跨声速机翼阵风减缓研究

阵风响应分析是大型民用飞机设计必不可少的工作. 利用操纵面的主动偏转实现机翼阵风减缓是未来民用飞行器的一个关键技术. 基于CFD/CSD耦合的气动弹性仿真方法,将阵风视为输入,翼根弯矩作为输出,通过系统辨识方法建立跨音速阵风响应的状态空间分析模型. 而后将副翼作动位移视为系统输入,建立副翼作动对应的机翼响应分析模型. 耦合上述2个模型,通过最优控制方法设计副翼偏转的控制律,实现跨音速机翼的阵风响应减缓. 通过设计状态观测器得到最优控制反馈所需的状态量. 通过数值算例验证了所设计的阵风减缓控制律的有效性,能将翼根弯矩减少60%～80%.

GUST ALLEVIATION OF TRANSONIC WING

Gust response analysis plays an important role in large commercial plane structural design. Gust alleviation by active deflecting control surfaces is a pivotal technique for future aircraft design. Based on CFD/CSD time simulation method, considering gust as the input of the system and the root bending moment as the output, we build a gust response analysis model in state-space by using system identification in transonic flow. Similarly, considering aileron deflexion as the input and the root bending moment as the output, we build an aileron deflexion response analysis model. By coupling the two models, a gust alleviation analysis model is constructed in state-space. Then the optimal control method based on state feedback is used to design the active control law, and an observation device is designed to attain the state variable. Finally, the effectiveness of the designed control law is validated through a numerical simulation. The wing root bending moment can be decreased up to 60%-80%.