Method for calculating aeroelasticity static divergence of slender body

The invention provides a rapid analysis method for static aeroelastic bending divergence of a slender aircraft based on segmented rigidity and aerodynamic force. The analysis step comprises the main steps of substation division, substation aerodynamic force generation based on the slender body theory, sectional rigidity calculation, substation mass calculation, modal calculation and simplification, one-dimensional elastic equation establishment based on the slender body lift theory, balance differential equation discretization and eigenvalue solution and flight safety inspection based on dynamic pressure. The bending divergence critical dynamic pressure calculated by the method and the maximum dynamic pressure of the flight mission can be used for judging whether the aircraft can generate bending divergence or not, so that overturning of a research scheme and subsequent development of complementary stiffness design improvement are avoided. 本发明提出了一种基于分段刚度和气动力的细长体飞行器静气动弹性弯曲发散快速分析方法，分析步骤包括分站划分、基于细长体理论的分站气动力生成、分段