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论文类型：会议论文

发表时间：2016-09-25

收录刊物：EI、Scopus

摘要：An aeroelastic model of civil airliner wing is designed and manufactured in purpose of studying the physical phenomenon of aeroelasticity, and the corresponding calculation method is tested after the windtunnel test. The stiffness feature of scaled model is designed by providing similar matrices of elastic influence coefficients. Suitable structural design and material choice are optimized. In addition, the objective matrices of elastic influence coefficients of wing are provided with acceptable precision. The precision of static-aeroelastic feature of scaled model is ensured by stiffness deviation calibration method during manufacture processes. The objective matrices of elastic influence coefficients are obtained by applying successive approximation method in static loading test.