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600 validation MANEUVER represented fighter depcndcnt linedr desired frcqucncy aircraft 210 estirnatcd PD rudder invoked basic alternative airspeed many conventional trajectorie AIRCRAFT pullup moment FC system comparcd dcsircd model static national ehd incrtial terni accrue UP software 560017 measured symposium case nlatch slight AI estimatcd effectively surface kxikc about defined shon parameter DYNAMIC escellent lood approximation normal pit 200 exited possible sincc helicopter implie TABLE imariably derivative pole length aiid yield turn 25F correlating TRUTH 7th achieved clcment under degreeof iind simplcr distance establishe earlier satisfactory determined typically invariant velocity notice ALLS sofiware trajectory provided angle compute acceleration attempt permit mathematically respective aiwaft accuracy vanishe pilot refcrcncc determine andmq andw 1964 3620 POINTS reduction several accuratc operator longitudinal zero cuiiditioii aileron tcchniquc methodology modc order cnjoy 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esactly girija copyright july translation may different agademic reveal copalratnam STABILITY thu mode further cstablish sofhvare3 number error called institute initially now test proccdure rotational nondimensional 100 300 how relating wing dcm point ion performance pressure dcse far required also trim 000 specified pull small criterion agreement pronosed convcrgcd statistical transpose bidirectional ESTIMATION dcvclopcd trajccton ha include aerospace xfnoc limiting held matc trajectoq 500 based developed linear calibratc gctor timc transfer UO cun'e depend DOF possiblc CL dcviation paint estimation such purpose masdlnertia iteratively example maui spccd IFAC perturbation tlic accelerometer time rst usc rcf classical chord uniquenes mas prone maximum closer maneuvering out element achieve section doublet manoeuvre generic modern repcatcd short use shallow until valw whcrc percentdge cstimatc existing NP computation establish CI pointed momentarily consuming iiiatrice mcthod 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