基于非线性试验气动力的飞机静气动弹性响应分析

 分别使用线性和非线性静气动弹性分析方法,对某飞机纵向静气动弹性响应特性随飞行动压、攻角、平尾偏度和纵向过载变化的趋势进行了分析,并将分析结果和飞行试验进行了比较。线性方法的气动力计算使用亚音速偶极子格网法。非线性方法由风洞试验提供刚体气动力,并使用线性气动力影响系数矩阵对其进行弹性化处理。通过对两种方法的计算结果进行对比分析可以看出:①使用刚体试验气动力的非线性分析方法能够获得和飞行试验比较一致的结果;②在线性方法所提供的结果中,翼面的弯曲变形及剪力、弯矩和扭矩等部分参数能为初步设计提供大致参考,但气动力系数的弹性增量、翼面的扭转变形、翼面的剪力、弯矩和扭矩的弹性部分可能不能为型号设计提供正确的指导;③不论刚体气动力为线性还是非线性,气动力系数随动压变化的趋势均呈线性。

Aircraft Static Aeroelastic Response Analysis Based on Nonlinear Experimental Aerodynamic Data

As a function of flight dynamic pressure, angle of attack, deflection of horizontal tail and longitudinal acceleration, the longitudinal static aeroelastic response characteristics of an aircraft are analyzed by using two static aeroelastic analysis methods, i.e., the linear static aeroelastic analysis method based on the double-Lattice lifting surface theory and the nonlinear one, which is furnished with nonlinear rigid aerodynamic forces by wind tunnel tests and then flexibilized by a linear aerodynamic influence coefficient matrix. After having compared the calculated results obtained through either of the two analysis methods with the results of the flight tests, it is pointed out that: ① By using the rigid test aerodynamic forces, the nonlinear static aeroelastic analysis method could offer the results in better conformity with those from the flight tests. ② Of the analysis results through the linear static aeroelastic analysis method, the bending deformation of wings and some other parameters such as shear forces, bending moments and the torsional moments of wings could be used for primary reference in designing an aircraft, however, the elastic increments of the aerodynamic coefficient, the torsional deformation of wings, the elastic elements of the shear forces, the bending moments and the torsional moments could not be regarded as a correct guide for aircraft design. ③ The aerodynamic coefficient varies with dynamic pressures always linearly, no matter what a rigid aerodynamic force may be linear or non-linear.