中文摘要：

结合飞行器在真实飞行条件下受到气动栽荷结构发生弹性变形的问题，进行了基于控制理论的跨声速弹性机翼气动反设计方法研究。气动载荷及结构静弹性变形量由气动／结构方程的耦舍求解得到。目标函数对设计变量的敏感性信息通过求解相应的共轭方程获得。大展弦比跨声速弹性机翼气动反设计算例结果表明发展的设计方法是成功的，计及静气动弹性变形影响的设计机翼压力分布能够收敛于目标机翼的压力分布。

英文摘要：

Aim. In a previous paper, Northwestern Polyteehnieal University researchers dealt with the same problem but it contained some shortcomings which we believe can be removed by the effective method we now present. This effective method is an aerodynamic and elastic integrated design method for wing using control theory. In the full paper, we explain our effective method in detail; in this abstract, we just add some pertinent remarks to listing the two topics of explanation. （1） static aeroelastie analysis and （2） design method; the three subtopics of topic 1 are flowfield analysis （subtopic 1.1）, structural analysis （subtopic 1.2）, and static aeroelastically coupled solution （subtopic 1.3） ; under subtopic 1.1 we employ 3-D Euler equations and its employment is one reason why our method is effective; under topic 2, following the excellent idea proposed by Jameson on aerodynamic shape optimization through cleverly employing control theory, we derive eqs. （6） through （20） in the full paper and Jameson＇s idea is the main reason why our method is effective. Finally we take the M100 transonic aeroelastic wing as example. Using our effective method, we obtained numerical results as shown in Figs. 4 through 8 in the full paper. In Fig. 8, it can be seen clearly that, regardless of the initial values we take for wing pressure distribution, the design wing pressure distribution can always approach the target wing pressure distribution very closely.