NASA Technical Reports Server (NTRS) 20010020952: Scientific and Technical Reports, Articles, Papers, and Presentations

78 Pages·4.4 MB·English

by  NASA Technical Reports Server (NTRS)

NASA/TM--2001-210795
FY 2000 Scientific and Technical Reports,
Articles, Papers, and Presentations
Compiled by
J.E. Tumer Waits
Marshall Space Flight Center, Marshall Space Flight Center, Alabama
National Aeronautics and
Space Administration
Marshall Space Flight Center • MSFC, Alabama 35812
January 2001
Available from:
NASA Center for AeroSpace lntormation National Technical Information Service
7121 Standard Drive
5285 Port Royal Road
Hanover, MD 21076-- 132(I
Springfield, VA 22161
(3011 621-0390
[phone]
ii
FOREWORD
In accordance with the NASA Space Act of 1958, the MSFC has provided for the widest practicable and
appropriate dissemination of information concerning its activities and the results thereof.
Since July I, 1960, when the George C. Marshall Space Flight Center was organized, the reporting of
scientific and engineering information has been considered a prime responsibility of the Center. Our credo has been
that "research and development work is valuable, but only if its results can be communicated and made understand-
able to others."
The N number shown for the reports listed is assigned by the Center for AeroSpace Information (CASI),
Hanover, MD, indicating that the material is unclassified and unlimited and isavailable for public use. These publi-
cations can be purchased from the National Technical Information Service, 5285 Port Royal Road, Springfield, VA
22161. The N number should be cited when ordering.
,,°
111

GEORGE C. MARSHALL SPACE FLIGHT CENTER
Marshall Space Flight Center, Alabama
FY 2000 SCIENTIFIC AND TECHNICAL REPORTS,
ARTICLES, PAPERS, AND PRESENTATIONS
TABLE OF CONTENTS
NASA TECHNICAL MEMORANDA .............................................................................................................. 1
NASA TECHNICAL PUBLICATIONS ............................................................................................................ 7
NASA SPECIAL PUBLICATION ..................................................................................................................... 11
MSFC CONFERENCE PUBLICATIONS ......................................................................................................... 12
NASA CONTRACTOR REPORTS ................................................................................................................... 13
MSFC PAPERS CLEARED FOR PRESENTATION ........................................................................................ 14
INDEX ................................................................................................................................................................ 59

NASA TECHNICAL MEMORANDA
TM-1999-209732 October 1999 Prior to the test it had been expected that the beam
Construction of aChemical Sensor/Instrumentation would lay down a static charge on the cloth and be
Package Using Fiber Optic and Miniaturization deflected without damaging the cloth. The burnthrough
Technology (MSFC Center Director's Discretionary isthought tobe an effect of partial transmission of beam
Fund Final Report, Project No. 97-12). R.L. Newton. power by a stream of positive ions generated by the high-
Materials, Processes, and Manufacturing voltage electron beam from contaminant gas in the
Department. 19990111739N "vacuum" chamber. A rough quantitative theoretical
computation appears to substantiate this possibility.
The objective of this research was to construct a
chemical sensor/instrumentation package that was TM-1999-209788 December 1999
smaller in weight and volume than conventional Unmanned Vehicle Guidance Using Video Camera/
instrumentation. This reduction inweight and volume is Vehicle Model (MSFC Center Director's
needed to assist infurther reducing the cost of launching Discretionary Fund Final Report, Project 97-23).
payloads into space. To accomplish this, fiber optic T. Sutherland. Avionics Department.
20000011914N
sensors, miniaturized spectrometers, and wireless
modems were employed. The system was evaluated using
iodine as a calibration analyte. A video guidance sensor (VGS) system has flown
on both STS-87 and STS-95 to validate a single camera/
TM-1999-209757 November 1999 target concept for vehicle navigation. The main part of
NASA's Microgravity Research Program 1998 the image algorithm was the subtraction of two
Annual Report. D. Woodard, Editor. Microgravity consecutive images using software. For a nominal size
Research Program Office. 20000014137N image of 256x256 pixels this subtraction can take a large
portion of the time between successive frames instandard
The Fiscal Year 1998 Annual Report describes key rate video, leaving very little time for other computations.
elements of the NASA Microgravity Research Program. The purpose of this project was to integrate the software
The Program's goals, approach taken to achieve those subtraction into hardware to speed up the subtraction
goals, and program resources are summarized. A review process and allow for more complex algorithms to be
of the Program's status at the end of FY 1998 and performed, both in hardware and software.
highlights of the ground- and flight-based research are
TM-t 999-209876 December !999
provided.
Friction Stir Welding for Aluminum Metal Matrix
TM-1999-209762 November 1999 Composites (MMC's) (MSFC Center Director's
Low-Pressure Gas Effects on the Potency of an Discretionary Fund Final Report, Project No. 98-
Electron Beam Against Ceramic Cloth. A.C. Nunes, 09). J.A. Lee, R.W. Carter, and J. Ding. Materials,
Jr., C.K. Russell, F.R. Zimmerman, and J.M. Processes, and Manufacturing Department.
2000004679N
Fragomeni.* Materials and Processes Laboratory and
*Ohio University. 20000010545N
This technical memorandum describes an
An 8-kv electron beam with a current in the investigation of using friction stir welding (FSW) process
neighborhood of 100 mA from the Ukrainian space for joining a variety of aluminum metal matrix
welding "Universal Hand Tool" (UHT) burned holes in composites (MMC's) reinforced with discontinuous
Nextel AF-62 ceramic cloth designed to withstand silicon carbide (SIC) particulate and functional gradient
temperatures up to 1,427 °C. The burnthrough time was materials. Preliminary results show that FSW isfeasible
on the order of 8 sec at standoff distances between UHT to weld aluminum MMC to MMC or to aluminum-
and cloth ranging from 6-24 in. At both closer (2 in.) lithium 2195 if the SiC reinforcement is <25 percent by
and farther (48 in.) standoff distances the potency of the volume fraction. However, a softening in the heat-
beam against the cloth declined and the burnthrough time affected zone was observed and is known to be one of
went up significantly. the major limiting factors forjoint strength. The pin tool's
material ismade from a low-cost steel tool H-I 3material,
NASATECHNICALMEMORANDA
andthepintool'swearwasexcessivseuchthatthepin comparedtothemodifiedCour-Palaissingle-plate
toollengthhastobemanuallyadjustedforevery5ftof penetratioenquationT.henthepredictionfsromeachof
weldmenItn.itially,boron-carbidceoatingwasdeveloped thesevendouble-platepenetrationequationswere
for pin tools, but it did not showa significant comparedwithtestresultsperformedattheNASA
improvemenitn wearresistanceB.asically,FSWis MarshallSpaceFlightCenter.Becausethedifferent
applicablmeainlyforbuttjoiningofflatplatesT.herefore, equationpsredicatwiderangeofprojectilediameterast
FSWofcylindricalarticlessuchasaflangetoaduct anygivenvelocityi,tisverydifficulttochoostehe"right"
withpracticadliametersrangingfrom2-5in.mustbe predictionequationforshieldconfigurationostherthan
fully demonstrateadndcomparedwithotherproven thoseexactlyusedin theequations'development.
MMCjoiningtechniquefsorcylindricaal rticles. Althoughdevelopefdorvariousmaterialsth,epenetration
equationsalonecannotbereliedupontoaccurately
TM-1999-209877 Decembe1r999
predicttheeffectivenessof a shieldwithoutusing
InformationFlowin theLaunchVehicleDesign/ hypervelocitiympactteststoverifythedesign.
AnalysisProcesWs..R.HumphfieSs,r.,W.Holland,*
andR.Bishop.*FlightSystemsDepartmenatnd TM-2000-209962 Februar2y000
*SverdrupTechnologIyn,c. 20000012425N Observationof IndividualFluorineAtomsFrom
HighlyOrientedPoly(tetrafluoroethyleFneilm) sby
Thispapedrescribethseresultsofateameffortaimed AtomicForceMicroscopyJ..A.Lee.Materialsand
atdefiningtheinformationflowbetweendisciplinesat ProcesseLsaboratory. 20000032164N
theMarshallSpaceFlightCenter(MSFC)engageidn
thedesignofspacelaunchvehiclesT.heinformatiofnlow Directobservatioonfthefilmthicknessm, olecular
ismodeledatafirstlevelandisdescribeudsingthree structure,andindividualfluorineatomsfromhighly
typesof templatesa:nN×Ndiagramd,isciplineflow orientedpoly(tetrafluoroethylen(eP)TFE)filmswere
diagramsa,nddisciplinetaskdescriptionsIt.isintended achievedusingatomicforcemicroscop(yAFM).Athin
toprovideengineerswith anunderstandingof the PTFEfilmismechanicaldlyepositeodntoasmoothglass
connectionbsetweenwhattheydoandwhereitfitsin substrateatspecifictemperaturebsyafriction-transfer
theoveraldlesignprocesosftheprojectI.tisalsointended techniqueA.tomicresolutioinmageosfthesefilmsshow
toprovidedesignmanagerwsithabetterunderstanding thatthechain-likehelicalstructuresof thePTFE
ofinformationflowinthelaunchvehicledesigncycle. macromoleculeasrealignedparalletloeachotherwith
anintermoleculasrpacingof 5.72.A,andindividual
TM-2000-209907 Februar2y000 fluorineatomsareclearlyobserveadlongthesetwisted
Double-PlaPteenetratioEnquationsK..B.Hayashida moleculacrhainswithaninteratomiscpacingof2.75,_.
andJ.H.Robinson.StructuresM, echanicsa,nd
Furthermore, the first direct AFM measurements for the
ThermaDl epartment. 20000032469N radius of the fluorine-helix and of the carbon-helix in
subangstrom scale are reported as 1.7 and 0.54 A
Thisreporctomparessevendouble-plapteenetration
respectively.
predictoerquationfsoraccuracyandeffectivenesosfa
shielddesignT.hreeofthesevenaretheJohnsonSpace
TM-2000-210014 February 2000
Centeroriginal, modified, andnewCour-Palais
Degradation Factor Approach for Impacted
equationsT.heotherfouraretheNysmithL, undeberg-
Composite Structural Assessment (MSFC Center
Stern-BristowB,urch,andWilkinsonequationsT.hese
Director's Discretionary Fund Final Report, Project
equationse,xcepttheWilkinsonequationw, erederived
No. 96-17). R. Ortega, J.M. Price, and D. Fox.
fromtestresultsw, iththevelocitiesrangingupto8km/
Structures, Mechanics, and Thermal Department.
sec.Spreadsheestoftwarecalculatedtheprojectile 20000025237N
diametersfor variousvelocitiesfor thedifferent
equationTs.heresultswereplottedonprojectilediameter This technical memorandum documents the results
versusvelocitygraphsfortheexpectedorbitaldebris
of the research to develop a concept for assessing the
impacvtelocitiesrangingfrom2to15km/secT.henew
structural integrity of impacted composite structures
Cour-Palaisdouble-platepenetrationequationwas
using the strength degradation factor in conjunction with
2
NASA TECHNICAL MEMORANDA
available finite element tools. For this purpose, a literature TM--2000-210129 March 2000
search was conducted, a plan for conducting impact Magnetically Actuated Propellant Orientation
testing on two laminates was developed, and a finite Experiment, Controlling Fluid Motion With
element model of the impact process was created. Magnetic Fields in a Low-Gravity Environment
Specimens for the impact testing were fabricated to (MSFC Center Director's Discretionary Fund Final
support the impact testing plan. Report, Project No. 93-18). J.J. Martin and J.B. Holt.
Propulsion Research Center. 20000036592N
TM--2000-210076 February 2000
Test Report for NASA MSFC Support of the Linear This report details the results of a series of fluid
Aerospike SR-71 Experiment (LASRE). S.K. Elam. motion experiments to investigate the use of magnets to
Subsystem and Component Development orient fluids in a low-gravity environment. The fluid of
Department. 20000037777N interest for this project was liquid oxygen (LO 2) since it
exhibits a paramagnetic behavior (is attracted tomagnetic
The Linear Aerospike SR-71 Experiment (LASRE) fields). However, due to safety and handling concerns, a
was performed insupport of the Reusable Launch Vehicle water-based ferromagnetic mixture (produced by
(RLV) program to help develop a linear aerospike engine. Ferrofluidics Corporation) was selected to simplify
The objective of this program was to operate a small procedures. Three ferromagnetic fluid mixture strengths
aerospike engine at various speeds and altitudes to and anonmagnetic water baseline were tested using three
determine how slipstreams affect the engine's different initial fluid positions with respect to the magnet.
performance. The joint program between government and Experiment accelerometer data were used with a
industry included NASA's Dryden Flight Research modified computational fluid dynamics code termed
Center, the Air Force's Phillips Laboratory, NASA's CFX-4 (by AEA Technologies) to predict fluid motion.
Marshall Space Flight Center, Lockheed Martin These predictions compared favorably with experiment
Skunkworks, Lockheed-Martin Astronautics, and video data, verifying the code's ability to predict fluid
Rocketdyne Division of Boeing North American. Ground motion with and without magnetic influences. Additional
testing of the LASRE engine produced two successful predictions were generated for LO2 with the same test
hot-fire tests, along with numerous cold flows to verify conditions and geometries used in the testing. Test
sequencing and operation before mounting the assembly hardware consisted of a cylindrical Plexiglas tank (6-in.
on the SR-71 .Once installed on the aircraft, flight testing bore with 10-in length), a 6,000-G rare Earth magnet
performed several cold flows on the engine system at (10-in. ring), three-axis accelerometer package, and a
altitudes ranging from 30,000 to 50,000 feet and Mach video recorder system. All tests were conducted
numbers ranging from 0.9 to 1.5. The program was aboard the NASA Reduced-Gravity Workshop, a KC-
terminated before conducting hot-fires in flight because 135A aircraft.
excessive leaks in the propellant supply systems could
not be fixed to meet required safety levels without TM--2000-210130 March 2000
significant program cost and schedule impacts. FY 1999 Scientific and Technical Reports, Articles,
Papers, and Presentations. J.E. Turner Waits,
TM--2000-210128 March 2000 Compiler. Information Services Department.
20000043603N
Rapid Production of Composite Prototype Hardware
(MSFC Center Director's Discretionary Fund Final
Report, Project No. 96-02). T.K. DeLay. Materials, This document presents formal NASA technical
Processes, and Manufacturing Department. reports, papers published in technical journals, and
20000050473N presentations by MSFC personnel in FY99. It also
includes papers of MSFC contractors.
The objective of this research was to provide a All of the NASA series reports may be obtained from
mechanism to cost-effectively produce composite the NASA Center for Aerospace Information (CASI),
hardware prototypes. The task was to take a hands-on 7121 Standard Drive, Hanover, MD 21076-1320.
approach to developing new technologies that could The information in this report may be of value to the
benefit multiple future programs. scientific and engineering community in determining
3
NASATECHNICALMEMORANDA
whatinformationhasbeenpublishedandwhatis
extracellular spaces could be estimated. By performing
available.
this estimation over time, the volume dynamics during
application of stimuli which affect the direction of gravity
TM-- 1999-210131 May1999
can be viewed. The resulting data can form a basis for
AnalysisandAssessmeonftPeakLightningCurrent further modeling and verification of cardiovascular and
ProbabilitieasttheNASAKennedySpaceCenter.
compartmental modeling of fluid reactions to
D.L.JohnsoanndW.WV. aughan,S*ystemAsnalysis
microgravity as well as countermeasures to the headward
andIntegratioLnaboratory*,UniversityofAlabama
shift of fluid during head-down tilt or spaceflight.
inHuntsville. 20000039434N
TM--2000-210252 May 2000
Thistechnicaml emorandupmresentassummarbyy
Mechanical Property Allowables Generated for the
theElectromagneticasndAerospaceEnvironments
Solid Rocket Booster Composite Nose Cap. A.J.
BranchattheMarshalSl paceFlightCenteorflightning
Hodge. Materials, Processes, and Manufacturing
characteristicasndlightningcriteriafortheprotection Department. 20000060843 N
ofaerospacveehiclesP.robabiliteystimateasreincluded
forcertainlightningstrikes(peakcurrentsof200,100,
Mechanical property characterization was performed
and50kA)applicabletotheNationaAleronauticasnd
on AS4/3501-6 graphite/epoxy and SC350G syntactic
SpaceAdministrationSpaceShuttleattheKennedy
foam for the SRB Composite Nose Cap Shuttle Upgrades
SpaceCenterF,loridaduringrollout,on-padandboost/
Project. Lamina level properties for the graphite/epoxy
launchphasesR.esultsofanextensivleiteraturesearch
were determined at room temperature, 240 OF,350 °F,
tocompileinformationonthissubjecatrepresenteidn
480 °F, 600 °F, and 350 °F after a cycle to 600 °F.
ordertoanswekreyquestionpsosedbytheSpacSehuttle
Graphite/epoxy samples were moisture conditioned prior
ProgramOfficeattheJohnsonSpaceCentecroncerning
totesting. The syntactic foam material was tested at room
peaklightningcurrenpt robabilitieisfavehicleishitby
temperature, 350 °F and 480 °E A high-temperature test
a lightningcloud-to-groundstroke.Vehicle-triggered
facility was developed at MSFC. Testing was performed
lightningprobabilityestimatefsortheaforementioned
with quartz lamp heaters and high resistance heater strips.
peakcurrentsarestill beingworked.Section4.5,
The thermal history profile ofthe nose cap was simulated
howeverd,oesprovidesomeinsightonestimatintghese
inorder to test materials at various times during launch.
samepeaks.
A correlation study was performed with Southern
Research Institute to confirm the test methodology and
TM--2000-2!0200 January2000
validity oftest results. A-basis allowables were generated
A Reviewof Electrical Impedance Spectrometry from the results of testing on three lots of material.
Methods for Parametric Estimation of Physiologic
Fluid Volumes (MSFC Center Director's TM--2000-210279 May 2000
Discretionary Fund Final Report, Project No. 96- Mars Global Reference Atmospheric Model 2000
03). B. Dewberry. Avionics Department. Version (Mars-GRAM 2000): Users Guide. C.G.
20000038205N Justus* and B.F. James. Engineering Systems
Department and *Computer Sciences Corporation.
Electrical impedance spectrometry involves
measurement of the complex resistance of a load at This report presents Mars Global Reference
multiple frequencies. With this information in the form Atmospheric Model 2000 Version (Mars-GRAM 2000)
of impedance magnitude and phase, or resistance and and its new features. All parameterizations for
reactance, basic structure or function of the load can be temperature, pressure, density, and winds versus height,
estimated. The "'load" targeted for measurement and latitude, longitude, time of day, and Lshave been replaced
estimation in this study consisted of the water-bearing by input data tables from NASA Ames Mars General
tissues of the human calf. It was proposed and verified Circulation Model (MGCM) for the surface through 80-
that by measuring the electrical impedance of the human km altitude and the University of Arizona Mars
calf and fitting this data toa model of fluid compartments, Thermosphere General Circulation Model (MTGCM) for
the lumped-model volume of intracellular and 80 to 170 kin. A modified Stewart thermospheric model
4