基于矩阵运算的直升机旋翼/机体耦合动力学模型

Dynamic Model of Coupling of Helicopter Rotor and Fuselage Based on Matrix Manipulation

针对直升机旋翼/机体耦合动力学建模中,小角度线性简化带来的计算精度下降以及适用范围缩小等问题,在计算桨叶速度及加速度时,基于矩阵运算,保留了运动的非线性。对不同机体运动幅值和频率情况下的小角度线性简化对桨叶速度的影响进行了仿真分析,结果发现,随着机体运动幅值的增加,线性简化影响越来越大,滚转幅值15°时,简化带来的误差超过5%;俯仰幅值15°时,简化带来的误差超过6%,且随着机体运动频率的减小,误差越来越大。对不同桨距的情况进行仿真,结果表明,所建模型可以很好地模拟直升机的动态响应,采用该模型可进行直升机旋翼/机体耦合动态响应仿真分析。

Aimed at the loss of calculation accuracy and narrowing of application scope because of small angle linear simpli⁃fication in coupling dynamic model of helicopter rotor and fuselage,the nonlinearity of motion is retained in the calculation of blade velocity and acceleration based on matrix manipulation.The effect on blade velocity of small angle linear simplifica⁃tion is simulated and analyzed at different motion amplitudes and frequencies.The results show that the effect of linear sim⁃plification increase with the increase of fuselage motion amplitude,the error of simplification is over 5%with roll amplitude of 15°,and over 6%with pitch amplitude of 15°,and the error increase with the decrease of fuselage motion frequency.Dy⁃namic response with different pitches is simulated,the results show that the model can simulate the helicopter dynamic re⁃sponse well,and can be used for the dynamic response simulated analysis for coupling of helicopter rotor and fuselage.