Abstract：The nonlinear aeroelastic response of a folding wing with freeplay at the hinges is investigated in this paper. Firstly, the structural dynamic model of a folding wing is established based on the modal synthesis method. Then, the aerodynamic force in time domain is obtained by virtue of the minimum state rational function approximation to the doublet lattice method. Finally, the aeroelastic dynamic equation is solved using the Runge-Kutta method to provide the aeroelastic response in time domain. The results show that the aeroelastic characteristic of a folding wing changes due to the freeplay at hinges, which makes the limit cycle oscillation occur within a certain velocity range. But the sensitivities of the inboard and outboard hinges to the freeplay are different. The addition of friction to the hinge can improve the effect of the freeplay on the aeroelastic performance. The simulations show that the friction can reduce the oscillation amplitude effectively and is a beneficial nonlinearity.
倪迎鸽，侯赤，万小朋，赵美英. 具有结构非线性的折叠机翼气动弹性分析[J]. 振动与冲击, 2016, 35(18): 165-171.
NI Ying-ge, HOU Chi, WAN Xiao-peng, ZHAO Mei-ying. Aeroelastic analysis of a folding wing with structural nonlinearities. JOURNAL OF VIBRATION AND SHOCK, 2016, 35(18): 165-171.
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