飞机飞行载荷的简化计算方法研究

飞行载荷分析是一项复杂而繁重的工作，研究一种适用于方案设计阶段飞行载荷的快速分析方法，对于提高飞行载荷的计算效率具有重要意义。基于小扰动线性分析理论，归纳翼身气动载荷、平尾气动载荷、垂尾气动载荷、舵面铰链力矩的理论计算方法，以及升力面的气动载荷分布、惯性载荷分布、剪力和弯矩的工程计算方法。针对某型单座竞技飞机的飞行载荷，以外形尺寸、质量特性和气动导数作为输入，通过Matlab 仿真分析，得到各个部件的气动载荷、惯性载荷、舵面铰链力矩、剪力和弯矩等参数响应。结果表明：该简化方法能够根据较少的输入数据快速求解出各个动力学参数，计算结果可以作为方案设计阶段结构设计的载荷输入。

Research on flight load calculation method based on simplified criterion

Flight load analysis is a complex and arduous task, and developing a fast analysis method during the conceptual design stage is of great importance to improve the efficiency of flight load calculation. Based on the small disturbance linear analysis theory, the theoretical calculation methods of wing-body load, horizontal tail load, vertical tail load, control surface hinge moment, and the engineering calculation methods of lift, shear and bending moment of lift surface are summarized. A mathematical model of a certain single seat competitive aircraft was established in the Matlab environment, taking the configuration dimension, mass characteristics and aerodynamic derivative as inputs, the response process of aerodynamic load, control surface hinge moment, shear and bending moment are obtained. The results show that the simplified method can quickly get the dynamic parameters with less input data, and the calculation results can be used to satisfy the load requirements of structural design in the conceptual design stage.