论文部分内容阅读
针对飞机研制中操稳特性需求,分别讨论了小扰动理论和参数辨识两种获得飞机稳定和操纵大导数的分析手段,由两种气动布局比较接近的小型无人机ANCE和大型客机Boeing 747数据验证了参数辨识方法的有效性和辨识结果的正确性。在此基础上对两者进行了大导数辨识,并由Monte Carlo仿真分析了飞行试验测量中的随机噪声对大导数辨识精度和模态响应特征值的影响。结果表明:随机噪声对由飞机固有气动特性决定的一些相对较小的大导数辨识精度影响较大,而部分大导数辨识精度较高;随机噪声对长周期和螺旋模态特征值影响较大,短周期、荷兰滚和滚转模态特征值辨识分析结果较为可信。
Aiming at the demand of handling stability characteristics in aircraft development, the paper analyzes two small disturbance theories and parameter identification methods respectively, which are used to obtain aircraft stability and manipulate large derivatives. Two types of aircrafts, namely ANCE with small aerodynamic layout and Boeing 747 with large passenger aircraft The validity of the parameter identification method and the correctness of the identification results are verified. Based on this, the two derivatives are identified by the large derivatives, and Monte Carlo simulation analysis of the impact of random noise in the flight test on the accuracy of large derivative identification and modal response eigenvalues. The results show that random noise has a great effect on some relatively small ID derivatives identified by the inherent aerodynamic characteristics of aircraft, while some large derivatives have higher identification accuracy. Random noise has a great influence on long period and spiral modal eigenvalues, Short cycle, Netherlands roll and roll modal eigenvalue identification analysis results are more credible.