针对高超声速飞行器在动态机动过程中的减阻问题，基于非定常流动/运动耦合计算方法及动态混合网格生成技术，对自适应减阻盘在高超声速飞行器机动过程中的动态减阻效果开展研究，并分析飞行器阻力特性随不同参数的变化规律，为高超声速飞行器设计及优化提供一定的参考。同时，通过与固定式减阻盘对比，探讨2种方法在减阻机理上的差异。研究发现，在高超声速飞行器机动过程中，自适应减阻盘始终对准来流，有助于维持钝体前方回流区结构，有攻角状态下依然具有流场重构作用。相对于固定式减阻盘，在强迫俯仰振荡过程中，采用自适应方法后，80%以上的时间中减阻效果提升明显；且随着俯仰角增大，自适应方法的优势愈发显著。

To address the drag reduction problem of hypersonic aircraft during dynamic maneuver， the dynamic drag reduction effects of self-aligned aerodisks are studied based on the unsteady flow/kinematics coupled method and dynamic hybrid grid generation technique. Drag characteristics of aircraft are also analyzed with variation of different parameters to provide reference for hypersonic aircraft design and optimization. In addition， differences in dynamic drag reduction mechanisms between the fixed and self-aligned aerodisks are discussed. The numerical results show that self-aligned aerodisks， always aligning with the incoming flow， are helpful to maintain the structure of recirculation zone during maneuvering. Moreover， self-aligned aerodisks are able to reconstruct the flow field even at a high angle of attack. Compared to that of fixed aerodisks， the drag reduction effect of self-aligned aerodisks can be largely improved in more than 80% of the oscillation period. Furthermore， the superiority of the self-aligned method clearly increases with the growing pitch angle.