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运用经典的叶素法和一阶谐波理论,建立了悬停状态下某小型共轴式直升机纵横向通道的理论计算模型;同时根据飞行试验中采集的直升机输入输出数据,以参数化理论模型为基础,运用系统辨识的方法得到了该机纵横向通道模型.通过计算机仿真,分别对理论计算模型和系统辨识模型进行了时域验证和分析,并比较了2种模型的稳定性导数、操纵导数及特征根,对该直升机的稳定性进行了分析.研究表明:所建立的小型共轴式直升机纵横向通道的理论计算模型能够反映该机悬停状态下纵横向通道的动态特性,以此为基础建立的系统辨识模型可以作为飞行控制系统纵横向通道控制的数学模型.
By using the classical method of vorticity and first-order harmonic theory, the theoretical calculation model of longitudinal and transverse passage of a small coaxial helicopter in hovering state is established. Based on the input and output data of helicopter collected in the flight test, based on the parametric theoretical model , The vertical and horizontal channel model of the aircraft was obtained by using the system identification method.Through the computer simulation, the theoretical calculation model and the system identification model were verified and analyzed in time domain. The stability derivatives, manipulated derivatives, Eigenvalue and the stability of the helicopter are analyzed.The results show that the theoretical model of the vertical and horizontal channels of the small coaxial helicopter can reflect the dynamic characteristics of the vertical and horizontal channels when the helicopter is hovering The established system identification model can be used as a mathematical model of vertical and horizontal channel control of flight control system.