2017StudentSymposiumProceedings
November9,20179:00am-6:30pm
LaSellsStewartCenterAgProduction/AgLeadersRooms
OregonStateUniversity
featuringpresentationsfromNASAstudentinterns,fellows,researchscholarsandstudentteams
OregonNASASpaceGrantConsortium
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2017NASAStudentSymposium
HostedbyOregonNASASpaceGrantConsortium(OSGC)
November9,2017
© OregonSpaceGrantConsortium,2017
Therightofpublicationinprint,electronicandanyotherformandinanylanguage is reserved by OSGC. Short extracts from OSGC publicationsmay be reproduced without authorization provided that the completesource is clearly indicated. Editorial correspondence and requests topublish,reproduceortranslatethispublicationinpartorinwholeshouldbeaddressedto:
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PresentationSchedule
8-9am POSTERSESSIONSET-UP-Breakfastprovidedforpresenters
9-9:30am OPENPOSTERSESSION
9:30-10am KEYNOTESPEAKER-Mr.TorryJohnson,AssistantDeputyDirector,Hydrosphere&BiosphereScienceNASAGoddardSpaceFlightCenter
TIME Presenter
10:00am CalebTurner-PortlandStateUniversity-NASAMarshallSpaceFlightCenterInternshipTitle:PropulsionAnalysisofLunarLanderConcept
10:20amJamesBenbrook,RyanDomres,DagimGebretsadik,ChloeJordan,andJustinLuc-OregonStateUniversityOSGCUndergraduateTeamExperienceAwardProgramTitle:OregonStateRocketryTeamESRASpaceportAmericaCupCompetition
10:40am SamColosimo-UniversityofPortland-NASAGoddardSpaceFlightCenterInternshipTitle:SiliconX-RayOpticsManufacturing
11:00am AmyCaldwell-OregonStateUniversity-NASAMarshallSpaceFlightCenterInternshipTitle:CreatingtheAcquiescentRailTranslatorEquipmentforMassandInertialSupport(ARTEMIS)
11:20am BertrandDeChant,MarkMusil,andJacobTiller-PortlandStateUniversity-OSGCUndergraduateTeamExperienceTitle:PortlandStateAerospaceSocietyLiquidFuelEngineTestStand(LFETS)
11:40am MatthewLucasandAudreyVaughn-Linn-BentonCommunityCollege-HigherEdResearchAwardTitle:LaunchProceduresforOffshoreFlights
12:00pm LUNCH/NETWORKING/POSTERS-Foodandrefreshmentsprovidedforpresenters
1:00pmLeviWillmeth-OregonStateUniversity-NASA’sIndependentVerification&ValidationFacilityTitle:AdaptingNASAAvionicsSoftwareCommonlyUsedonRocketsandSatellites,toControlaCommerciallyAvailableDrone
1:20pm LouisDetweiler-SouthernOregonUniversity-NASAAmesResearchCenterTitle:ToolSupportforUASHazardRiskAssessment
1:40pm MichaelPolander-OregonStateUniversity-OSGCUndergraduateTeamExperienceAwardProgramTitle:OSU2017RockSat-XProgram-Hephaestus
2:00pmDianeDemchenko-PortlandStateUniversity-OSGCUndergraduateResearchFellowshipTitle:CreatingaGeneralAntiviral:TestingtheInhibitionofSpindle-ShapedVirus1andYellowFeverVirusbySilverNanoparticles
2:20pm MatthewMorse-OregonStateUniversity-NASAMarshallSpaceFlightCenterInternshipTitle:OrbitalClassNanosatelliteLaunchVehicleSpin-StabilizationSystem
2:40pm NinaCox,DanielFolkerts,andSavannahGrey-OregonCoastCommunityCollege-HigherEdResearchAwardTitle:UsingRadiosondestoDetectAtmosphericChangesDuringtheTotalSolarEclipse
3:00pm BREAK
3:20pm AlexFarias-PortlandStateUniversity-OSGCUndergraduateTeamExperienceAwardProgramTitle:PortlandStateAerospaceSocietyCompositeCryogenicFuelTank
3:40pm CharityWoodrum-UniversityofOregon-OSGCFacultyResearchAwardProgramTitle:EvolutioninSolitude:FieldGalaxiesfromHalftheAgeoftheUniversetothePresent
4:00pmMilesCurry-OregonStateUniversity-OSGCInternship:OregonSeaGrantSeacastProjectTitle:Seacast-APythonWebApplicationtoDisplayHighResolutionWeatherandOceanForecastModelsforOceanConsumers
4:20pmAlexanderChabert,ThomasManfredonia,andSavonSengsavanh-UniversityofPortlandOSGCUndergraduateTeamExperienceAwardTitle:Micro-RadialJetEngine
4:40pm AustinGulstrom-OregonStateUniversity-NASAGoddardSpaceFlightCenterInternshipTitle:AnalyticalSoftwareValidationforCompositeTechnology
5-6:30pm RECEPTION/NETWORKING/POSTERS-Foodandrefreshmentsprovided
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KeynoteAddressTorryAJohnsonAssistantDeputyDirectorforHydrosphere,Biosphere, andGeophysics,EarthSciencesDivisionNASAGoddardSpaceFlightCenterMr.TorryJohnsonhasworkedatGoddardSpaceFlightCentersince2003.Currently,Mr.Johnsonservesasthe Assistant Deputy Director for Hydrospheric and Biospheric Sciences within the Earth SciencesDivision.In this role, he oversees the fiscal andoperationalmatters of the organization.In addition,Mr.Johnson function as the Agency's Activity Manager for the Tribal College and University Project. Thisprojectintersects with the Office of Education and seeksto provideopportunities to engageAmericanIndian and Alaskan Native students/faculty inSTEM endeavors, building upon NASA's uniqueassets.Mr. Johnson’s special area of interest is PublicOutreach and Engagement and hasworkedwithprojectssuch asKnow Your Earth, a nationwide, multi-mission education & public outreach effort that seeks toexposethepublictoEarthScienceviamassmedia(billboardcampaignsandmovietheaterPSAs)andAdopta Pixel, a “citizen-science” effort aimed at getting the public involved in the collection of land coverimages.Healsolikestoserveasasciencefairjudgeandmentorhighschoolandundergraduatestudents.Mr. Johnson currently serves as an advisor for the NSF funded Integrated Geospatial Education andTechnology Training (iGETT), whichhelps two-year colleges meet the growing workforce need forgeospatialskills.
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AbstractsJamesBenbrook,RyanDomres,DagimGebretsadik,ChloeJordan,andJustinLucOregonStateUniversityOSGCUndergraduateTeamExperienceAwardProgramOregonStateRocketryTeamESRASpaceportAmericaCupCompetitionThe Spaceport America Cup (SAC) is an intercollegiate rocket engineering competition that provides aplatform for schools around theworld to design, build, and launch sounding rockets. The 2017 OregonStateRocketry(OSR)teamenteredintothestudentresearchedanddesignedadvancedcategory.Thegoalwas to reach a target altitude of 30,000 ft. above ground level while carrying a scientifically relevantpayload,andtorecovertherocketandpayloadafterlaunch.The team is comprised of mechanical, electrical and computer science engineering sub teams. Themechanicalsub-teamswereresponsibleforthedesignandconstructionoftheairvehiclestructure,motor,propellant,recoverysystemandpayload.The2017rockethasacarbonfiberbody,solidpropellantmotor,anddual stageCO2parachutedeployment. Thepayload is a fixedwing glider that is ejected at apogee,unrollsitswing,andcollectsCO2dataasitdescends.Theelectricalandcomputersciencesub-teamscollectandtelemeterflightdatabacktothegroundstation.Twotestlauncheswereperformedpriortocompetition.Eachtestlaunchhadfailuremodes,buteachonewas addressed and mitigated prior to the final launch. On June 22nd at Spaceport America the rocketreached25,283ft.AGL.Therocketandpayloadwere found inrelaunchcondition;however, thepayloadwing was still rolled so the functionality of the guidance system was inconclusive. The CO2 detectorfunctionednominallythroughouttheflight.TheOSRTeamplaced3rdinthe2017SAC.AmyCaldwell,OregonStateUniversityNASAMarshallSpaceFlightCenterCreatingtheAcquiescentRailTranslatorEquipmentforMassandInertialSupport(ARTEMIS)At NASA's Marshall Space Flight Center, the 86 square-meter solar sail, its deployer, and the masstranslation table of the Near-Earth Asteroid Scout Cube Satellite are in their final stages of design andtesting.Thiscubesatelliteanditscomponentsaredesignedtooperateinzerogravity,makingitchallengingtotestanyoftheirfunctionsonEarth.However,duetoitsfragility,themasstranslationtableisthemostdifficult to test because it would sustain a lot of damage if it was operated on the surface of Earth.Therefore,theprojectofdesigningandcreatingacustomsetuptoallowforthetestingofthiscomponentwas created. Over the term, a machine named ARTEMIS, an acronym for Acquiescent Rail TranslatorEquipmentforMassandInertialSupport,wasdesigned,drawn,andanalyzedinthecomputer-aideddesignsoftwarePTCCreo.ARTEMISwasthenconstructedon-siteintheFabricationLaboratory.Thefinalproductat the end of ten weeks was a functional machine that removes the mass load from the translationmechanism. The machine also allows for movement in the x and y directions at the discretion of thetranslation table with negligible resistance. Future developments of ARTEMIS will allow for the masstranslationtabletobetestedundervacuumconditionswithvaryingtemperaturesandtranslationrates.
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AlexanderChabert,ThomasManfredonia,andSavonSengsavanh,UniversityofPortlandOSGCUndergraduateTeamExperienceAwardProgramMicro-RadialJetEngineThe University of Portland Micro Radial Jet Engine Team (MJET) designed, manufactured and tested asmall-scalejetengineforongoinguseasauniversitylaboratoryexperiment.TheteamoffourMechanicalEngineering students (Alexander Chabert, Jake Johnston, Thomas Manfredonia and Savon Sengsavanh)startedwithanoverarchinganalysisoftheBraytoncycleandbrokedowndesignanddevelopmentcriteriainto five key elements: diffuser, compressor, combustor, turbine and nozzle. The goal was tomake theengineself-sustainingandachieveapproximately20poundsofthrust. Integraltoprojectsuccesswasthedivision of labor and specialization to both increase speed of the process as well as allow the team toacquireawidebreadthanddepthofknowledge.Eachmemberwasassignedaspecificsectionof the jetwithdesignandmanufacturingresponsibilitiesforthatelement.UtilizingUniversityofPortlandresourcesaswellasbenefitingfromindustryexpertiseandcontributions,mostnotablyBoeingGresham,BlountandPrecision Castparts, the teamwas able to construct and test the engine. Subsequent design teams willattempttopushtheengineintofulloperation.Theprojectwasanamazingopportunitytogainrealworlddesignexperiencewithinaerospace.TheprojectwouldnothavebeenpossiblewithoutTheUniversityofPortlandandOSGC’sassistance.Threeof thefourmembershavegraduated, twoarepursuingcareers inaerospace, one is attending the Colorado School of Mines PhD program specializing in Thermal FluidSciencesandthefourthisinROTCwithmilitarycareerplans.SamColosimo,UniversityofPortlandNASAGoddardSpaceFlightCenterSiliconX-RayOpticsManufacturingTheadvancementofX-rayastronomylargelydependsontechnologicaladvancesinthemanufacturingofX-rayoptics.FutureX-rayastronomymissionswillrequirethousandsofnearlyperfectsegmentstoproduceanX-rayoptical assemblywith<5arcsecondHPD (half-powerdiameter) resolving capability anda largephoton collecting area, a feat impossible to accomplish with traditional glass mirrors. To meet theserequirements, research has been done in developing time-efficient and cost-effective processes tomanufacturesingle-crystalsiliconmirrors.Single-crystalsiliconispreferredoverglassasamirrorsubstrateduetoitsstiffness,lackofinternalstress,lowerCTE(coefficientofthermalexpansion),andhigherthermalconductivity.Theperformanceofthetelescopeisnotonlydependentonhighqualitymirrors,butalsothefocus of themirror assembly. This poster details improvements to some of the sub-processes ormirrormanufacturing,aswellasthealignmentofthemirrorassembly.NinaCox,DanielFolkerts,andSavannahGrey,OregonCoastCommunityCollegeOregonSpaceGrantHigherEducationResearchAwardUsingRadiosondestoDetectAtmosphericChangesDuringtheTotalSolarEclipseThe purpose of our projectwas to identify anymeteorological anomalies in the atmosphere during theAugust 21, 2017 total solar eclipse.We collected data using latex balloons filledwith helium, several ofGraw’s DFM-09 radiosonde weather sensors, and Graw’s GS-U ground station. Our equipment tookmeteorologicalreadingsoftemperature,dewpoint,andpressure,aswellaswindspeedanddirection.Inthe weeks leading up to the eclipse we performed multiple test launches to ensure the integrity and
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accuracyofourequipment.Onthedayoftheeclipse,welaunchedtworadiosondesbeforeandtwoaftertotalitytomonitoranychangesintheatmospherethatmayhavebeencausedbytheastronomicalevent.Ourresultsindicatedthattherewerenosignificantmeteorologicalchangesasaresultoftheeclipse.Thedataremainedrelativelystableshortlybeforeandaftertotality,althoughtherewereslightchangesinthelocations of the surface inversion and tropopause. This was unexpected as terrestrial conditions hadappearedtochangedramaticallyduringtheeclipse,intermsoftemperature.Thisoverallprojectwilladdtothebuddingscienceofthestudyoftotalsolareclipsesandwillhopefullycontributetothesophisticationofaninternationalstandardforstudyingsuchcosmicevents.MilesCurry,OregonStateUniversityOregonStateUniversitySeaGrantSeacastFellowshipSeacast-APythonWebApplicationtoDisplayHighResolutionWeatherandOceanForecastModelsforOceanConsumersSeacastisawebapplicationthatdisplaysforecastedoceanandweathermodelsoftheOregonCoastandparts of the California and Washington Coast via mobile and desktop browsers. Two of the modelscurrently usedareproducedatOregon Stateby facultyof theCollegeof Earth,OceanandAtmosphericSciences(CEOAS)andarethehighestresolutionfortheirtypeanddomain.LocalOregonfishermanaccountfor the user base and frequently use the site to locate potential fishing areas. Interns are tasked withmaintain and updating the site with new features. This summer’s improvements included: support formodelswithlowerresolution,butlargerforecasteddateranges,toextendcurrentbasemodels; increasesitestabilitybycreatingmorereliabledownloadfunctions;improvingapplicationslogs;andalargerefactorofthecodebaseanddocumentationtoincreasedeveloperreadability.Presentationwillpresentonthesenewfeaturesaswellasdiscussthesiteasawhole.BertrandDeChant,MarkMusil,TaraPrevo,andJacobTiller,PortlandStateUniversityOSGCUndergraduateTeamExperienceAwardProgramPortlandStateAerospaceSocietyLiquidFuelEngineTestStand(LFETS)Testingisacriticalpartofdevelopinganewliquidpropellantengine.WhenthePortlandStateAerospaceSociety(PSAS)decidedtoswitchfromsolidtoliquidpropellantsfortheirhighaltitudeamateurrockets,theneedforasophisticatedbutreliableteststandbecameacriticalpathproject.TheLiquidFuelEngineTestStand (LFETS) will serve as a testing platform for PSAS' liquid propellant rocket motor hardwaredevelopment.Designedtobescalabletoamaximumenginethrustcapacityof10kN(2250lb),initialmotortestingwillbeona3Dprinted,2.2kNproofofconceptenginedesign.Theteststandhasfoursystems:ahigh-pressure Nitrogen pressurization system, a cryogenic liquid oxygen system, an isopropyl alcoholcompatible fuel system, and a spark torch ignition system. Plumbing systems have been designed formaximum reliability with built in fail safes. A custom electronics system is being built based on theMarionette open source data acquisition system. In the future, the LFETSwill also act as a test bed forintegrating future technologies, including an electric propellant pumping system and a cryogenic-compatible composite propellant tank. Besides providing critical test infrastructure for PSAS, LFETSprovides an outstanding learning opportunity for the students involved due to its collaborative, opensource,interdisciplinary,safetycritical,anddemandingnature.
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DianaDemchenko,PortlandStateUniversityOSGCUndergraduateResearchFellowshipCreatingaGeneralAntiviral:TestingtheInhibitionofSpindle-ShapedVirus1andYellowFeverVirusbySilverNanoparticlesBroad-spectrumantiviralswillprobablybeessentialforlong-durationmannedspacetravel.Recently,silvernanoparticles(AgNP),wereshowntoreducetheinfectiousabilityofanumberofvirusesandresistanceisunlikely to develop. Previous research has explored the inhibition effects of AgNPonHIV-1,Monkeypoxvirus,Tacaribevirus,andHepatitisB,andallofthemhaveconcludedthatsilverblockstheinfectiousabilityof each virus. Using quantitative plaque assays, I have tested the effects of different AgNP on two verydifferent viruses, the extremophile Spindle ShapedVirus 1 (SSV1) and the Yellow FeverVaccine (YFVax).SSV1 is inhibited by AgNP. The method of inhibition is still unknown. Further studies will explore themechanism or mechanisms of inhibition. The effects of modified AgNPs on these viruses will also betested.LouisDetweiler,SouthernOregonUniversityNASAAmesResearchCenterToolSupportforUASHazardRiskAssessmentTo enable unmanned aircraft systems (UAS) operations in the national airspace system, demonstratingcomplianceto federalaviationregulations (FARs) is required.CompliancetotheFARscanbeshownbyasafetycase,whichisanengineeringartifactpresentingthejustificationforsystemsafetyandevidenceofsafety risk management. Safety arguments form a core component of safety cases; however, theirproductioncanbecumbersomeandtimeconsumingastheymustbethoroughandcomprehensive.NASAAmesResearchCenterhasbeendevelopingtheAdvoCATEtoolsettoprovideautomationsupportfortheproduction of aviation safety cases. The main focus of this internship is to advance AdvoCATE byimplementing hazard and requirements analysis table editors. Hazard and requirements tables are anecessarycomponentofasafetycaseastheyprovideawaytodocumentanddisplaytherelevantsafetyhazardsandtheirposedriskstoUASoperations.Thecontentofthesetablesalsoincludehazardcausesandconsequences, likelihoods of hazard occurrence, consequence severity, residual likelihood, initial andresidual risk levels,alongwithhazardcontrolandmitigationrequirementsdevelopedatvarying levelsofdetail. Prior to this internship, such tableswere createdoutside of AdvoCATEdue towhich keeping thesafety case content consistent with the hazard analysis and the corresponding requirements was achallenge.Theadditionofthiscapabilityisasteptowardsclosingthisgap,which,inturn,willcontributetoeasierandmoreefficientdevelopmentofaviationsafetycases.AlexFarias,PortlandStateUniversityOSGCUndergraduateTeamExperienceAwardProgramPortlandStateAerospaceSocietyCompositeCryogenicFuelTankOverthepasttwoyears,thePortlandStateAerospaceSociety(PSAS)hasdevelopedtechnologyforaliquidfuel,highaltitudeamateurrocket.Thetransitionfromsolidtoliquidpropellantrequiredthedevelopmentof a prototype fuel tank that could hold a cryogenic propellant such as liquid oxygen. Traditionally,propellanttankswerefabricatedoutofmetal.Thegoalofthisprojectwastodesignatankusingcompositematerialtoimprovetherocket’sperformancebyreducingitsdrymass.Thetankwasmanufacturedusinga
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compressionmoldingtechniqueinwhichlayersofcarbonfiber,structuraladhesive,andhoneycombcorematerialwerelaidupontoaluminummatingringslinedwithathinfluoropolymerlinertoformacylindricalmodule.Thecompositesandwichislayeredsothecarbonfiberprovidesthetankwithstrengthintheaxialand tangential directions, while the honeycomb core provides strength in the radial direction. Thefluoropolymerlineractsasabarriertopreventthepropellantfromleakingintothecompositelayers.Endcapswereshrink-fitontobothendsofthemodule,compressingthelinerandcreatingaseal.Preliminaryhydrostatic burst test confirmed that the tank can perform at the desired operating pressure of 45 psi.Compressiontestdeterminedthata3’’diametermodulecanwithstanda9600lbaxialloadat-190°C.Inthefuture,pressurizedtestswithliquidnitrogenwillbeconductedtotestthecryogenictankatthecombinedthermalandpressureloadexpectedduringoperation.AustinGulstrom,OregonStateUniversityNASAGoddardSpaceFlightCenterAnalyticalSoftwareValidationforCompositeTechnologyComposites are two ormorematerials combined on amacroscopic scale, remaining distinct in the finalproduct,andinheritingmanyofthebestfeaturesofitsconstituents.Oneofthekeyfeaturesofcompositesaretheirmaterialproperties,suchastensilestrengthormodulusofelasticity.Unfortunately,thesecanbehardtoaccuratelydeterminewithoutextensivetestingofcoupons.DIGIMAT,specificallyDIGIMAT-VirtualAllowable (VA), is a relativelynewsoftwarewhosepurpose ispredictionof laminate compositematerialpropertiesthroughavarietyofuserinputssuchaslayup,environment,andlaminaproperties.Thepurposeof this studywas to test theaccuracyandprecisionofDIGIMATatmaking these theoreticalpredictions,specificallywhen thematerial inquestionpossessedahighvoidcontent. Severalpanelswerepreviouslyfabricatedat lowvacuum toensure existenceof voids,whileothers remained freeof flaws. From thesepanelstestcouponsforfibervolume,tension,compression,andshearweremanufacturedtobetestedandcomparedagainstDIGIMATpredictions.Uponcompletion,resultsshouldprovidestatisticalinformationastohowwellDIGIMATperformswiththepresenceofthesevoidsandunderidealcircumstances.RachelHausmann,OregonStateUniversityNASAJetPropulsionLaboratoryCreationoftheFinalHazardMapsfortheNextMarsMission:InSightLandingSite,ElysiumPlanitia,MarsInSightwillsendageophysicallandertoElysiumPlanitia,Mars,in2018.Weproducedhazardmapsderivedfrom surface characteristics to quantify landing success. Probability of success is constrained via landingsimulations based on the engineering constraints and final hazard map. Geospatial datasets weregeoreferenced in order of increasing resolution: MOLA elevation maps, 463 m/pixel; HRSC data, 12.5m/pixel; CTX 5–6m/pixel; and HiRISE 0.25–0.3m/pixels. Rock and photoclinometry derived slopemapscovering the final landing ellipsewere produced and georeferenced using theHiRISENoMAP tie points.Sincetheinitial launchplanin2016,moresurfacedatawascollectedandnewmosaickingmethodswereused to make the georeferencing process more efficient. These new methods will be applied to theproductionofMars2020hazardmapsandfutureMarsmissions.
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MatthewLucasandAudreyVaughn,Linn-BentonCommunityCollegeOregonSpaceGrantHigherEducationResearchAwardLaunchProceduresforOffshoreFlightsThe Linn-Benton Community College Space Exploration Team held two successful offshore high-altitudeballoonlaunchesfromthedeckoftheresearchvesselPacificStorm.ThepayloadfilmedtheumbracastedbythetotaleclipseasitpassedacrosstheOregoncoastlineonAugust21,2017.Assigningrolesandhavinga setproceduremade the launchprocessoperatemoreefficiently.Approximately tenonshore launcheswere conducted to rehearse procedures in preparation for the launch.During these launches,membersbecamemore familiar with their roles and the roles of others on the team to prepare for any and allsituationsthatmayoccur.Completinganoffshoreflightdiffersfromastandardonshorelaunchgiventhatthe sea produces various weather conditions such as; sizable waves, increased chance of precipitation,higherwindspeed,andthepossibilityof limitedvisibility.Seasickness, internetaccessibility,andoffshorecommunicationareamongotherfactors.Asuddenchangeinwinddirectioncausedatear inthe latexofthe balloon which caused the payload to not achieve the desired altitude. The launch did not achieve80,000feet,howevertheteamlearnedfromitssuccessesandfailures,andanticipatethatthenextlaunchwillbesuccessful.MatthewMorse,OregonStateUniversityNASAMarshallSpaceFlightCenterOrbitalClassNanosatelliteLaunchVehicleSpin-StabilizationSystemCost-effectivesmall launchvehiclesarehighlydesiredbyorganizations thatwishtoplaceCUBESATS intolow Earth orbits (LEO) without piggy backing off larger payloads. Spyder—a four stage small launchvehicle—is currently under development. In order to keep costs down, Spyder will avoid complex andexpensiveavionicsand instead implementa robust spin-stabilization system.Thisproject focuseson thedesign and development of Spyder’s 3-4 stage spin-up mechanism using standard hobby solid rocketmotors(SRMs).Motorsizinganalysisshowsthatatotal impulseof170-220Ns isrequiredtoachievethedesiredspinrateof4Hz.Duetoinherentlayoutconcerns,simultaneousignitionoftheSRMsiscrucialtopreventmissionfailureprecessionandnutationangles.MATLABsimulationsshowthatamotorfiringdelayno greater than 20 ms ensures that maximum nutation angles remain less than 10 degrees. CurrentdevelopmentofascaledSpaceShuttle-derivedignitioncircuitisunderway.Testingprocedureswillinvolveuse of a passive hemispherical air bearing with mass moments of inertia matching those of Spyder. AmyRIOunitwillcontroltheignitioncircuitandcollectmotiondatafromvariousinstruments.Theresultsofthe test are expected tomatch closelywith those derived from theMATLAB simulation.Manufacturingoptions for the final design are also under consideration to ensure the product remains light and costeffective.LindseyOberhelman,LauraQueen,andJonahRose,UniversityofOregonOSGCFacultyResearchAwardwithDr.ScottFisher/UOScientificCommissioningoftheRobbinsforUndergraduateResearchWepresentthecontinuationofourworkandresearchrelatedtothecommissioningandoperationsofanew telescope system at Pine Mountain Observatory (PMO). Throughout this past summer, our teaminstallednewSLOANfiltersonthe“Robbins,”a14-inchMeadeCassegraintelescope.Thetelescopeusesa
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research-qualityCCDcamerawitha focal lengthof 2.56 cm, the systemhasa field-of-viewof35x35arcminutesandapixelscaleof0.7.Building on our work from last season, we observed remotely with the Robbins telescope from theUniversityofOregoncampusinEugeneforthefirsttime.Thisimprovementcoupledwiththeinstallationofthenew filtershas allowedus tobegin collaboratingwithNASA’s StratosphericObservatory for InfraredAstronomy (SOFIA). We provided optical photometry of the Herbig stars AB Aurigae and MWC 758 tocompare to infraredobservationsmadewithSOFIA.Weperformeddifferentialphotometryandabsolutephotometry, using several standard stars to calculateour zeropointoffsets. To accomplish this taskourteam learnedhowtohowto reduceandstack imageswith theprofessional softwarepackages IRAFandAstroconda. In addition, we are currently developing our own image stacking software using theprogramminglanguage,Python.MichaelPolander,OregonStateUniversityOSGCUndergraduateTeamExperienceAwardProgramOSU2017RockSat-XProgram-HephaestusThe2017OSURockSat-Xteamsoughttodemonstratethatanautonomousroboticarmcouldsurviveharshlaunchconditionsandstillperformcomplexoperationsinthespaceenvironment.Toachievethisgoal, the12membersoftheteamweredivided into4subteams.Structures, formaterialselection and to design supports for the payload to endure launch conditions. Robotics, to design themechanical components of the robotic arm. Electronics, to design themicrocontroller that connects thepayloadcomponents.Software,toprogramthemicrocontrollertorunthepayload.OnAugust 21st 2017, the rocketwith theOSUpayloadwas successfully launchedand retrieved.Prior tolaunchingitwasdiscoveredthatthetimereventlinehadburnedoutonthemicrocontroller,preventingtheteamfromactivatingthearmduringflight.Inanefforttosalvagemissionobjectives,acodewaswrittentoactivatethecameratoperiodicallytakevideowhenpowerwasprovidedtotherocket.Uponretrieval,thecameraremainedfunctionalandseveralvideoclipswererecordedonthecamerasSDcard.Beforethecamera lostpower, itwasabletocapturetwoshortclipsof interest.Oneduring launchandonewhileinflight.Thestructuralcomponentsofthepayloadallreturnedwithnoobservabledamage.Themicrocontrollerandmotorsallretainedfunctionality.Itwasconcludedthatthetimereventlinedfailedduetorepeatedtestingwithoutproperprotectionofthecircuit. All other components chosen for the rocket performed to expectations and would be goodselectionsforfuturemissions.CalebTurner,PortlandStateUniversityNASAMarshallSpaceFlightCenterPropulsionAnalysisofLunarLanderConceptRoutineaccesstothelunarsurfaceforpayloadshasbeenidentifiedasajointNASAandcommercialspaceflightmissionstatementmovingintothefuture.Venturingintopublicandprivatepartnershipsforthisendgoalshouldallowamoreaffordablemarketforlunarspacetravelandscientificinquiry.Initialdesignofapropulsion system to support these robotic lander concepts has been undertaken by ER21 (LiquidPropulsion) utilizing the ROCETS (ROCket Engine Transient Simulation) software for the sizing ofcomponentsbasedoncustomerrequirements,aswellasspecifichardwareanalysisanddesignusingCADmodelingsoftwareand3Dprinttechnology.Throughconstructingtwopropulsionmodels,8klbfthruster
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and4x2.5klbfthruster,theinitialconstraintsofthisventurecanbebetterunderstoodtoaideinthejointdevelopment of the robotic lunar lander concept. Purely analytical models were generated to give abaselinesteadystateresponseofthepropulsionsystem.LeviWillmeth,OregonStateUniversityNASA’sIndependentVerification&ValidationFacilityAdaptingNASAAvionicsSoftwareCommonlyUsedonRocketsandSatellites,toControlaCommerciallyAvailableDroneNASA launches a lot of rockets and satellites,most ofwhich perform similar tasks such as sending backtelemetryorexperimentaldata,performingexperimentsormaintenance tasksona regular schedule,ormaking attitude adjustments. Instead of rewriting the software that controls these common tasks fromscratchforeverylaunch,NASAbeganusingasetofprogramscommonlycalledtheCoreFlightSystem(cFS)software.The cFS software includes a set of files that define the current computer and mission hardware, andanother set of modular ‘apps’ that are specific to the current mission. This allows NASA to run similarsoftwareoneverythingfromsoundingrockets,toCubeSats,oreventheJamesWebbSpaceTelescope.Thegoalof this internprojectwastoadaptcFStocontrolacommercialhobby-gradedrone.Thespecificdrone used ran on linux, included a wifi connection, and the manufacturer supported an applicationprogramming interface (API) to interactwith the hardware, but the sameprinciples could be applied toothermodels of drone. This was the continuation of an earlier research project that began at JohnsonSpaceCenter.CharityWoodrum,UniversityofOregonOSGCFacultyResearchAwardwithDr.ScottFisher/UOEvolutioninSolitude:FieldGalaxiesfromHalftheAgeoftheUniversetothePresentWe analyze the stellar populations and evolutionary history of bulge-dominated field galaxies atredshifts0.3<z<1.2aspartoftheGemini/HubbleSpaceTelescope(HST)GalaxyClusterProject(GCP).Highsignal-to-noise optical spectroscopy from theGeminiObservatory and imaging from theHSTare used toanalyzeatotalof43galaxies,focusingonthe30passivegalaxies inthesample.Usingthesize–massandvelocitydispersion–massrelationsforthepassivefieldgalaxieswefindnosignificantevolutionofsizesorvelocitydispersionsatagivendynamicalmassbetweenz~1andthepresent.WeestablishtheFundamentalPlaneandstudymass-to-light(M/L)ratios.TheM/Lversusdynamicalmassrelationshowsthatthepassivefield galaxies follow a relation with a steeper slope than the local comparison sample, consistent withcluster galaxies in the GCP atz=0.86. This steeper slope indicates that the formation redshift is massdependent,inagreementwith"downsizing,"meaningthatthelow-massgalaxiesformedtheirstarsmorerecentlywhile the high-mass galaxies formed theirs at higher redshift. The zero-point differences of thescaling relations for theM/Lratios imply a formation redshift ofzform=1.35(+0.10)(-0.07) for the passivefield galaxies. This is consistent with the(HdA+HgA)’ line index which implies a formation redshiftofzform=1.40(+0.60)(-0.18).
