ai-aerospace/ams_data_full_2000-2020 huggingface dataset:
3:00SESSION IIImACTUATORS, ROVERS, ROBOTS ANDPOSTER PREVIEW KarlAnderson, Session Chair MoogInc,Chatsworth, CA •DCMotorSelection forSpaceMechanisms DavidMarksandRichard Fink,MoogInc.,Research Triangle Park,NC •Designing andManufacturing ofExtremely LowMassFlightSystems Michael Johnson, JetPropulsion Laboratory, Pasadena, CA •Design ofaRobotic WristandTool-Exchange Mechanism forSatellite Servicing Russell Howard, University ofMaryland, College Park,MD •Operational Improvements ofaPyrotechnic UltraLowShockSeparation Nut Alexander Luna,Hi-Shear Technology Corporation, Torrance, CA •Alternatives toPyrotechnics -NitinolRelease Mechanisms Andrew Tuszynski, Hi-Shear Technology Corporation, Torrance, CA •System Characterization andMotorStepVerification through Rotary Acceleration Signals ScottStarinandFredCrosno, CDAInterCorp, Deerfield, FL •HighResolution Standard Proximity Sensor RogerBlaser, Vibro-Meter SA,Fribourg, Switzerland 6:30-9:30 RECEPTION ANDDISPLAYS ATTHESHERATON--West Ballroom on6thFloor Invitedcomponent andsoftware suppliers display current products andprovide tutorials NASA/CP--2002-211506 x
THURSDAY, 16MAY2002 7:30 THURSDAY PRESENTERS' BREAKFAST--Hope Roomon7thFloor 8:30 SESSION IV--DEPLOY II GaryHeinemann, Session Chair AEC-Able Engineering, Goleta, CA •Qualification oftheInflatable Sunshield InSpace(ISIS)Mast DavidRohweller, TRWAstroAerospace, Carpinteria, CA •ISSS/ADeployment--The HighsandLowsofEVAContingency Capability, ADesigner's Perspective BertHaugen, Malcolm FerryandKevinKlein,Lockheed MartinSpaceSystems, Sunnyvale, CA •TheLightweight Deployable Antenna fortheMARSIS Experiment ontheMarsExpress Spacecraft Geoffrey MarksandMichael Reilly,TRWAstroAerospace, Carpinteria, CA;Richard Huff, University ofIowa,IowaCity,IA 10:00 BREAK 10:15 SESSION V--INSTRUMENT MECHANISMS II Martha Milton, Session Chair NASAMarshall SpaceCenter •MABE: High-Precision Tip/Tilt Mechanism BasedonMagnetic Bearing Technology Nicolas LoixandJ.Ph.Verschueren, Micromega Dynamics SA,Angleur, Belgium; Lucio Scolamiero, ESA/ESTeC, Noordwijk, TheNetherlands •Development ofaFineSteering MirrorAssembly Ruben Nalbandian andJeffWilliams, MoogInc.,Chatsworth, CA •ADescription andPerformance ofMechanisms usedintheHighResolution Ionospheric Thermospheric Spectrograph PhillipKalmanson andRussell Starks, Praxis, Inc.,Alexandria, VA;Hsiung Chou,Raytheon STX,Lanham, MD;Kenneth Dymond andStefan Thonnard, NavalResearch Laboratory, Washington, D.C. 11:45 LUNCH BREAK 1:00 SESSION VImRELEASE ANDDOCKING MECHANISMS Robert Fusaro, Session Chair NASAGlennResearch Center (ret),Cleveland, OH •Design ofanEVA-Capable Four-Point Restraint System Armond Asadurian andJimHammond, MoogInc.,Chatsworth, CA;KazuoHamada and Hiroshi Irikado, NECTOSHIBA SpaceSystems, Japan; Michio ItoandMihoEndo, NASDA, Japan •Intricacies ofUsingKevlarCordandThermal Knives inaDeployable Release System: IssuesandSolutions Alphonso Stewart andJasonHair,NASAGoddard Space FlightCenter, Greenbelt, MD •Release Mechanisms ontheGravity Probe-B Relativity Mission SeanMcCully andDennis St.Clair,Lockheed MartinSpaceSystems Co.,Sunnyvale, CA •Conceptualization andDesign ofaMechanical Docking System TroyNilsonandMitchWiens, Starsys Research, Boulder, CO •Automating Separation System Reliability Testing RyanPerroy, Planetary Systems Corporation, SilverSpring, MD 3:30 BREAK NASA/CPm2002-211506 xi
3:45SPECIAL PRESENTATION: ROSEPARADE FLOAT MECHANISMS Theunder-the-hood details onwhatmakes thosebeautiful, animated, short-lived floats dazzleaudiences around theworldeveryJanuary 1st. Michael Johnson, JetPropulsion Laboratory, Pasadena, CA 5:30-10:30 SYMPOSIUM BANQUET ATGREAT LAKES SCIENCE CENTER WalkorbustoScience Center 7:00 Dinner anddisplays 10:00 Return tothehotel NASA/CP--2002-211506 xii
FRIDAY, 17MAY2002 7:30 FRIDAY PRESENTERS' BREAKFASTIHope Roomon7thFloor 8:30 SESSION VImTRIBOLOGY ANDGROUND TEST DavidOsterberg, Session Chair Honeywell Inc.,Glendale, AZ •Random Vibration Failure Mechanism ofaConrad Bearing usingCrown Bali-Retainer KlausEngel, Regina Kwiatkowska andMihaiVladimirescu, COMDEV,Ltd.,Cambridge, Canada •Comparison ofSeveral Different Sputtered Molybdenum Disulfide Coatings forUsein Space Applications Robert Fusaro, NASAGlennResearch Center, Cleveland, OH;MarkSiebert, University of Toledo, Toledo, OH •Space BallBearing LoadCapacity withDryLubrication AndreBorrien, Jean-Bernard Mondier andE.Conde, Centre National D'Etudes Spatiales, Toulouse, France •Tribological Properties ofaPennzane®-Based LiquidLubricant (Disubstituted Alkylated Cyclopentane) forLowTemperature SpaceApplications Clifford Venier, PennzoiI-Quaker StateCompany, TheWoodlands, TX;Edward Casserly, Penreco Company, TheWoodlands, TX;William Jones, Jr.andMarioMarchetti, NASA GlennResearch Center, Cleveland, OH;MarkJ.Jansen, Sest,Inc.,Middleburg Hts.,OH; Roamer Predmore, NASAGoddard SpaceFlightCenter, Greenbelt, MD •ISSSGANT GroupLevelOffloading TestMechanism XilinZhang, EMSTechnologies Canada, Ltd.,St.Anne-de-Bellevue, Canada •Relationship between theDifficulty IndexandtheEvaluation Accuracy ofGround Deployment Testing Hironori Ishikawa andAkiraMeguro, NTTNetwork Innovation Laboratories, NTT Corporation, Kanagawa, Japan 11:30 BREAK 11:45 PRESENTATION: ANOVERVIEW OFGRC 12:15 TECHNICAL SESSIONS CONCLUSION •Presentation oftheHerzlAward •Closing Remarks 1:30 BUSES DEPART HOTEL FORGRCTOUR 1:30-3:30 GLENN RESEARCH CENTER FACILITY TOUR NASA/CP--2002-211506 xiii
Organizing Committee FredB.Oswald, HostChairman, NASAGRC StuartH.Loewenthal, General Chairman, Lockheed Martin Edward A.Boesiger, Operations Chairman, Lockheed Martin ObieH.Bradley, Jr.,NASALRC Michael J.Eiden, ESA/ESTEC Carlton L.Foster, NASAMSFC ClaefF.Hakun, NASAGSFC Christopher P.Hansen, NASAJSC AlanC.Littlefield, NASAKSC Edward C.Litty,JPL Ronald E.Mancini, NASAARC FredG.Martwick, NASAARC Stewart C.Meyers, NASAGSFC Martha E.Milton, NASAMSFC Wilfredo Morales, NASAGRC MinhPhan,NASAGSFC JohnF.Rogers, NASALRC Donald R.Sevilla, JPL MarkF.Turner, NASAARC Advisory Committee DavidF.Engelbert, NASAARC(ret) RobertL.Fusaro, NASAGRC(ret) JohnW.Redmon, Sr.,NASAMSFC(ret) AlfredL.Rinaldo, Lockheed Martin(ret) William C.Schneider, NASAJSC(ret) Bowden W.Ward,Jr.,NASAGSFC(ret) NASA/C P--2002-211506 xiv
Design Conditions Sampler hasoneormoreprojectors, andeachprojector firesaprojectile inordertofragment anasteroid surface intosmallpiecesassample. Thefragmented sample iscollected andconducted intoastorage vesselcalled'catcher' through ahornandaductbyitsownmulti-reflection. Thesample obtained inevery sampling projection isstoredseparately inthepartitioned catcher. Afteralltheprojection, thecatcher movesintoacontainer inareentrycapsule toretrieve thesample ontheearth.Thecontainer isairtightin ordernottoleakvolatile matterofthesample duringcruiseandalsotoprevent aninvasion ofatmosphere duringreentryandrecovery. SPCECRAFT SIDEPANEL SEPARABLE SAMPLE CATCHER REVOLBABLE AND RETRACTABLE DUCT I,IFI PROJECTOR(S) AS SAMPLE COLLECTION HORNLASER RANGE FINDER TODETECT TOUCHDOWN OF MOVABLE HORN ASTEROID SURFACE Figure1.Outline ofSampling Scientific restrictions areasfollows. Theamount ofsample issufficient forscientific analysis andthe sampling process mustnotdegenerate thephysical properties ofthesample. Thesampler isequipped withuptothreeprojectors, eachofwhichcanprojectoneprojectile. Thesizeofthecatcher andthesizeof ductfromthesurface tothecatcher should haveroomforfragments ofupto10mmindiameter. The fragments ofdifferent sampling attempt position onanasteroid surface arestoredseparately. Thesample should notbecontaminated byartificial matterandnatural matteroriginated ontheearth.Theartificial contamination mattercomesfromthrusters ofthespacecraft, projectors ofagunpowder type,sampler structure surface, slidingmechanisms, manufacturing andhandling processes, andsoon.Thecleanliness oftheenvironment during handling andintegration processes ismonitored, andwitness platesare attached tothesampler tomonitor thecontamination duringthemanufacturing, handling, andthe integration atthelaunching site.Thematerials andthesurface treatment ofthestructure andmechanisms ofthesampler shouldbeselected nottoreducescientific merit. Therearealsomanyengineering restrictions andconditions. Anchoring thespacecraft forsampling will notbeavailable. Sampling involves hovering, touchdown, andlift-offofthespacecraft. Thespacecraft and thetotalsystem should bekeptsafeduringthesampling sequence, although thesequence ofactions proceeds autonomously without anycommand fromtheearth.Thesampling actionmustnotdamage the NASA/C P--2002-211506 2
ISAMPLER I SAMPLING ASSEMBLY I -_CATCHER ASSEMBLY I __SAMPLE SEPARATION MECHANISM OFREVOLVING TUBE RETRACTION MECHANISM OF SAMPLE CONDUCTION TUBE CATCHER TRANSPORTAION MECHANISM ANDSTRUCTURE __LATCHANDSEALMECHANISM I OFCONTAINERHORNASSEMBLY I ---_HORN STRUCTURE ANDMECHANISM I _FIXEDHORNI _EXTENDIBLE CLOTHHORN _MOVABLE HORNI __CLAMP ANDRELEASE MECHANISM __EXTENSION MECHANISM AND COMPLIANT STRUCTURE _1DEPLOYABLE SHIELD1 --[PROJECTOR l Figure3.Structure ofSampler ClassificationTable1.Weiqht ofSampler Mechanisms Weight [10.3kg] Sampling Mechanism Portion Catcher Mechanism 70 Sample Separation Mechanism 390 Sample Conduction TubeRetraction Mechanism 250 Sample Conveyer Mechanism LatchandSealMechanism152O 97O Electrical andThermal Wiring 350 BoltsandNuts 100 HornMechanism Portion HornMechanism 4650 Projectors 450 Electrical andThermal Wiring 300 BoltsandNuts 100 Total 9150 Metallic partsofthefixedhornandthemovable hornaremadeofaluminum alloyplate.Thematerials and thethickness ofthehornaredetermined baseduponpenetration testsofprojectile. Theothermetallic structural partsaremadeofaluminum alloyandmagnesium alloy.Extendible andadaptive hornismade ofclothofhigh-tension polyarylate fiber(VECTRAN) andadouble-helical springofglassfiberreinforced plastic(GFRP). Theselection ofclothmaterials needsthepenetration testsandmuchconsideration to longandseverespaceenvironments. NASA/CP--2002-211506 5
Sampling Sequence andCharacteristics ofSampler Thehorniskeptretracted atthelaunchinordertosatisfytheallowed envelope, andisextended after launch. Thespacecraft descends toward anasteroid, andaprojector isfiredjustafterperception of touchdown. Firingistriggered bytheperception ofdisplacement oftheextended movable horn.The displacement isdetected byalaserrangefinder.Themovable hornistocoverthecratercaused bya projectile, andthefixedhornandtheconduction tubearetocollectandconduct fragments intoacatcher usingmulti-reflection; noadditional powerisnecessary toconduct thefragments. Thehornisalso adaptive tocomply withtheslopeandroughness ofthesurface, andistoprotectthespacecraft against high-speed fragments andreflected projectiles. Tothisend,themovable hornhasadeployable shielding brimmadeofcloth.Thebrimisdeployed atthesametimeastheextension ofthemovable horn.The schematic diagram isillustrated inFigure4(a). FIXEDDUSTSHIELD Figure4.Sampling Sequence, (a)Extension ofHorn Thesample obtained ineverysampling attempt isstoredinthecatcher separately byarevolving duct mechanism. Afterthefirstprojection, theaperture oftherevolving duct,whichisopentothefirstsample roomA,rotates 120degrees toclosetheroomAandtobeopentothenextsample roomB,andthe catcher become readyforthenextsampling. Aftereachsampling attempt, thespacecraft lifts-offassoon aspossible toavoidacrashattheasteroid surface. Afterthefinalsampling attempt, theaperture ofthe revolving ductrotatesanother 120degrees andconfronts ablindwallinthecatcher. Theconduction tube together withtherevolving ductrecedes fromthecatcher, andthecatcher moves intothecontainer through thebackboard ofthereentry capsule. Therearabrator ofthereentry capsule andthelidof container areattached tothecatcher, andareconveyed together withthecatcher. Thelidislatched automatically attheendofthetransportation. Thelengthoftheconveyer guidance cylinder is230x10.3m, andthetransportation distance is160xl0-3m.Thesealingforcetocompress thedoubleO-ringisobtained byothersprings installed insidethelid.Theinitiallyclamped springs arereleased byanactionofNEA. Thecontainer iskeptairtightuntilitisdismantled ontheearth.Onlythesealmechanism ofthecontainer worksbyusingspringforces,whicharereleased byanNEA.AnNEAisusednotonlybecause thespace foranactuator inthelidisextremely limited, butalsobecause thesample should bekeptawayfrom combustion gasesofapyrotechnic actuator, andbecause largeactuation shockbypyrotechnic devices hasbadeffectsontheelectronic instruments adjacent tothesealmechanism inthereentrycapsule. The remaining conveyer forceisreleased inordernottocausedisturbances attheseparation ofthereentry capsule fromthespacecraft. Thereentry capsule isseparated usingaspin-separation mechanism. The schematic diagram isillustrated inFigures 4(b)-(d). NASA/C P--2002-211506 6
Z  SPOEORAFTliREENTRY (_ATCHER XCAPSULE _PANEL _VOOMSAANDB CONTAINER SEPARATION OFSAMPLE FORROOM AANDROOM BSAMPLING CONCLUDED (CATCHER ISCLOSED) Figure4.Sampling Sequence, (b)Sample Separation Process iiCYLINDER x(_z CONVEYER GUIDANCE ___Jlllilllllltlllll!llllllllCONTAINER LIDAND _,j_¢/REARABIATO L CONDUCTION TUBEISCLOSED AND RETRACTED DOWNWARD. READY FORTRANSPORTATION OFCATCHERCATCHER ISTRANSPORTED INTO CONTAINER, ANDCONTAINER LIDIS LATCHED TOREENTRY CAPSULE. Figure4.Sampling Sequence, (c)Catcher Storage Process /SEALACTUATOR IPO_ VERCABLE C:NS_TRA_IN_IRE _JhLIIIII,IIIIIIIIIIIIIIIIII'_AY_R LID CONTAINER ISSEALED BYSEALMECHANISM. RESIDUAL CONVEYER FORCE IS THEN, POWER CABLE FORSEALACTUATOR RELEASED. ISCUT. READY FORCAPSULE SEPARATION Figure4.Sampling Sequence, (d)Container Sealing Process NASA/C P--2002-211506 7
Sliding Test Thesampler hasbeentestedafterthesystem vibration testonboard thespacecraft, andthewhole function hasbeenverified. Alsoallactions including operations ofSMAandpyrotechnic actuators have beencompleted successfully inathermal vacuum chamber. Afundamental slidingtestofthematerials bytestpieceshasbeencarried outinavacuum environment beforethemanufacturing ofthemechanism. Slidingpartsofthesampler system havebeenalsotestedin asandyenvironment. Theslidingtestofthemechanism inadustyorcrunchy environment hastwo purposes; oneistoprovetheoperation ofthesampler, andthesecond istofindthelimitation ofoperation underthedust.Theclearance ofeveryslidingparthasbeenverified byslidingtestsusingfragments of basaltwithawiderangeofgrainsizedistribution. Basaltisatypicalhardrock.Thedustusedinthetestis thecollected fragment madebyimpacting projectile intobasalt,andtheparticle sizedistribution ofthemis expected tobethesameastheactualsample onanasteroid iftheasteroid ismadeofbasalt.Excessively severeconditions intheamount ofdustmaybeinvolved, inordertoknowthelimitation offunction. The testconsists ofthefollowing foursteps. (1)Theoperation usingthepredetermined springisrepeated 100timeswithout dust,andthe variation ofnecessary operating forceismeasured. (2)Themechanism withdustisoperated usingthepredetermined spring, andthefunction is verified forcategorized particle size.Theamount ofdust,theparticle size,andtherelative directions between slidingandgravityarevaried. Thenumber oftestcombination ofthese parameters isabout100. (3)Thenecessary operating forcewithout dustismeasured aftertheteststep(2). (4)Aftertheteststep(3),thenecessary operating forceforcategorized particle sizeismeasured. Theamount ofdust,theparticle size,andtherelative directions between slidingandgravityare varied. Theslidingtestshavebeenapplied totherevolving andretracting part,wherethesample isseparated intoeachroombyarevolving ductandtheductisretracted beforeconveyance ofthecatcher, andthe transportation part,wherethecatcher together withtherearabrator areconveyed linearly intothereentry capsule. Theresultsofslidingteststeps(1)-(4)oftherevolving andretracting partareshowninTables 2(a)-(d), respectively. Theresultsofslidingteststeps(1)-(4)ofthelineartransportation partareshownin Tables3(a)-(d), respectively. ('1Table2.Sliding TestofRevolving andRetracting Duct,(a) Variation ofSlidinq DragForceafterRepeated O}eration; TestStel_(l___ Number ofOperation Revolving DragForce Retracting DragForce ('1) [_ 10 16.9IN] 13.0 20 29.8 14.7 30 26.7 10.4 40 32.3 16.5 50 40.4 19.2 60 24.5 20.0 70 41.0 17.6 80 41.6 18.4 90 33.7 25.4 100 31.8 21.0 Without Dust NASA/CP--2002-211506 8
Dust ParticleSizeDustAmount [106m] [10-6m 3] <53 1 10 53-125 1 10 125-250 1 10 250-420 1 10 420-590 1Table2.SlidingTestofRevolving andRetracting Duct,(b) Operation CheckunderDustEnvironment; TestStep(:!) AxisofGravityatRevolution Test('1) Direction ofGravityat Retraction Test('1) X-axisY-axis Z-axis 10 590-840 1 10 840-1600 1 10 Mixed 10X-axisX-axis Y-axis (*2)(*3) ('2) OOO O OO OOO OOO O OO O OO O OO O OO O OO O OO O OO O OO O OO O OO O OO O xO 70 O:NormalOperation x:LockedY-axisZ-axisZ-axis (*3)('2)(*3) OOOO OO OOOO OO OOOO OO OOOO OO OOOO OO OOOO OO OOOO OO OOOO OO OOOO OO OOOO O O OOOO OO OOOO OO OOOO OO OOOO OO OOOO OO xO x xx x ('1)FortheDirection ofGravity,SeeFigure4(b). (*2):0deg-120deg Revolution (*3):120deg-240deg Revolution Table2.SlidingTestofRevolving andRetracting Duct,(c) Variation ofSlidinqDragForceafterOperation CheckunderDustEnvironment; TestStep(3) Revolvinq DragForce[N] Retracting DragForce[N] BeforeTestStep(2)AfterTestStep(2)BeforeTestStep(2)AfterTestStep(2) 22.4 23.9 17.9 16.6 Table2.SlidingTestofRevolving andRetracting Duct,(d) Variation ofSlidinqDragForceforDustParticle Size;TestSte;}(4) ParticleSize('1)[10_m] WithoutDustRevolution [N] 23.9Retraction [N] 16.6 <52 23.9 16.6 53-125 19.0 20.9 125-250 14.6 17.9 250-420 11.3 20.4 420-590 12.2 20.5 590-840 6.3 20.9 840-1600 14.7 33.0 Mixed ('1)Dustamountis lxl0-_m_.9.3 22.2 NASA/CP--2002-211506 9
Direction of Operation Loading PositionTable3.Sliding TestofLinearConveyer, (a) Variation ofSliding DragForceafterRepeated Operation; TestStep(1) Horizontal Vertically Upward Center Eccentric on Eccentric on Center Eccentric UpperPart LowerPart Measurement Before After Before ('1) (*2) ('1) DragForce('1) 3.8 19.7 6.1 IN] ('1):Before100Operations without Dust (*2):After100Operations without DustAfter Before After Before After BeforeiAfter., (*2) ('1) (*2)__('1) ('2)_._± ('1) (_2)___, 52.1 4.0 10.6 10.2 10.2f12.3!24.0 ! Table3.Sliding TestofLinearConveyer, (b) _eration CheckunderDustEnvironment; TestStep_2) Particle Size <53 53-125 125-250 250-420 420-590DustAmount 1Direction ofGravityat  _Z-axis 10 O O 1 O 10 10 10 10 590-840Dust O O O O O O10 oO O O O OO O O o O O O O O O O O O O OOO OI 840-1600 1i lO oox(*2)__l Mixed 10 0 0 01 10 0 ONormal Operation x:Locked ('1):FortheDirection ofGravity, SeeFigure4(c).oi (*2):Locked atthefirstattempt, Normally operated atthesecond attempt. Direction of Qperation Loading PositionTable3.Sliding TestofLinearConveyer, (c) Variation ofSliding Drag_ForceafterOperation CheckunderDustEnvironment; TestSteE(_3)_ Horizontal Vertically Upward Measurement DragForce('1) x:Locked -•NoTestCenter Eccentric on Eccentric onUp_perPart LowerPart Before After Before/ AfteriBefore After -(_h--(*2)_ i_(_)____(__L_) .... 12.0,24.2 28.8!xil-i10.1 ('1):BeforeTestStep(2) (*2)Afterteststep(2)Center Eccentric BeforelAfter'Before After_)_ [('2)[_(_1)___ (*2)__....... _..... [9.7I Ii-- X NASA/CP--2002-211506 10
Dust Amount [10-6m 3] 10Table3.Sliding TestofLinearConveyer, (d) Variation ofSliding DragForceforDustParticle Size;TestStep(4) Dust Direction ofOperation Horizontal Vertically Upward Particle Size [10-6m] Without Dust Mixed <53 53-125 125-250 250-420 420-590 590-840Center 24.2 21.1 16.7 8.4 11.1 13.1 22.2 21.0 37.8 37.7 840-1600Eccentric onUpper Part 41.6 40.6 18.8 21.6 23.7 42.9 31.5 84.2 70.8Loading Position Eccentric onLower Part 10.1 8.5 16.8 4.8 7.4 !8.4 4.6! 18.3 !22.2 ,Center 9.7 23.2 9.3 12.9, 36.1 48.9 60.0 73.0 53.2'.Eccentric 21.3 29.0 x x ._ X x:Locked Steps(1)ofbothofthepartsresulted intheslidingdragforceincreasing astheoperation isrepeated, roughly speaking. Itshouldbenotedinsteps(4)ofbothofthepartsthatthedustofsmallparticle size mightdecrease thedrag,whichseemstobesimilartoafunction ofroller.Theslidingtestsresultsshowed thatthemechanism worked undermostofthedustconditions including excessive c'ases,andthatonlyin somecasesitdidnotwork,wherethedustamount isunrealistic ortheeccentric amount oftheforce application pointisunrealistic. Thetestsindicated theenvironmental limitation foroperation andthe necessary operating force. Pyrotechnic ShockTest Thecontainer shouldbekeptinvacuum inordernottoreducethesamples scientific value.Thecontainer suffersfourtypesofshockloadafteritissealed. Thefourtypesofshockare(1)capsule separation from spacecraft, (2)parachute jettison fromthecapsule, (3)parachute deployment, and(14)landing. Theshock levelsofthemareshowninFigure5.Theformertwoarecaused bypyrotechnic actuators, whichare installed inthereentrycapsule system. Thelattertwoshockenvironments arelowerthanthecompressive forcecapability ofthesealspringasshowninthefigure.Thecapsule separation shock(1)isenveloped in theparachute jettison shock(2).Thismeansthatthecontainer airtighthasonlytobeverified against the parachute jettison shock(2). Thehigh-frequency shockisapplied tothecontainer flange,andthevacuum inthecontainer ismonitored. Ahelium leakdetector isalsousedtomonitor insidethecontainer. Thecontainer wastestedbothin atmosphere andinheliumatmosphere. Thetestresultsaysthatthecontainer liddoesnotopenevenif theshockofparachute jettison isapplied. NASA/CP--2002-211506 11
0910000 1000 100 I 10 1 10If1 i,ii,,¢-,-!d-, r,E] : : I" !! Acceleration atSampler Container ','_ nsdetheReentry Capsule ,.F_ (1)Capsule Separation , _ (2)Parachute Jettison i _ (3)Parachute Deployment/ '' """ (4)Landing / SealSpringCapability 100 1000 10000 Frequency [Hz] Figure 5.Mechanical Environment ofReentry Capsule Conclusion Sampler, theasteroid sampling mechanism forMUSES-C, hasbeendeveloped andtested inprescribed environments. Duetoscientific requirements, onlytheselected lubricants areusable atthesurface of sliding parts,andthesurface coating ofstructure thatmaytouchsample hasbeenselected. Thefunction ofmechanisms hasbeenverified, andtheoperation limithasbeenobtained. Thesealofthesample container hasalsobeenverified. NASA/CP--2002-211506 12