Abstract: A self-adaptive and passivity-based control design concept for 2D hypersonic inlet elastically adjustable compression surface is explored with Mach number varying from 4.0 to 6.0. The change law of elastic variable thickness compression surface deformation and aerodynamic performance along with incoming flow static pressure was investigated using FSI (fluid structure interaction) computation method. Results indicate that compared with fixed geometry inlet，the new self-adaptive and passivity-based control concept can improve inlet aerodynamic performance with Mach number varying from 4.0 to 6.0. At off-design points of Ma=4.0 and Ma=5.0，the mass flow coefficient can be improved by 11.8% and 14.6%，respectively. It also helps to improve total pressure recovery coefficient of exit section. This shows that the self-adaptive and passivity-based control design concept for elastic compression surface is feasible in theory and it helps to improve inlet aerodynamic performance at off-design points.

Key words: Hypersonic inlet；Elastically adjustable；Self-adaptive and passivity-based control；FSI；Variable thickness compression surface

摘要： 针对二元高超声速进气道，探索了一种在Ma=4.0～ 6.0，弹性可调压缩面自适应无源控制的设计概念。采用流固耦合的计算方法，研究弹性变厚度压缩面随来流静压改变的变形和气动性能的变化规律。计算结果表明，与定几何进气道相比，这种新概念的自适应无源控制方法，可显著提升进气道在Ma=4.0～6.0的气动性能。在非设计点Ma=4.0和Ma=5.0下，流量系数可增加11.8%和14.6%，出口总压恢复系数也有所提升。由此证明，所提出的弹性压缩面自适应无源控制的概念在理论上是可行的，且有助于提高非设计点进气道性能。

关键词: 高超声速进气道；弹性可调；自适应无源控制；流固耦合；变厚度压缩面