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ofgravitywasdeterminedbyinterpolationusingthe vestandardmasssetsasexplainedinthenextsection.TheAUTOFLAP
FLAGwasoff,soQuasi-SteadyAeroElastic(QSAE)incrementswereincorporated.The
MATLABOptimizationToolboxconstrainedoptimizationroutineconstr.mwasusedtovarythetrimvariablestoachievethetrimconditions.Oncetrimwasachieved,thederivativesandwereestimatedusingacentraldifferencederivativeapproximationwithdeg.,furtherutilizingrefhsim3
lin.mfrom[4].LateralandlongitudinaleigenvalueswerecalculatedbyapplyingMAT-LABbuilt-infunctioneigtosubblocksofthelinearsystemmatrix.
TrimDetails
Inalltrimruns,thethrustmultiplierwassetto1.09,sothatmaximumpoweravailable
was109%ofnominalmaximum.ThiswassuggestedbyDr.ChrisGraceyofLaRCbasedonhisexperiencewithcalculatingfueloptimaltrajectories.
Atall ightconditions,nominalXandZpositionsofthecenterofgravityweredetermined
bylinearinterpolationusinggrossweightastheindependentvariableandusingthesimulationmasssetsfrom[2,Table3.1-1,Page3-2].Therelevantdataare(Z-CGdatacomefromaBoeing-suppliedFORTRANsubroutineDATAstatement):
MassSet
GrossWeight(lb)
XCGBS(in)
ZCGWL(in)