TECHNICALMEMORANX’M No. 1210 - NASA · 2 Ntc}TMNos1210.,.. .....
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+ a) 4 . ,”,,:..,: ““ ji”. , ONALADtTISORY COMMITTEE I FORAERONAUTICS TECHNICAL MEMORANX’M No. 1210 DEVELOPMENT OF SPOILERCONTROI.SFOR REMOTE CONTROL OF FLYING MISSILES ,BYG.ErnstandM.Kramer Translation ofZWB Forschungsbericht Nr.1717,January1943 Washington ,. -*e e ~.-l March1949 A1:. ... &:”,.,: -.. -i .... .. https://ntrs.nasa.gov/search.jsp?R=20050028416 2018-08-29T19:18:21+00:00Z
Transcript of TECHNICALMEMORANX’M No. 1210 - NASA · 2 Ntc}TMNos1210.,.. .....
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ONALADtTISORYCOMMITTEEIFORAERONAUTICS
TECHNICALMEMORANX’M
No. 1210
DEVELOPMENT OF SPOILERCONTROI.SFOR REMOTE
CONTROL OF FLYING MISSILES
,BYG.ErnstandM. Kramer
TranslationofZWB ForschungsberichtNr.1717,January1943
Washington,. -*e e ~.-l
March1949 A1:....&:”,.,:-..-i.... ..
https://ntrs.nasa.gov/search.jsp?R=20050028416 2018-08-29T19:18:21+00:00Z
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TECHNICP.LMEM3RANIXMNO.121CI
,.... ,. .DEVIZLOEMENT.OFSPOILERCONTROLSFOR
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Thepresentreport.iie~swiththe.@er@m~cj c~structiv~jandinstrumentaldevelopmentofa spoilercontrolfor”remotecontrolofflyingmissiles.
1,.INTRODUCTION.
Themode’ofoperationofthespoiler.controlconsists,inprinciple,ofinduclngseparationofflowatanappropriate~ointof theairfoilbyELcontrollablespoilerandt~oughitintroduces,avariationint,helift,henced”contr~leffect.,Thespoileroontrolhasbecome.knownthroughtheattemptstoremovethedefectsofthenormalaileropcontro$of.airpbnes.(Seereferences1,2,end3.) As simpleandoonvfnolngasthe~oi.lerprincipleappearsatfirst,a nuderof“tiff.icultiesw,ereencofitemdduringthedevelopmentofa.apoilor~fleroncontrolf’dyn”ormalairplanes,whichuptonowpreventedits‘practicalapplication’.’,, ...,.,
,,~ntheremotecontrolofflyingmi,es+l?s,suchasbombs,qpecialconditionsezeihvolved,‘whlohagainposetthe”question ‘whetherornota spoilercontrol’”wouldQff,er‘anyadvantageoverthecpntrol’withconventtonaldontrol!~u@&ces;‘Attractive.characteristics,Qfthespoiler”are,inprincipl~,.,itslowpowerrequirement‘~ditslowinbr’tibjbothofwhic~re&ton.thefactthat,cornp’kredto.theoonvention~controlsurfacpa,‘bnlyVery,’.smallmas”ses(hingedspoilers)needtobeactuated.whfchcanbe ‘eq,eily designedwithneutralaero@ia@cbalance.‘.. ..“, ..—..—..., 1.
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2 Ntc}TMNos1210
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Oncea practicallyinertia-freecontroloflowpowerrequire-menti.savailable,substantialtechnicalsimplifications,particu-larlyinconnectionwithremotely controlledflyingmissiles,arepossible,whichcollectivelyhavea beneficialeffectonthespacerequired,theweight,thecostsandthooperationalsafetyofthecontrol.Practicedemandssimpleandrobustdevices.Hence,theattemptaC@theDVLtodevelopa spoilercontrolsuitableforremotelycontrolledflyingmissiles.,
..-Theaerodynamicandstructuraldevelopmentofa
elementuptoitspresentstageisdescribedanditsapplicationdiscussed.
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,.11.AERODYNAMICDEVELOPMENT,,, . .
syoilercontrolpossible
Frcmthevery firstitwasclearthatthedifficultiesofthedevelopmentandtbecompletionofa newtypeofcontrol hadtobesimplifiedbyreabonofthefactthata~over+-alldesignoftheflyingmissilewasclioeensothatthesamecontrolelementcould *beuniformlyutilizedforthecontrolaboutallthreeaxes,sothatnoseparatedevelopmentforaileron,elevator,andrudderwasrequired.TheresultWasa tail-unitdnn.zcture.ofthemissileaashownin vfigure1}consistingofSIXidenticalcontroldemerits.Topreventinterferenceeffectsandalsotesuppresstheangle-of-yaweffect,thecontrolelementswere,atfirst,fittedwithend”platos.
Knownuptokhenwasthemountingofa spoilerontheuppersurfaceofthewingatabout1~~percentofthechord(fig,3(&t)),Thisarrangementensuresadequatespoilereffecti~enessathighang~qsofattack,butunsatitifactoryatlowangles, $ince theangleso,fattaok”atthetailunitare $maIJbecauseofthedownvashofthewings,,and’because’constanteffectivenessofc’wtrclinthe.poslti?e&ndnegative:x%ngeofanglea,ia&pePa%i,veja thick8ymmetrica~”profi16was”chosenfirstforthecbn$rol”element(25~~~c6ntWickwiththemsximumthigkneesqt!l.Opercentofthechord)anda spoiler”providedontheupperandlowersurface(Zigs,3(b)”and14).Testsestablishedtheposttionofthespoilerofmqximuw:efficiencyatabout50percentofthewj.ngchord.:Inviewofcmistruction.diffic+.tiesonlyone””spoilerwidth,,50pproentofthocontrol elementspan,waschosenatfirst,... . ...
Thefun&mentalbehaviorofsueh:~sppil~~1,sindicatedinfigure2, Itisseenhowupto.a certains~oilerheightthespoileri’sifioffcictive”(bouixlary-lqyereffect)apdfrequentlye,venproducesa slightcountereffectfollowin$a“steeprise.
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.... .inactionuntil,aftercorn@etebreakdown~fflow$theeffectofafurtherincrease in spoiler heightissmall’.!I@eheight‘atwhichpracticallyW aerodynamicactionisattained.,, ishereinaftertermedthe“requiredspoilerheight’’azzdtliFheightatwhichnopositiveaction occure yet, @e “permissiblespoi+erheight.”.’3.
Thespoilerpathsrequiredprovedthemselvesko greatforthearrangementofFigure3(a)andforelectricaloperation;thatis.,thepowerrequiredandthoinertiaofthespoilerdidnotyetper@tihesubsequentlydescribedext~melysimpleremoteccmtroldesign.Atthisstageofdevelopment‘thefollowing reflectionresultedinsomeprogress(fig.3(c)):”byconnectingthe”spoilersofbothprofilesidesandlettingtheminrestpositionex~efidtheprofilebythepermissiblespoilerheightplushalfthespdlerpath,ityield&foreach&gnetonly”h~thel,ift,.that.is,atleasta doubledratingfactor
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Theimprovementissecuredbysnincreaseinaerodynamicresistanceatneutralspoilersetting,hence,applicableonlywherethedragoftieccmtrolis unimportsnt”(reference4).
Iftiedevelop.ment,knd‘tivolveda controlelementfornormalflyingSpeeti,+, tinsn”’&earrangementoffigure”3(c)would “havegivensatisfactory.reeults,sinceitaffordedpracticallyusefulspoilerpathsevenatlowMachnumbers(M<o.6).Butthedesignproblemonwhichthecontrolwastobeuqedcalledfora speedrangestartingat M% 0.3 andulthateQ..‘.+extendingbeyoqdsonicvelocity.E!xperimenttiathighflowvelocitydiscloseda relationshipbetweentherequiredandthepermissiblespoilerheightandtheMachnmiberinthesensethatbothvaluesdecreaseathighMkchnruibers;thatis,lessheiglhtisnecessaryathighMachnumberstosecurecomdete
4 separati~offlow,but-elsoo&ypermissible,ifnodistuf%anceisisshowninfigure& onthebasisu showsthecriticelMachnumberat
a lesserspoilerheighti=tooccur.Thisrelationshipoftestdata.F@,u?e4 S.hOwhichtheflow,evenwithout
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spoiler,breaksa~y fromthe,rearportionoftheprof$le~hence)wherethecontiolfallsforaercxiynamicreasons, < ,,., .,
‘ Atthisstagea waytoremovethese’difficulti~~wasfoundintheaerod=io fixingofthebodydesign.The considerationinitiatingthisimprovementrested’ontheobservationthateven. .atthehighestMachnumberinvolvedfortheparticularprofilesmallspoiler,heightawerestillconsistentlyovercomewithout.dis’turbance.Accordingly,ithadtobepossibleto-increasetlieperrriimible,thatis,nondisturbingspoilerheight(in,@nsoftheorigj.nalprofilecontour),whenthespoilerisfdiredinneutralposition,thatis,givenanaergdyha~ioally”beneficialprofilestepatthespot~erlocation(fig,3(d)),Such_aprofilestepprotrudinginthehighestpo@t‘of.th6stepwasboundtomakethespollormoreefficientbecauseit”~wersthethicknessoftheboundarylayerand.producc%”ahigherincreadeofspeed.Theonlyprcblemwasto.findthehei~t,ofthisstepwithoutinducingseparationatthehighestMach.n~b_erspermissibleforthepartic~larProfile.Figure5representstheresul.tforthebeststepadaptedtothh profile.Cquparison.oftheresults,
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withandwithoutstep,disclosesthemarkedimprovm_entsecuredbythestep(fig.6). Therequiredspoilerpathwasreducedtoaboutonethirdofthevaluewithoutstep(reference~).
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Aside”fromtheprincipalimprovementofthespoiJ.erthemud.meansforreducingtheMacheffect-suchasreducingprofilethick*nessandcamber-weretestedstepbystepand&&[email protected]~hicknesaof~ percentwith40percentchordlocationofma@numthicknesswasmodifi.edbyanextensionina,16.6-percent-proffie.~i~ thic~es’s”at.63perctitofthechord,we prc?’~lscambernearthetrailinge-tiebeingremovedbyappropriatelyinc:se~ed.trailtig-edgp.tiicbess(fig.7).Figures4, 5,and6 indicatemeasurements,withthisprof,ile,!l?he.’fncreaseintra~ling-edqe thj.ckness is involvedonlywherethead.ditiomilresistanceofthecontrulplaysnopart”,‘-~sewhpre&6’thick6nin.& -—upofthetrailingedgemustbereplacedbyaninc,reaseinprofilechord.
Ittooka numberofpreliminaryteststofinda sulta~leshapeoftheswept-backcontrolelement.Atfj.rsttheelement —wassweptback,asa whole(fig.8)anditwasfoundthatthesweepbackmakesthespoil.er”veryquicklyineffective.At 30°sweepbackofthetotalfin,thespanofspo$lerhadtobedoubledandthedeflectionincreasedhy~ percentthcome . —anywhereueartheeffectoftheoriginalelement.At45°sweepbacknoappreciableactionisattai,~bleeyenwithdoubleddeflection,Anyhopeofworthwhileincreaseinthecritical
..vMachnumberbasedonthesweepbaokwasabandoned.
5NACATMNo.2210
Facedbyth&sefacts,thefindesign(fig.9), waschosen;theleadingedgehada &jOsweqp,bac~,~hp,enddiskintheforwardportionof~~%.profilewasremoveda&l”th&outeredgesuitabl$’rbtmded‘off.Thethenuhrestrictmd‘lateralflow-offtogetherwiththe45°swept+%ackl$a#ingedge”andtheadditionaldecreaseinprofilethicknessof$h~::$niidti)partpr~ducedfavorableapproachflow-conditions.ButastherequiredcriticalMaciifiber’couldstillDotbereachedwiththisarran&ment,the trailingedgowasthickenedupToreandSQthefuhdainentalbehavioroffigure10ascertained;thatis,a thicktrailingedgepromisGsadequatespoilereffectivenessbeyondthet%~tragge~subsonicwindtunnelspermitmeasurements@v upto “M%0,9),a thintrailingedgosufficienteffectiveqosswithintherangeofmeasurement.,Thesame’holdsfor”acorrespondingvar3ationoftheheightofthestep’(fig.11)althoughnotto.thesameextent..Thenextstageofdevelopmentinvolvedthesteady”variationofthetrailing~dge”thicknessandthw’stepkei~htwithinthespen”ofthecontrolelernentj’whichyielda practlcalcontrolcharac-:’.teristic’forhighandlowMachnumberg,sincethecharacteristicofthediffbreritpro~ilesissuperposed.Asthesuperpositionisattheexperjsoofcontrolelementauction,itmaynotbe “pushedbeyondthereqtiiromentsfordesignaccuracyandreac.tlon’timeoftheparticularmissile.Figure12presentstheresult““”~ofa measurement“on&controlelementwithcontinuouslyvaryi~trailing-edgethicknessandheightofstep.Comparisonwith-fi.~e6 disploseqtheextehsio~ofthepracticalspeedrange’“ “at the.eXpo”nSeoftheaction(reference6)0 . .
.“. .Inthemeasurementsrepree~ntedinfigures4,5,6, 10,.11~”-
and12,thesfioiler“wasreproducedbysuperimposedangles.The :effectoftheAlothecossaryfortheexitofthespoilerfrcm .theprofileconteurisitiicatedirifigure13, ItipseenthatthesW% smoothestheactioncurves,thatis,theactionpeak .●ccurringatcertainMaclInumbersismoderatedand’a?wacticallymoreusefulcharacteristicisattained. .- ., .... ,.,, ,.
Themeasurementsforthef@re& k,5,6,10,11,E, 1;, -a~d24arereproducedonlyforangle‘ofattacka = 00,,:sincethe” “’”h-~y dematidsonthehigh-spesdtunnelOftheD~ permittedrid””’-‘systematicvtiiationovertheangle-of-attack.range.Semplidgat a= 3° and a= 5° disclosed’noappreciablerelationbetweenspoileractionandangleofAttack..
A controlelwientdesfghedon thisbasiswasflight-tested(twoflighttests)andproved~tisfactorybeyondthetestrangeof’”thehigh-speedtunnel’uptktheterminalvelocityof’ssymetem’per”~edond:redchedthus:far,ttiat”j.s,”upto”aMach.numberaf0.98. ,..,
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III.CONSTRUCTIONOFSPOILER~
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Figurelk’raprese~tsa sedi.gn&drawingofthe.speilertendered%7theDVLin1939toa manufacturerfora missiloof2.5Wkilogramstotalweight:figure15“show8thecorrespondingcontrolelement~acctidingtothestateofd.e~elowefitatthatt~’.
Thee~ement“(fig.16)consistsinbothcasesoftwobell-shapedmagnetsandtheoscl”llatinga~.tfie..l?etveen&h.e~g~ts>thecasing,andtheelasticallysupportedparallellMca$e.Allrnovingpartsweredesignedfor minimuqweight.Inthefirstversion.thespoilercasingsta?npad”fdomO.~millimetersheetiron, Thesafeloadingofthespoilerplatewas10kil~grams.ThQtotalweightofthemovingpartsamou~~e~toabout50grams.Fcra spoileryathof~3,mi121rneterstQiselementchangesoverfromcompletedeflehionQfonesideto”thetitherinabout 1/100 second,providedthatmagneticl.ag”i~avoidedbyappropriato~ydesfgnednmgneticcircuit”.’Thp.p&@,inpu>requiredis5watts,andthesmallest~gneticelev8t@”forGe~”.0.3kilogramsThespoileris-aerodynamicallyiqd}fferen%; *“-thatia,thereisnomeamreablevariationoftheactWti%-
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forceoftkespoilerbyaerodynamicforceswithina djmb.?nicpressurerangeofO toXOO kilogramspermet8r2t._-,: v_,..
Essentialwastheproblemofthe’neoessary.,[email protected]&giv$g~p,@lerpath.Sincenodifficulti,eaareinvolvedi?fhddesigq,ofa:n.aer~dynamicallyindifferent’spoiler,,itrequires,ip~rinciple, onlythemagneticforcewhich,safelyovercoyestheelast$cresto.rjngforcedof.thefrictionless~rallel;lfti~ge.’.,~herigidityoftheelasticparallellinkageitself~,isgovernedlargelyhytheohang~verperiod.rbquitiedandthe$levat.ormass~s___ .... ,:
‘Thefirstversion(fig,~6)wasdeteloped&& ~h&epointsofview.T~t is,itwas’aerodynmgicallyneutral~theparallellinkageavoidedeverybearingfriction;a hot-airhe~tingsystemexhaustingatthespoilers~ots,pre~eti%d.ioingandpenetrationoff’creigno%jeotsw“ithincertainltmi{s’;andthema$~ticelevatorforceof0.3kilogrammin@~ valuewas~afalyableto.overcopwtheelasticforcesofthe~alleltlin?mge.,
i,,,.,,~,Altho&hextensiveflighttesti~’”ofthiscontrol element
hassofargivennboccasiafori$,j.tmaybeobjectedthatpenetratingdirt.uightcausethespoilertostlokor.atleastimpedsitsfreedcmofmovemezit.TheIN%hasthereforecheckedthewaysinwhichtheoperatingsafetyofthespoilercatibe
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fo~ingwithoutvitiatingtheother.alreadyattainedperformances.‘Onepossibilityconsistsinimprowingthemagneticsystemofthespoilerbychangingfrcmflattodippingarmat~e(fig.1~).Underotherwiseidenticalassump-tionstheratioofactuatingforcetopowerrequiredcanb?raisedbyaboutfourt~s thevalue.
.. ..-.Butanincreaseinelevatorforcealoneisnotcapableof
preventinganobstructionofthespoilerthroughpenetrating -dirt;thereforetheDVLcheckedthisproblemfromtheconstructivesideandreachedthesolutionrepresentedinfigure18, Inthisconstructivesolution theedgesoftheprofilestep,betweenwhichthespoilermovesatabout1millimeter“clearance~“ayedesignedoomblikeofelastlc”mater.ial~~throughwhicha s’ticki&oftheelevatorduetopenetrationof“foreignbodies”is’g~evented.Thedesign.oftheteethoftheelasticCombensuresade@aterigidityrelativetotheappliedairIoads.Figure18alsoshowsanorigi~,llynotprovidedhousingofthema4netslds. Pene- .tratingdirtcanthusnotobetructthemagnetamatureandcaWe”1sticking,atthespoilevslots,Stncetheelasticsupportofthe-.elevatorwasfromtheveryfirstinsensitivetodirt,allsensit~vepointsofthespoileh+rethusprotectedandthedangertooperatirgsafetyduetodirtisprecluded.(Seereference 7.)’ ~ .,
ConsideringthdttheweightofthemovingpartsCE!I!stillb~’..considerablydecreasedbytheuseoflightalloysandinthe “latestversionthespoilerpathwasloweredfrom~s millimetersto*2 millimeters,itse,emsentirelypossibletodesigna spoilerelement “ofthedescribedorderofmagnitudewithl-wattto2-watthorsepowerforabout5/1000secondswitch+vertime.
~, POSSD3LJZAPPLICATIONSOFA pRACTICuyNON-INFRTIAL
ELEVATORWIT3LOW-POWERREQUIREMWT.-.-...
a.RemoteControlofFlyingMissiles,.
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Theuseofthepracticallyinertia-freq,elev@oronremotely,controlledflyingmissilesaffor@&fundamental-simplificationoftheremotecontrol,Thenormalelevatormust,withregardtoitsinertia,be controlledinrelationt.othedeflection; ‘thatis,toeachsignal(orccamand)oftheremotecontrol therecorrespondsa definiteelevatordeflec$,ion.A continuousvariationoftheelevatoractionth&eforerequiresa devicethattransfomnstheoncomiugelectricccpmandincorrespondingelevatasettings.
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8 NACJI.TMNo.1210
Onthepracticallyncn-inertialelevator,however,evmy ,desiredintermediateyalueofelevatoractioncazibeformed .froma suitabletimesequenceof#’ullelevatordeflections(fig.19).Tbosolepromiseis.thatthefrequencyoftheperiodicelevatorchangeischosenlargeenoughsothattheflyingmissile,owingtoitsLownaturalfrequency,transmitstheperiodicallyrayidlyvaryingfullelevatordeflectionssatiefactori.ly.Sucha controlt~ereforerequiresforcon-sistentvariationofoontrol act~onnointermediatedevicefortransformingtheorderinthedesiredelevatorsetting,aethepracticallyinertia-free“elevatorbyutilizationoftheinertiaoftheflyingrnjssiletakesoverthetransfomnat$onitself.Inotherwords,onthepracticallyinertia-freeelevator -theconsistentcoritrolincontrasttotheelevatorafflictedwithinertiarequiresnomoreeffortt~ [email protected]@e llyeslI- ~%or)control.‘Thusthereceivercanbec,utindirectattheelevatorasinthesimple~~on- off!’c~ntrol.(re?e~ence8). _.
Thepreviouslydescribedspoilermec&nism(fig.16)wasinstalledona flyingmissileof1500kilogramstotal-weightandthereceivercutindirectattbeelevqtor.Themodulationfrequencywas5 Hz;thema$xhmunnatural,frequency.ofthemissile,about1 Hz. Themeasurementsindicatedsatisfactoryfunctioningofthecontrolandextensiveflighttestsdisclosednoobjections{reference11).
b.ArtificialStabilizationofFlyingMissilee
Remotelycontrolledflyingmissilesfrequentlyrequiroartificialstabilizationofonebodyaxis,preferablythelongi-tudinalaxis,whentheygointentionallyorunintentionallyina.dive,becausethopureaerodynamicstabilizationofthelongi-tudinalaxis- duet.ogravity- failsina .yerticaldive.Thesimplestformofsuchanartificialstabilizationoftihelongi-tudinalaxisconsistsinconneot.inga “position”gyroscopeintheaileron.TheelementaryformofstabilizationisfndicatedwhenthealwaysavailableaibdampingissufficienttodampoutexternaldisturbancesquickenoughandtheelevatorreversalLintervalisshortenough’sothatthephasedisplacementbetweentheccmuandofthegyroscopeandtheresponsetothecommandbytheelevatorresultsinlowandpermissibleamplitudesofthestationaryrollingoscillationaccompanyingthistype--ofstabUf-—zation.
Foranabmptconnectingcontrol correspondingt~-thespoilerthestationaryamplitudeoftherolloscillationwith
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max~umvalue(m@).
At ttieintervalbetweenswitch-overcommandof~cacopeandactualrovemulofailort-tnmomeat(s)
,-~ % : ,,aerodynamicconstantofdampi~~lnro~ (mkgs)at @ = 1)
,Thenecessaryaileronmomentandtheattainableaerodynamic
dampi~:inroll~areusualiyfixedwithinmrzmwMmite for eachproject”..Buttheswitohing-overperibdcan beconsiderably.loweredwiththeintroductionofthespoilerInplaceof.the~normaloontrol.ThisexplainsW4Ythesimples~formofdabili-” - —zationofthelongitudinalaxisbypo8itiongyroeoopeanda~ler.onwiththespoilarisapplicableevenincbseswhereWiththeuseofa po~malcontrolthiswould,notbepermissible.. .’” .,
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Inthenumericalcomparisonofthispossibility& specificpro~ectsitistobebornefnmindth&tthenormalelevator“2aerodynamicallycouplesal.most.freefrominertia,whilethe I
spoilerhasanaerodynamiclag(reference3), Theidealvaluefortheairtightspoileris .
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thegainsecuredonthemechanical.sidea little.Innecessitytheaerodynamicinertiacanbeconsiderablywithoutotherdrawbacksb.ytheinterrupterDermeablo
toair(references,9,and12),- ‘- ‘ ,
c.ArtificialStabilizationofControlDirection
Onflyingmissileswithaxiallysymmetricaleffectivewingsystem,suchascrcmeorannularwings,thestabilixtionofthelongitudinalaxiscanbeavoidedincertainuond-itionsinfavorofstabilizationofthecontroldirection.Forinstance,ona bombsuchasinfigure20, it is completelyimmaterialwhetherthemissileturnsaboutitslongitudinalaxleinf13.giltormaintainsa certainposition.Thesoleessentialisthattherequiredcontroldireotionbemaintainedindependentofthe ‘ . -rotation,Wat is,atanyinstantassuredbyactuationofthecorrectelevator.Such”’acontro>requires-n~ail~rbn,butmerelya positiongyroscopefittedwithan.elev~toz.selector(fig.21),hookedupcorrectl.yinthe controloftheflyingmissile.To obtainylththetwocontroldirectionsprescribed’bythetailunitanexactpositionoftheresulttngcontrol
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directions without.additionalequipment,themisafl.lemustturnfastenoughthro~ correspondingtwistofthewingincidenceandthusgivea satisfactoryaveragevalue formation.adaptedto wthedurationoftheccmmmd.Thepositiongyroscopeissoconnectedbetweenreceiverandinterruptereleqentsthat,forinstance,atthesimplestversion(fig.21) theelevatorremainsswitchedonaslongasitremainsinthequadrantof&’j”whilethemissileturns.Ifthemissileturns further,thegyrostabilizedcollectoractuatestheelevatorente~lnginthesequadrants.Inthedesignofthecollectoroffigure21,theadaptionefthecontro~ directiontotheexpectedd.@ectionisstillsteppedvetiya&u.ptlyandcorrespondsinnowaytothetheoreticallyrequiredsinelaw.Inthearrangementoffigures22and23thaadaptationtothetheoreticallyrequiredsinusoidalforcedistributionisfurtheradvancedandsufficient,asa rule,forpracticaldemandsincc@binaticnwiththestatioiumyrotationaboutthelongitudinal.axis.
Theuseofa normalelevatorwiththiscontrolintroducesdifficultiesduetotherelativelygreati~ertiaoftheelevator,whilethespoilercontrolwithitslowedinertiausuallyoffersnoobstacletotheapplicationoftheartificialstabilizationofthecontroldirection.Onecanevengofurtherandsuperimposetheshnplestrsmote.controlwiththeartificialstabilizationofthecontroldirection,whichthengivesth~”simplest~ginable
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stabilizedremotecontrolforaxiallysymmetricalsyst~, Thiscontrolrequiresonlythereceiver
effectivewingailda pOBi$$06.
11
~oscope;aileron,dampinggyroscope,camandtransmitterfortheelevatorsand,.incaseofnecessity,theservanotoroftheelevators areeliminatedthroughutilizationofthelowinertiaand thesmallpowerrequirementsofthespoilers.Sinceapositiongyroscopeinitufunctioningissubstantially’lesssusceptibletorevolutionsperminutedecreasethana dampinggyroscope,thepreviouslystartedgyroscopecan,forshortflights,bemadetorunfree.Theeliminationofthedampinggyroscopeinthiscasealsoobviatesthegyroscopebatteryandthegyroscopetransformer(referenoe 2.0).Theunusually low powerrequiredofthecontrolandtheabsenceofallauxilj.aryequipmentmakeitpcssibletousebatteriesoflargestoragecapacity,whichfulfillsanurgentwishofpractice.Th3srotatorycoptrolhastheaddedpropertyofremovingtrimmingerrorsduetodesigndefectsinconsequenceofrotationofthewholemissile.
Allofthesefactorsdescribedwererealizedina subsequentdevelopmentofthe1500kilogramrnisoile(fig.20).Itsmaximum
.’. rateofrevolutionwaschosenat1 revolutionyersecond-.Thesimpledesignisrepresentedinthewiringdiagmm (fig.21).
●
V.AERODYNMK!RESISTANCEOFTEESPOILERCONTROL
Forreasonsofprincipletheopinionmaybeheldthatthespoilorcentrolcouldachieveimportanceonlywhentheaerodynamicresistanceofthecontrolisofno significanceorevendesired(thatis,forinferiorglidersordivingmissiles).Forappraisalofthisproblem,thelift/dra&ratio(Aca/A~r)of’thecoritrolelementoffigures7 and7 isshownplottedagainsttheMachnumberinfigure24;A% istheadditionaldragatfullspoilerdeflectionoverthedragwithoutspoiler,thatis,thesumofinduceddragandadditionaldragproducedbyseparationofflow;Aca istheliftproducedbythespoiler.Itisseen thata suitablespoilerarrangementattainsa lift/dragratioofover4:1evenfortheunfavorableaspectratiooftheexploredoontrolelement.Thespoilorcan,ofcourse,besocontrolledalsoby increasingthespoilerpathsthatItdisappearsintheprofilewheninneutralposition,henceproduoesnoadditionaldrag.Moreoverjitisknownfromearlierexperimentsthattheaerodynamicresistance(andtheaerodynamicswitch-oyerperiod)ofthenormalspoilercanbeimprovodwithoutlossofefficiencyby“properperforatinginthespoilerplates(refWences12and9)w Furthermore,
9
ITi,ci.TMNO. I21O12
fora missilewithgood‘“L/Da moiefavoz%iieaspect-ratioofthex
controlelementwillbe.ohose,nthaninthe“presentcaseandthecited.thickeningupoftheprofilet~ailinged’ger&placedbyacorrespondingIe@heningofthe2rof~lecOtheryossibtlitiesofloweringtheadditionaldragofthecontrolincludeincrea$ed
—
fuselage length~hence,reducedtall-planerequirtien~,andaubsti-tutionofoneoftheconyehtio-1two-axescontrolfor~ee-a~es...control. -.,
II . —Transl&t@byJ*Vamie.r “ ~ , ......NatiomlAdvisoryCcmmittee‘ .- ~
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2.
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3.2.
IamERENms
Weick,F-E.,So&, H-A.,andGough,M*N.: Atbn oftheLateralControlCharacteristicsofandVariousSpoilerswithDifferentAmountsofNACARep.No.&94,1934.
Weick,F● E.,endWenzinger,C.J,: preliminaryRollingMomentsObtainedwithSpoilersonBoth
13
FlightInvest@a-ShortWideAileronsWingDihedral.
IiwestigationofSlottedandPlain
Wings● NACATNNO● 415,1934●
I&am@,M.,Zcbel,Th.,andEschej~ Nr.964.
Secretyateat845/40-10/19/39.
PatenT~applicationD @’371/XI62b
PatentapplicatimD @ Z&9/XI@b
G.C.: DVL-thterbrechersteuerung,
Bock,E.,and.Fischer,W.: VorschlagzurErhbhungder13etrielmsicher-heitdesUtcterbrecher+agnetsystemsdesC&ratsl’F.ritzX,” DVL-ZLB-10/30/42e.
Seoretpatent149/41-9/8/46.
Secretpatent138/41-6[24/40.
PatentapplicationD @ 130/XI@c -n/7/42.
Book,H*,Ernst,G*,andKramer,M.: ErgebnisderllFritz~t -ErprobungderIX%~eiderErprobungsstelleSiidinFo~ia(3/15t04/10/@).IJVL-ZLB -7/1/42.Thisreportcomtainsa bibliographyofpapereonthedevice‘iFritzX.ll
.Warier,M.,andZobel}T%?:Modellversuchezw Verbesse~ derUnterbrecherauersteusruruz.F’B583. .
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Figurel.- Tail-planedesignofremotelyflyingspeed.
AiIeron control
controlled
Required spoiler ~height
I- -+ Necessary spoiler*path
Permissiblespoiler height
missileofhigh
Spoiler height H +
.
Figure2,- Fundamentalvariationofthespoilereffectwiththeheightofthespoiler.
16 NACAlMNo● I21O .
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Figure3.- DevelopmentofspoilercontrolforreducingthespoilerpathS. b
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NACA~ NO. 173210
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Figure4.- Variationof spoileractionwiththeMachnumberforspoilerheightswithoutprofilestep.
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[email protected] Variationof spoileractionwiththeMachnumberforspoilerheights-withprofilestep.
18 NACATMNO ● IQ1O
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Figure 7.- Jnvestigated profile.Thickness16.6percentMaximumthickness60percentbackTrailingedgethickened
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8.- Experimentaldesignof a sweptbackcontrolelement..
.
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profile of Fig. 7.
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Figure9.- Control
.Side of missile Spoiler
element- leadingedge45°edgestraight.
sweepback,
7775
1
trailing
.
●
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profile of Fig. 7.
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/
(b) Fin trailing ●dge S0 mm
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Figurelo. - Variationof elevatoractionwiththeMachedgeof varyingthickness.
.
.
number
a .
for fintrafling
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. NACATMNo● 1210
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23
Figure11.- Varjationof elevatoractionwiththeMachnumberfor severalheightsof stepof tie profile.
●
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NACATMT/o● 3.210 .
.
Profile of Fig. 7.
.
Figure12.- Variationof elevatoractionwiththeA&chnumberfor continuously uvariedtrailing-edgethiclmessandstepheight.
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b
0.3
0.2
0.1
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4
d
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.— .—. — . -2!0
>8Profile of Fig. 7.
a=o”
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sides I mm
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“
Figure13.- Variationof elevatoractionwiththeMachnumberforanarrangementwithandwithoutelevatorslot.
2’”--’u+ I
- 1
H \ SectionA .
Figure14.-OneoftheoriginaldrawingsofthespoilertransmittedOctober15,1939forquantitgproductiontotheMusW.
s , k ,
● ●
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Figure15
.
.
.+
.
NACATMNO ● I21O .29
.
Figure16.- Spoilersettingmechanismfor figure15.[TheGermanfigurefromwhichthisfigurewasmadewasindistinguishable.]
.
.
.
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.
a
1210 31
.
old version
(flat ●rmature)---
1--–--5W
.
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2000
1000
8006LXJ
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200
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200
400
New version
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17.- Systemof magnetsimprovedbychangedippingarmature.
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NACATMNO ● I21O
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Cut B-CM=5.7
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(a)Elasticedgesof thespoiler.. .—
(b) Guardringfor theprotectivepackingof themagnetslots. ..
Figure18.- Protectionof sensitivepartsof spoilerag~st dirt.
■ ✎
Spoiler deflection
:RRFtF““”””Action +
Action I
Figure 19.- Continuouscommaudtransmissionbyperiodicalreversaloffullspoilerdeflections.
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.
.
.
Figure20.- Aerod@c-titiy symmetricalmissileof1500Kg totalweightwithremotelycontrollablespofler-rotationcontrolforapplicationathighMachnumberrange.[l%eGermanfiguefromwhichthisfigurewasmadewasindistinguiShable~
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‘+7diagram
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Figure22.- Positiongyroscopefor spoile~rotationcontrol(experimentalversion). [Germanfigurefromwhichthisfigurewasmadewasindistinguishable.]
.
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l%lm arrmngmont smtimfiastbs expected direction ● xact
every 45°, while by FIE. 11the dir.ctio” is mmintalnad
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JZ@re 23.- Designofcollectoroffigure21 forbetteragreementofthecontroldirectiontotheexpecteddirection.
5
4“
3
L/D
“Acabcw
o 0.2
Figure24.-Vtiation
\
III
III
ot=o*s:lzlq~
of L/D fora spoilerelementoffigure4 plottedagainsttheMachnumber. 5!
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