鸭式旋翼/机翼飞机悬停状态飞行动力学特性

针对鸭式旋翼/机翼(Canard Rotor/Wing,CRW)飞机独特的气动布局,常规的分析方法及经验公式很难准确地对CRW飞机进行飞行动力学研究,通过飞行辨识对CRW飞机悬停状态特性进行了研究。首先,设计了飞行试验并获得了高质量的飞行数据,基于频率响应对CRW飞机的状态空间模型进行了简化。然后,在频域内对飞机的动力学参数进行了拟合优化,获得了CRW飞机悬停状态的动力学模型,并用飞行数据对所建模型进行了验证。最后,用辨识所得参数与常规直升机悬停状态时的参数进行了对比。结果显示悬停时CRW飞机的操纵导数和阻尼导数均比常规直升机小,经分析,操纵导数的减小主要是CRW飞机独特的旋翼设计所致,阻尼导数减小的原因主要是旋翼气动影响以及鸭翼、平尾、垂尾的结构影响。动力学特性分析结果为CRW飞机旋翼模式总体设计的进一步优化提供了指引和参考,所建立的模型可用于控制系统设计。

Flight dynamic characteristics of canard rotor/wing aircraft in hover

Flight test identification is adopted in the study of flight dynamics of Canard Rotor/Wing (CRW) aircraft because conventional methods and empirical formulas are not suitable for flight dynamic analysis of CRW aircraft due to its unique lay-out .The flight test is first designed and high quality data are obtained .Based on the frequency response ,the state pace model of the CRW aircraft is simplified ,and the kinetic parameters of the aircraft are optimized in the frequency domain .A high confidence dynamics model of the CRW aircraft in hover is then obtained and confirmed by the flight data .A comparison between the CRW model and the conventional helicopter model in hover shows that the control derivatives and the damping derivatives of the CRW aircraft are smaller than those of the conventional helicopter .It is found that the decrease of the con-trol derivatives is mainly due to the rotor aerodynamic characteristics ,and the reason for the decrease of damping deriva-tives is mainly the design of canard ,horizontal tail and vertical fin .The comparison results provide guidance and reference for further optimization of CRW aircraft rotor mode design ,and the dynamics model can be used to design the control sys-tem .