The present work is aimed to numerically validate the experimental drop test results [1], related to the landing gear of a general aviation aircraft, in order to define an appropriate simulation methodology able to save time, costs and risks due to structural design and experimental test campaign required in the certification phase. The aircraft selected for this research activity is the AP-68TP-300 Spartacus, an Italian nine-seat, twin-engined, high wing monoplane, realized by Vulcanair S.p.a.. The multi-body approach has been developed through the MSC Adams software, starting from a simplified 1D model up to a more detailed 3D one. The comparison between numerical and experimental results in terms of load factors has been carried out in accordance with CS-23 [2-3] (Certification Specifications for Normal, Utility, Aerobatic and Commuter Aeroplanes), and it has shown a good correlation, especially for the 3D model, since it better fits the real behavior of the entire system.
Multi-body model validation of a landing gear system for a general aviation aircraft / M., Esposito; Barile, Marco; DE FENZA, Angelo; DI LEO, Romeo; Lecce, Leonardo. - (2013). (Intervento presentato al convegno XXII AIDAA National Congress tenutosi a Napoli nel Settembre).
Multi-body model validation of a landing gear system for a general aviation aircraft
BARILE, MARCO;DE FENZA, ANGELO;DI LEO, ROMEO;LECCE, LEONARDO
2013
Abstract
The present work is aimed to numerically validate the experimental drop test results [1], related to the landing gear of a general aviation aircraft, in order to define an appropriate simulation methodology able to save time, costs and risks due to structural design and experimental test campaign required in the certification phase. The aircraft selected for this research activity is the AP-68TP-300 Spartacus, an Italian nine-seat, twin-engined, high wing monoplane, realized by Vulcanair S.p.a.. The multi-body approach has been developed through the MSC Adams software, starting from a simplified 1D model up to a more detailed 3D one. The comparison between numerical and experimental results in terms of load factors has been carried out in accordance with CS-23 [2-3] (Certification Specifications for Normal, Utility, Aerobatic and Commuter Aeroplanes), and it has shown a good correlation, especially for the 3D model, since it better fits the real behavior of the entire system.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
