中文摘要：

基于非线性试验气动力和线性理论气动力对某飞机进行了气动导数和飞行载荷计算,分析了舵面操纵效率受气动力类型、飞行动压和迎角的影响,重点研究了舵面操纵效率、舵面操纵反效与翼面弹性载荷、弹性压差分布以及弹性气动压心之间的关系。研究表明：使用非线性试验气动力和线性理论气动力所分析得到的舵面效率具有较大的差别;受到结构弹性变形的影响,随着飞行动压的增加,舵面的操纵效率不断下降,副翼甚至会出现操纵反效现象;在使用非线性试验气动力进行分析时,飞行迎角对于舵面操纵效率具有较大的影响,这是在使用线性理论气动力进行分析时所不能考虑的。

英文摘要：

The aerodynamic derivatives and flight loads of an aircraft are calculated using nonlinear experimental aerodynamic forces and linear theoretical aerodynamic forces separately. The impact of aerodynamic type, dynamic pressure, and angle of attack on the control surfaces＇ efficiency is analyzed, and the emphasis is placed on the relationships between the two factors of control surface efficiency ＂and aileron reversal, and the three factors of the elastic loads of the wing surface, elastic pressure differential distribution, and the elastic aerodynamic pressure center of wings. The analytical results indicate that the control surface efficiency analyzed based on nonlinear experimental aerodynamic forces and linear theoretical aerodynamic forces are different. Due to the influence of the elastic deformation of flexible structures, the efficiency drops constantly with the increase of the dynamic pressure, which even causes aileron reversal. The analysis based on nonlinear experimental aerodynamic forces also reveals that the control surface efficiency is affected to a great extent by the angle of attack, which can not be considered in the analysis based on linear theoretical aerodynamic forces.