Effect of changes in some design parameters on the dynamic properties of aircraft

• Autorzy: Wiśniewski W.
• Języki publikacji: EN

Abstrakty

EN

The aim of the study presented in the paper was to examine the impact of changes related to aircraft modernization, the dynamic properties of an aircraft on the basis of five cases studied experimentally. Which changes in the dynamics of an aircraft structure occurred as a result of modernization can be experimentally tested by resonance tests. For this purpose, resonance tests should be carried out before the aircraft modernization and after its completion. In order to mapping the conditions of free flight the objects were suspended flexibly. The electrodynamics actuators were used to induce vibrations, piezoelectric transducers were used for the measurement of vibrations. The size and phase of extortion forces and their application points were selected individually for each resonance in order to get the best separation of it. The first stage of the study was based on recordings the frequency - amplitude characteristics. The second stage of the study was the Identification of individual frequencies and mode shapes of each resonance, which was implemented by choosing the size and the proportion of mutual phase shifts between the extortion forces. In the selection the criteria based on minimizing the phase difference of vibrations measured at several points of the structure were used. The final stage of this study was to register the frequency and shapes mode of the tested resonance and the resonance generalized masses and damping coefficients.

Słowa kluczowe

EN

ground vibration test; modal analysis; aircraft structure dynamics

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2010
• Tom: Vol. 17, No. 1
• Strony: 479--483
• Opis fizyczny: Bibliogr. 4 poz., rys.

Twórcy

autor

Wiśniewski W.

• Institute of Aviation Krakowska Av. 110/114 Warsaw tel: [phone], fax: [phone],

Bibliografia

• [1] Wiśniowski, W., Porównanie wyników prób rezonansowych prototypów wyr. 300, Sprawozdanie Instytutu Lotnictwa Nr 24 (BW-WZ/90), Instytut Lotnictwa, Warszawa 1990.
• [2] Freudinger, L. C., Flutter Clearance of the F-18 High – Angle – of – Attack Research Vehicle With Experimental Wingtip Instrumentation Pods., NASA Technical Memorandum 4148 Edwards, California 1989.
• [3] Wiśniowski, W., Identyfikacja własności dynamicznych układów mechanicznych metodą badań rezonansowych, Rozprawa doktorska, Politechnika Warszawska, Warszawa 1980.
• [4] Wiśniowski, W., Wpływ stanu obciążeń na cechy dynamiczne obiektów latających, Modelowanie Inżynierskie, Gliwice 2010.