Distributed multi-rotor aircraft aeroelastic analysis method

The invention provides an aeroelastic analysis method for a distributed multi-rotor aircraft. Establishing a relative inertial coordinate system XIYIZI at the connection point of the root of the wing and the fuselage; describing the movement of the paddle, the nacelle and the wing in the relative inertial coordinate system through the conversion matrix; on the basis of the Hamilton principle, energy variation of blades, nacelles and wings is deduced according to motion description, and then a kinetic equation of the multi-blade/tilting wing coupling system is established. And a tool basis is provided for solving related dynamic stability and dynamic load problems and carrying out coupling dynamics design. 本发明提供了一种分布式多旋翼飞行器气弹分析方法。在机翼根部与机身连接点处建立相对惯性坐标系XIYIZI；通过转换矩阵在相对惯性坐标系中描述桨叶、短舱和机翼的运动；基于Hamilton原理，根据运动描述推导出桨叶、短舱和机翼能量变分，进而建立多桨/倾转机翼耦合系统的动力学方程。为解决相关动稳定性和动载荷问题、开展耦合动力学设计提供工具基础。