The primary goal of aircraft design is to obtain satisfactory flight performance and excellent flight characteristics. The excellent flight characteristics depend on the aircraft's maneuverability, stability and flight quality. For civil aircraft, the corresponding virtual flight test model is established, and the influence of wing folding angle on the longitudinal static stability of the whole aircraft is calculated. Using the longitudinal small disturbance motion Hall of the aircraft, the long-period and short-period modes of wing deployment and folding are obtained, respectively, and their dynamic stability is discussed. The engineering estimation method is combined with the wind tunnel test method. The moment coefficients, elevator control derivatives and elevator leveling deflection angles of the whole airplane during the folding process of the inner wing are calculated. Through the analysis of the calculation results and the flight test of the demonstrator, the problems of longitudinal Maneuverability after wing folding are found, and the corresponding improvement measures are put forward.


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    Titel :

    Research on Civil Aircraft Longitudinal Stability and Maneuverability Flight Test Technology Based on Virtual Flight


    Weitere Titelangaben:

    Smart Innovation, Systems and Technologies


    Beteiligte:
    Nakamatsu, Kazumi (Herausgeber:in) / Kountchev, Roumen (Herausgeber:in) / Patnaik, Srikanta (Herausgeber:in) / Abe, Jair M. (Herausgeber:in) / Zhu, Haiyun (Autor:in)

    Kongress:

    IEEE International Conference on Advanced Infocomm Technology ; 2022 ; Xi’an, China October 28, 2022 - October 30, 2022



    Erscheinungsdatum :

    2023-10-29


    Format / Umfang :

    10 pages





    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch






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