew and Space Transportation Systems Cost Model (CASTS), a new, unique cost model for use in estimating crew and space transportation systems. This paper will provide an overview of the capabilities, estimating approach, historical database, and key features of CASTS as well as plans for future improvements. Introduction The Crew and Space Transportation Systems Cost Model (CASTS) is part of a new cost analysis capability intended for use in estimating space transportation systems including crewed systems and earth-to-orbit and in-space transportation systems. CASTS is currently being developed under a broader development effort led by NASA Marshall Space Flight Center’s Engineering Cost Office (ECO) as part of the Program Cost Estimating Capability (PCEC). Under the guidance and direction of the MSFC ECO, PCEC is being developed by the Marshall Integrated Program Support Services (MIPSS) team led by Victory Solutions, Inc. In keeping with the aim implicit in the last “C” in PCEC, CASTS is focused on developing an integrated capability coupling a parametric cost model with the historical data from whence it is developed, rather than “just” a parametric
[Show full text]
United States Space Program Oral History Collection [Kapp]
United States Space Program Oral History Collection [Kapp] Melissa Carson (2001); Amanda Buel (2019) 2001 National Air and Space Museum Archives 14390 Air & Space Museum Parkway Chantilly, VA 20151 [email protected] https://airandspace.si.edu/archives Table of Contents Collection Overview ........................................................................................................ 1 Administrative Information .............................................................................................. 1 Biographical / Historical.................................................................................................... 2 Scope and Contents........................................................................................................ 2 Arrangement..................................................................................................................... 2 Names and Subjects ...................................................................................................... 2 Container Listing ............................................................................................................. 4 Series 1: Audio, 1939-1977 and undated................................................................ 4 Series 2: Transcripts, 1966-1969 and undated...................................................... 83 United States Space Program Oral History Collection [Kapp] NASM.XXXX.0138 Collection Overview Repository: National Air and Space Museum Archives Title: United States Space Program Oral History
[Show full text]
Project Apollo: the Tough Decisions / Robert C
I-38949 Seamans BookCVR.Fin 4/26/05 3:31 PM Page 1 d PROJECT APOLLO National Aeronautics and Space Administration Office of External Relations History Division Washington, DC 20546 : The ToughDecisions Robert C. Seamans, Jr. Robert C.Seamans,Jr. PROJECT APOLLO The Tough Decisions Monographs in Aerospace History No. 37 • SP-2005-4537 NASA SP-2005-4537 Robert C. Seamans, Jr. PROJECT APOLLO The Tough Decisions Monographs in Aerospace History Number 37 National Aeronautics and Space Administration Office of External Relations History Division Washington, DC 2005 On the cover: A Saturn rocket figuratively reaches for the Moon. Library of Congress Cataloging-in-Publication Data Seamans, Robert C. Project Apollo: the tough decisions / Robert C. Seamans, Jr. p. cm. Includes bibliographical references. 1. Project Apollo (U.S). 2. Manned space flight 3. Space flight to the moon. I. Title. TL789.8.U6A581653 2005 629.45’4’0973—dc22 2005003682 ii Table of Contents iv List of Figures vii Acknowledgments ix Foreword 1 Chapter 1: Introduction 5 Chapter 2: Eisenhower’s Legacy 11 Chapter 3: The Kennedy Challenge 57 Chapter 4: Johnson’s Solid Support 83 Chapter 5: NASA Management 107 Chapter 6: The Grand Finale 117 Chapter 7: The Aftermath 127 Appendix 1 131 Appendix 2 139 Appendix 3 143 About the Author 145 Acronyms and Abbreviations 149 NASA Monographs in Aerospace History Series 151 Index iii List of Figures Page 13 Figure 1 Results of a study commissioned on 6 January 1961 and chaired by George Low. These findings were available on 7 February 1961. Page 14 Figure 2 NASA Management Triad in the office of James E.
[Show full text]
19720063748.Pdf
APOLLO DESIGN FEA TURES C. H . Feltz Assistant Program Manager and Chief Engineer, Apollo Space and Information Systems Division, North American Aviation, Inc. Abstract Design Features Arising From Limitations in Available Boosters This paper presents some Apollo design features that were dictated by special problems The relative sizes of the various launch vehicles associated with a manned lunar landing and return that are either in use or considered for use in the mission. Design features primarily attributed to United States manned space program are shown in booster limitations, crew safety, and natural Figure l. Of these vehicles, only Saturn V or mission requirements are discussed. Emphasis is NOVA has the performance capability to fulfill the placed on those features considered unique. Apollo objectives. For a direct lunar-landing Examples of specific topics considered are the mission, the NOVA vehicle would be the most general designs of the command module, heat desirable from the standpoint of performance, but shield, environmental control system, service because of the longer development time and higher module propulsion system, and Earth landing cost of the NOVA, NASA selected Saturn V as the system. Apollo launch vehicle. /IKlTt: SIZ( AHO COHfICiUlATiOH Introduction 01 HCNA ARE HOT FIlM Although unmanned space probes have pene trated into deep space and, in particular, have transmitted information back to Earth regarding our neighboring planet Venus, man's personal venture into space has thus far been confined to Earth-orbital flights. The success of the Mercury program has been phenomenal. Project Gemini is an extension of the Mercury program with a greater number of Earth-orbits, two men in the capsule, and Earth-orbital-rendezvous missions .
[Show full text]
Review for the Space Shuttle I Ntroducti On
CRYOGEN INSULATION TECHNOLOGY REVIEW FOR THE SPACE SHUTTLE James R. barber NASA -Lew i s Re sea rch Cen te r Cleveland, Ohio I NTRODUCTI ON The cryogenic insulation required for a reusable space shuttle vehicle falls into two general categories. These are (1) the insulation required for the ascent LH2 tanks on both the booster and orbiter and (2) the insulation required for the on-orbit propellant tanks within the orbiter. This figure shows one possible arrangement of propellant tanks in a typical orbiter. The larger LH2 and LO2 tanks contain the ascent propellant and the smaller tanks contain the on-orbit propellant. This paper provides a brief description of the technology available for the insulation systems required for the LH2 ascent tanks and the LHZ and LO2 on-orbit tanks. In addition, programs to provide the technology necessary to achieve acceptable insulations the space shuttle, that are already in progress or planned for the immediate future, are identified. 146 147 Environment and Design Considerat ions The environment to which the shuttle will be exposed is, in several respects, similar to that of the Saturn vehicle. The ground hold and ascent portions of the flight for both the shuttle booster and shuttle orbiter are similar to those of the Saturn II and Saturn IV-B vehicles. Where the environment for the shuttle differs from that of the Saturn is in the requirements for stay time in orbit and the need to withstand the stresses of re-entry in a reuseable condition. The shuttle environment is summarized in this figure.
[Show full text]
Separation, Transposition and Docking of Apollo 11 in Low-Earth Orbit
Separation, Transposition and Docking of Apollo 11 in low-Earth Orbit Julius A. Birch Unaffiliated (Dated: May 5, 2018) A selection of visual media from the Apollo 11 Mission, namely, the 70mm photographs AS11-36- 5301 through AS11-36-5313 and the 16mm film magazine A, are shown to strongly suggest that at the time of their filming Apollo 11 craft were in low-Earth orbit. The visual media comprise the film footage and the photographs of the craft and the Earth filmed before and during the maneuvers separation, transposition and docking (STD). The STD reportedly occured during the translunar coast some 30 minutes after the translunar injection (TLI). In the STD, the Command and Service Module (CSM) would dismount the rocket Saturn-IVB (S-IVB) carrying the Lunar Module (LM) and the CSM up to that point, then dock with and extract the LM. The S-IVB would then split from the group to fly behind the Moon and in an orbit around the Sun. In determining the location of the Apollo 11 craft, the sizes of Earth and the S-IVB rocket and their distances from the camera are extracted from the media assuming a selection of camera lenses. The extracted CSM flight data include the turning rate and the turning angle, the maximum separation distance, and the docking velocity. From their comparison to the Flight Plan, the Mission Report and to the oral transcripts from the Apollo 11 Flight Journal, it is found that the 16mm Mauer Data Acquisition Camera (DAC) was filming with the 10mm lens, and not with the 18mm lens as NASA reported.
[Show full text]