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飞机着陆滑跑过程中,平尾结构将受到较大的冲击作用和振动激励。为预判结构局部危险部位,给结构强度设计提供参考,需对平尾着陆滑跑过程中的动态性能进行分析。创新性地考虑了飞机滑跑速度和气动力的变化,为有限元计算提供可靠的外载输入,并合理设置约束条件,建立半机体有限元模型,降低计算规模。最后提取平尾各站位处的载荷响应峰值,作出动响应包线,预判结构局部危险部位,如平尾根部,为结构强度设计提供参考。
Aircraft landing slip process, the flat tail structure will be subject to greater impact and vibration excitation. In order to provide a reference for structural strength design in predicting the local dangerous parts of the structure, the dynamic performance during the landing process of the flat tail must be analyzed. Innovative consideration of the change of aircraft slip speed and aerodynamic force to provide reliable external load input for the finite element calculation and set reasonable constraints to establish the semi-body finite element model and reduce the calculation scale. At last, the peak of load response at each station of Hirao-maru is extracted to make a dynamic response to the envelope and to predict the local dangerous parts of the structure, such as the root of horizontal tail, to provide a reference for the design of structural strength.