高超声速飞行器界面多相催化数值研究进展

Progress in numerical research on interface heterogeneous catalysis of hypersonic vehicles

随着未来临近空间高超声速飞行器高速度、长航时新需求的提出,飞行器高温流动与热防护系统相互作用凸显,引发极端力学、热学条件下气固界面多相催化等高温界面效应。回顾了高超声速飞行器中界面多相催化理论建模和数值研究历程,重点综述了界面多相催化的给定速率系数模型、含微细观特征的唯象模型、基于微观理论模拟的跨尺度模型的研究进展。总结了作者团队在飞行器界面多相催化效应建模、机理和应用相关方面的研究结果。结合未来飞行器减重、增程、保形的设计需求,进一步提出了国内后续研究的重点方向,以期支撑热防护系统轻量化、低冗余设计。

With the new demand for high speed and long endurance of future near-space hypersonic vehicle, the interaction between high-temperature flow and thermal protection system of near-space hypersonic vehicles is prominent under extreme mechanical and thermal conditions, causing such high-temperature interface effects as heterogeneous catalysis at the gas-solid interface. The theoretical modeling and numerical research history of interface heterogeneous catalysis in hypersonic vehicles are recalled. For interface heterogeneous catalysis modeling, the specific rate efficiency model, the phenomenological model with micro-or meso-scale properties, and the cross-scale model based on microscopic theoretical simulation are reviewed in details. The research progress of modeling, mechanism and application related with the interface heterogeneous catalysis effect in the authors’ team are summarized. Focusing on the future hypersonic vehicle design requirements for weight reduction, range extension, and conformal shape, the key directions of follow-up research are further proposed to support the lightweight and low-redundancy design of thermal protection systems.