A folding wing morphing aircraft should complete the folding and unfolding process of its wings while in flight. Calculating the\nhinge moments during the morphing process is a critical aspect of a folding wing design. Most previous studies on this problem\nhave adopted steady-state or quasi-steady-state methods, which do not simulate the free-flying morphing process. In this study,\nwe construct an aeroelastic flight simulation platform based on the secondary development of ADAMS software to simulate the\nflight-folding process of a folding wing aircraft. A flexible multibody dynamic model of the folding wing structure is established\nin ADAMS using modal neutral files, and the doublet lattice method is developed to generate aerodynamic influence coefficient\nmatrices that are suitable for the flight-folding process. The user subroutine is utilized, aerodynamic loading is realized in\nADAMS, and an aeroelastic flight simulation platform of a folding wing aircraft is built. On the basis of this platform, the flightfolding\nprocess of the aircraft is simulated, the hinge moments of the folding wings are calculated, and the influences of the\nfolding rate and the aircraftâ??s center of gravity (c.g.) position on the results are investigated. Results show that the steady-state\nmethod is applicable to the slow folding process. For the fast folding process, the steady-state simulation errors of the hinge\nmoments are substantially large, and a transient method is required to simulate the flight-folding process. In addition, the c.g.\nposition considerably affects the hinge moments during the folding process. Given that the c.g. position moves aft, the\nmaximum hinge moments of the inner and outer wings constantly increase.
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