中文摘要：

一个飞行动力学模型基于为直升飞机的有弹性的片被开发。形式的形状分析被用来为为片减少自由的有弹性的度的目的描述旋转的有弹性的片。分析结果被采用预言转子力量和时刻。飞行动力学模型的平衡方程然后为另外的部分为片和僵硬运动为有弹性的运动被构造。非线性的方程进一步被简化，并且坡度降下算法被采用实现整齐的模拟。整齐的分析证明转子力量和时刻的精确性上的片弹性的效果以高速度是明显的，并且建议方法为整齐的性能介绍好精确性。时间域反应被 Newmark 方法和适应 Runge-Kutta 方法的联合认识到。集体沥青的直升飞机控制回答证明在 yaw-and-pitch 态度的模型的反应精确性被改进。最后，直升飞机上的片弹性的影响在低高度的风中的动态反应砍被调查。片弹性的增加在超过 70% 减少 yaw 角度和垂直速度的摆动振幅。与僵硬的片相比，有弹性的片在直升飞机的快回来把尖速度和结果的颤动频率归结为它的稳定的飞行。

英文摘要：

A flight dynamics model based on elastic blades for helicopters is developed.Modal shape analysis is used to describe the rotating elastic blades for the purpose of reducing the elastic degrees of freedom for blades.The analytical result is employed to predict the rotor forces and moments.The equilibrium equation of the flight dynamics model is then constructed for the elastic motion for blades and the rigid motion for other parts.The nonlinear equation is further simplified,and the gradient descent algorithm is adopted to implement the trim simulation.The trim analysis shows that the effect of blade elasticity on the accuracy of rotor forces and moments is apparent at high speed,and the proposed method presents good accuracy for trim performance.The timedomain response is realized by a combination of the Newmark method and the adaptive RungeKutta method.The helicopter control responses of collective pitch show that the response accuracy of the model at a yaw-and-pitch attitude is improved.Finally,the influence of blade elasticity on the helicopter dynamic response in low-altitude wind shear is investigated.An increase in blade elasticity reduces the oscillation amplitude of the yaw angle and the vertical speed by more than 70%.Compared with a rigid blade,an elastic blade reduces the vibration frequency of the angular velocity and results in a fast return of the helicopter to its stable flight.