mechanically connectedtoanindividualarrayandsupportedonbearings.Eachofthetubesis separately drivenbyanindependent mechanism consisting ofa30°stepper motorwithathreestage planetary gearbox, apinionandspurgeardrivetrain,andthreemicroswitches forposition telemetry. The ADMjoinstotheCanister viaaboltcircleando-ringseal.TheADMislubricated withBraycote grease. TheGenesis contamination controlrequirements aremetbyventing theinterior ofthemechanism through thefloorofthecanister. Rotaryteflonsealsprevent ADMoutgassing intotheinteriorofthe canister. Additional Design Considerations Thecleanliness ofthedelivered FlightModelintegrated canister andinparticular theinteriorofthe canister iscriticaltothesuccess oftheGenesis mission. Allthematerial returned inthearraysandthe concentrator willbeassumed tobesolarwindsoitisessential tokeepcontaminants fromtheseultrapurematerials. Thisisaccomplished inavarietyofways.Thematerials inthecanister design, particularly withinthecanister interiorwerechosen tominimize contamination ofthesolarwindsamples andtomaximize theabilitytocleanthepayload hardware. Theonlyopening intheclosedcanister is through thefilter.Theprocessing sequence ofthecanister issetuptokeepthecanister interiorasclean asneeded. TheFlightModelintegrated canister isbuiltatJPLandundergoes bothvibration andthermal/vacuum qualification testingatthissubsystem level.Thecanister thengoestoJohnson SpaceCenter(JSC) whereitispartially disassembled andrigorously precision cleaned. Thecanister isreassembled ina Class10cleanroom. InFigure14,theCoverDriveMechanism isreinstalled aftercleaning atJSC. Personnel perform theoperation inaClass10cleanroom whileoutfitted inDryden suitswithHEPAfilters. Thehexagonal collectors arereplaced withnewpristine collectors. Thecanister isclosedandlockedin theultracleanroom atJSCanditisneverop-ened againuntilitisinspace. Thecanister ispurged with clean,drynitrogen fromthispointuntillaunchfairingcloseout. Integration withintheSRCandthe spacecraft takesplaceoutside theultracleanenvironment soitisimpossible toopenthecanister without contaminating thecollectors andtheconcentrator. Theonlywaytoverifytheflightelectrical interface between thespacecraft andtheintegrated canister iswiththe"NoOpen"functional tests. Conclusions Bothmechanisms haveinteresting designchallenges oftheirown.IntheLockRingMechanism, the rampprofile,thetorquerequired forlockingthering,andthelockringflexuredesigns allinteract. Keyto thedesignofthistypeofmechanism istheincorporation andcontrolofthestructural compliance (flexures) thatallowsacontrolled preload inthemetal-to-metal separable sealsurface. Thecapture rangeoftheLockRingrvTe_h-an_sm a-i_ditspush-offstroke areals6_irectly related. IntheCoverDrive Mechanism, incorporating boththetorquetubeandthecoverarmflexures posedaparticular problem. However, themostinteresting aspectofallisthecoupling between thetwomechanisms andbetween the mechanisms andthestructure. Thecanister sealisneeded because oftheextreme contamination requirements inthecanister interior. Theexistence ofthesealforcestheCoverDriveMechanism hinge linetothetopofthesealcrownheighttomaximize theactualcapture rangeoftheLockRingMechanism. Thishingelinelocation makesthecoverarmflexures necessary. Theforceneeded todeflectthecover armflexures addsdirectly tothepreload required fromtheLockRingMechanism whenclamping theseal interface. Thecanister c6verandbasestructure designdirectly influences theloadstransmitted across thesealinterface thereby affecting theLockRingMechanism design. Parameter changes inonearea duringdetailed designiterations quickly rippledthrough allthepayload designinteractions. Allthese interactions addedcomplexity totheoveralldesignproblem. 2O4