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FullScaleLowPowerWindwardCommunityCollege–UniversityofHawaii2010‐2011
FullScaleLowPower(FSLP)Testfiles
Contents:
1 FSLPOverview2 RocSimResults3 EstimateofCG,StabilityMargin,andThrusttoWeightRatio4 MotorSpecifics5 Graphs
a. Accelerationb. Velocityc. Altitude
6 LaunchPadDesign
TeamSummary• UniversityofHawai’i–WindwardCampus• Hale‘Imiloa
45‐720Kea’ahalaRd.Kane’oheHawai’i96744
• Dr.JosephCiotti(PrincipleInvestigator)Dr.JacobHudson(TeamOfficial)HelenRapozo(ITSpecialist)KristiRossJoleenIwaniecToddEspositoPatrickLancasterJasmineMaru
LaunchVehicleSummary
• RocketName:LeoHano• Theteamrocketistobe121inchesinlength,witha6”diameter• TherocketisdesignedtoacceptaK780Rwith98‐75mmmotoradapter• Therocketisdesignedtohaveadualdeploymentrecoverysystem
incorporatinga42”droguedeployedatapogee,anda144”maintobedeployedat1000’altitude.
• 10/10railwithalaunchraillengthof14’• Nopayloadistobeflown
FullScaleLowPowerWindwardCommunityCollege–UniversityofHawaii2010‐2011
FullScaleLowPowerWindwardCommunityCollege–UniversityofHawaii2010‐2011
1 FLSPOverview
SuccessfulcompletionoftheUSLIprojectrequiresthataFull‐ScaleLow‐Poweredfighttest(i.e.aPrototypetest)beperformed.TimingforthetestiscontingentuponKaneoheMarineCorpsAirStation(KMCAS).ThemainreasonforthisisbecauseKMCASistheonlyfacilitywithalargeenoughinfrastructureforustoperformatestofthismagnitude.Thismeansthatthesafetyofourprelaunch,flight,andrecoveryareofthehighestpriority.Tohaveasuccessfulmissiontheteammustensurethatallsafetyrequirementsaremaintainedthroughoutthemission.Theteammustalsomeetallthefollowingcriteriabelow.MissionCriteria:
• Motorfunctionsproperly• Avionicsfunctionsproperly• Successfulrecoveryoftherocketandallitscomponents• Bothparachutesdeployed• Therocketiscompletelyintact• Theappropriatelevelsofsafetyaremaintainedthroughouttheentireprocess
ofpreparation,launch,flight,andrecoveryoftherocketToachieveanytypeofsuccessinthemission,therocketmusthavedeployedaparachuteandmustbeintactuponrecovery,meaningithastheabilitytobeconsideredflightreadyandmeetsallsafetyrequirementswithoutanyrepairsdoneit.Iftheteamdoesnothaveaparachutedeploymentandtherocketisnotintactuponrecovery,themissionwillbeconsideredafailure.ForFSLP,thereisnopartialsuccess.Propermotorselectionrequiresseveralconsiderations,asuitablethrusttoweightratio,andapredictedmaximumaltitudethatisabove1200feetinorderforthedualdeploymenttesttowork.Ourlimitedrecoveryfielddirectsthatwecannotgotofaroverthisheight.Furthermore,themilitarycedescontrolofitsairspaceovertotheFAAonthedaystheyopenituptocivilianoperations.Assuch,wemustkeepourflighttobelow2500feet.Motorselectionwasalsodependantonmotoravailability.Allthingsconsidered,thechoiceofmotorwasanAerotechK780R.Thisgivesusamaximumheightof1960feet,whichiswithinourflightconstraints.Ouronlyconcernisthatthethrusttoweightratioisonlyabout5.2atmaximum,and4.2onaverage,whichismarginal.Theflightprofilethatourrocketwillfollowisthestandarddualdeploymentroutine,andhasbeensimulated(undervariouslaunchconditions)onRockSim.Theflightwillbeginwiththeboostphase.TheK780Rmotorwillproduceanaveragethrustof~175lbs(givingusamaximumthrusttoweightratioof~5.2),withaburntimeof2.94seconds.Themaximumestimatedaccelerationis~10g’s(344ft/s/s)forabouta1/10ofasecond,withanaverageof~4.2g’swithanestimated
FullScaleLowPowerWindwardCommunityCollege–UniversityofHawaii2010‐2011
maximumspeedof222mile/hr(325ft/s).Atmotorburnout,therocketthenentersitscoastphase.Weexpecttherockettoreachapogee~12.3secondsafterlaunch.Atapogee,a42‐inchdroguechutewillbedeployed,yieldinganinitialdescentspeedof~82ft/s.Atanaltitudeof1000ft,a144‐inchmainchutewillbedeployed,slowingtherocketdescentrateof22ft/s,whichwebelievetobeasafedescentrate.Thetotalflightdurationisexpectedtobe~62seconds.2 RocSimResults
USLIROC2011–SimulationresultsEngineselection[K780R‐None]Simulationcontrolparameters
• Flightresolution:800.000000samples/second• Descentresolution:1.000000samples/second• Method:ExplicitEuler• Endthesimulationwhentherocketreachestheground.
Launchconditions
• Altitude:0.00000Ft.• Relativehumidity:50.000%• Temperature:80.000Deg.F• Pressure:29.9139In.
Windspeedmodel:Light(37MPH)• Lowwindspeed:3.0000MPH• Highwindspeed:7.9000MPH
Windturbulence:Fairlyconstantspeed(0.01)• Frequency:0.01000rad/second
• Windstartsataltitude:0.00000Ft.• Launchguideangle:0.000Deg.• Latitude:22.000Degrees
Launchguidedata:
• Launchguidelength:144.00000In.• Velocityatlaunchguidedeparture:53.5867ft/s• Thelaunchguidewasclearedat:0.559Seconds• Theuserspecifiedminimumvelocityforstableflight:43.9993ft/s• Minimumvelocityforstableflightreachedat:100.4338In.
FullScaleLowPowerWindwardCommunityCollege–UniversityofHawaii2010‐2011
Maxdatavalues:
• Maximumacceleration:Vertical(y):344.468Ft./s/sHorizontal(x):0.508Ft./s/sMagnitude:344.468Ft./s/s
• Maximumvelocity:Vertical(y):324.4643ft/s,Horizontal(x):6.2505ft/s,Magnitude:325.2313ft/s
• Maximumrangefromlaunchsite:208.87743Ft.• Maximumaltitude:1960.39075Ft.
Recoverysystemdata
• P:DrogueDeployedat:12.295Seconds• Velocityatdeployment:20.0897ft/s• Altitudeatdeployment:1960.39071Ft.• Rangeatdeployment:‐208.87743Ft.• P:MainParachuteDeployedat:25.906Seconds• Velocityatdeployment:81.3824ft/s• Altitudeatdeployment:999.92078Ft.• Rangeatdeployment:‐126.63283Ft.
Timedata
• Timetoburnout:3.064Sec.• Timetoapogee:12.295Sec.• Optimalejectiondelay:9.231Sec.
Landingdata
• Successfullanding• Timetolanding:61.296Sec.• Rangeatlanding:63.80652Ft.• Velocityatlanding:Vertical:‐28.1473ft/s,Horizontal:4.9767ft/s,
Magnitude:28.5839ft/sCompetitionsettingsCompetitionconditionsarenotinuseforthissimulation.
FullScaleLowPowerWindwardCommunityCollege–UniversityofHawaii2010‐2011
FullScaleLowPowerWindwardCommunityCollege–UniversityofHawaii2010‐2011
3 EstimateoftheCG,StabilityMargin,andThrusttoWeightRatioComponent Wt(oz) Est.CG(in)
€
(Wt.)r NoseCone 38 24 912GPSFlight 50 24 1200PayloadTube 40 43 1720Bulkhead 5 37 185Experiment 50(var.) 43 2150Drogue 8 51 408Bulkhead 5 49 245Coupler 20 55 1100AvionicsTube 30 64 1920Bulkhead 5 61 305AVAlCan 16 65 1040Avionics 35 65 2275Bulkhead 5 68 340Coupler 20 74 1480BoosterTube 80 97 7760MotorMount 50 106 5300Cen.Ring 3 91 273Main 20 83 1660Fin/Fin‐can 60 109 6540VDCAssembly 10 119 1190Cen.Ring 3 120 360MotorRetainer 5 120 600K560W 98 115 1127098‐75mmAdapter 9 115 1035
€
(Wt.) =∑ 665oz.
€
(Wt.)r =∑ 51,267oz‐in
Therefore:
€
CG =(Wt.)r∑(Wt.)∑
=51268665
= 77.09inchesfromthenoseconetip.
SincetheCenterofPressurehasbeencalculatedtobe90.25inches,ourstabilitymarginis…
Margin
€
=90.25 − 77.09
6.00=13.136.00
= 2.19
Thisindicatesthatourrocketwillbeslightlyover‐stable,withanaveragethrusttoweightratioof4.2,andamaximumof5.2.
FullScaleLowPowerWindwardCommunityCollege–UniversityofHawaii2010‐2011
4 MotorSpecifics
AeroTechK780 (DatafromThrustCurve.org)
Manufacturer: AeroTechEntered: May25,2006LastUpdated: May4,2009Mfr.Designation: K780RBrandName: K780RCommonName: K780MotorType: ReloadDiameter: 75.0mmLength: 39.5mmTotalweight: 2934gProp.Weight: 1268gCert.Org.: TripoliRocketryAssociation,Inc.Cert.designation: K794(85%)Cert.date: AverageThrust: 780.0NMaximumThrust: 965.0NTotalImpulse: 2371.0NsBurnTime: 3.0s
FullScaleLowPowerWindwardCommunityCollege–UniversityofHawaii2010‐2011
CaseInfo: 75/2560PropellantInfo: Redline
FullScaleLowPowerWindwardCommunityCollege–UniversityofHawaii2010‐2011
5a PlotofAccelerationversustimeforFSLP
Ascanbeseen,thepredictedaccelerationisfairlytypical;thereisarapidincreaseintherocketvelocityforthefirstsecond.Thereafter,theaccelerationbeginstodecreaseuntilnearburnout.Afterthat,dragforcesdominate,reducingtherocketspeedrapidly.Gravityfinallyreducestherocket’sverticalvelocitytozeroatapogee.
FullScaleLowPowerWindwardCommunityCollege–UniversityofHawaii2010‐2011
5b PlotofVelocityversustimeforFSLP
Ascanbeseen,theexpectedrocketvelocityisalsofairlytypical.Therocketisexpectedtoreachamaximumspeedofmach0.28(nowherenearsonic)shortlybeforemotorburnout.Thisisexpectedbecausethemotorthrustcurveshowstheburntoberegressiveatthattime.
FullScaleLowPowerWindwardCommunityCollege–UniversityofHawaii2010‐2011
5c PlotofAltitudeversustimeforFSLP
ThepredictedplotofthealtitudeversustimefortheFSLPlieswellwithinouroperationalconstraints,withburnoutcorrespondingtoapointofinflectionofthecurve.
FullScaleLowPowerWindwardCommunityCollege–UniversityofHawaii2010‐2011
7 LaunchPad
Asitstandsrightnow,thecosttosendthenecessarylaunchequipmenttotheUSLIlaunchsiteisprohibitivetosaytheleast.TheplanfortheUSLIlaunchisthatWCCUSLIteamwillbeusingtheUAHuntsvillelaunchpadequipment(theyhaveagreedtoletususeit).Nevertheless,inordertoperformaFSLPtest,WCCneedstofabricatealaunchpadanditsassociatedelectronics.Forthisendeavor,theAeroPACgrouphasbeenagreathelp.Oneoftheirmembershasdonatedasinglechannellaunchcontroller,whichhasbeenbasedoffoftheirmultiplelaunchcontroller(schematicsfollow).TheRocSimsimulationforourrocket,usingtheK780R,showedthatthebottomoftherocketreachedasafevelocityat100.4”(~8feet4inches).Thissuggestsalaunchraillengthof10feet(assumingarailbuttonseparationof18inches).However,duetoamarginalthrusttoweightratio,webelievethatalongerlaunchrailshouldbeused.Raillengthsof12to14feetarebeingdiscussed.Therailistobemadeofmediumextrudedmetaluni‐strutcapableofacceptingstandard10‐10railbuttons.Currently,constructionofalaunchpad,basedontheAeroPAClaunchpaddesign(plansfollow),isunderway.Uponcompletion,andbeforeuse,everyeffortwillbemadetoensurethatthecenterofgravityfortheloadedlaunchpadfallswithintheareadefinedbythebaseofsupport.
FullScaleLowPowerWindwardCommunityCollege–UniversityofHawaii2010‐2011
FullScaleLowPowerWindwardCommunityCollege–UniversityofHawaii2010‐2011
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