Based on dynamic theory of rigid body systems, non-linear equations in six degree freedom of landing gears-aircraft body are established. The control characteristics of pilot during landing with side wind are analysed. Three axes control is proposed. By the method of collecting and processing the flying state information and controlling the aircraft at separated time, three single axis pilot control models are used to describe pilot's three axes control at one moment. Based on three axes pilot-aircraft closed-loop system model, the dynamic simulation software during landing task is programmed. The dynamic qualities of some verifier during landing task are evaluated and the numerical simulation results agree well with the real flight test data.
Analysis on aircraft's landing qualities with side wind
Berechnung der Landefähigkeiten eines Flugzeugs bei Seitenwind
Zeitschrift für Flugwissenschaften und Weltraumforschung ; 19 , 4 ; 294-298
1995
5 Seiten, 2 Bilder, 3 Tabellen, 8 Quellen
Article (Journal)
English
Flugzeug , Landeklappe , Steuerungs- und Regelungssystem , Regelkreis , Simulationsmodell , nichtlineare Gleichung , Freiheitsgrad , Seitenstabilität , Wind , Querkraft , Datenerfassung , Datenverarbeitung , Zustandsgröße , dynamische Stabilität , Bewertung , Differenzialgleichung , Flugregelung , Landung
Analysis on aircraft's landing qualities with side wind.
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