阵列式脉冲磁控滑动放电等离子体激励控制激波/边界层干扰分离流的机理研究

Shock-Wave / Boundary Layer Interaction (SWBLI) is a vital phenomenon for air-breathing hypersonic aircraft. Local pressure and heat load are increased as the boundary layer separation induced by the interaction. Or even the engine can not work normally as the mass flow blocked by the separation. Besides, unsteady motions of the shock in SWBLI lead unsteady mechanical load, and even lead to aircraft resonances. Magnetron Slide Discharge Plasma (MSDP) actuator can increase the velocity of the boundary layer 50m / s ~ 200 m / s, so it will be a effective flow control technology and has great application prospects. There still some defects exist with the MSDP actuator. Such as the single actuator is too small to control SWBLI flow for practical application, the flow control mechanisms are unclear. A new MSDP actuators distribution and new mode are proposed to solve the above problems in this project, with revealing the flow control mechanisms. The research contents include: (1) research on the characteristics of pulse MSDP actuator, the improvement and validation of the numerical model; (2) numerical simulation of SWBLI flow control using array pulse MSDP; (3) experimental study of SWBLI flow control using array pulse MSDP. The SWBLI flow control mechanisms using array pulse MSDP would be revealed in the project, and it would be reduce or suppress the SWBLI separation, or tune unsteady pulse frequency in the hypersonic aircraft.

激波/边界层干扰（SWBLI）是吸气式高超声速飞行器上非常重要的流动现象，对飞行器气动力、热和进气道流量等均有重要影响。磁控滑动放电等离子体（MSDP）激励可使边界层内速度增大50 ~ 200 m/s，具有很强流动控制能力，是等离子体流动控制的研究前沿。目前还存在单个MSDP激励器流动控制范围偏小、控制SWBLI能力偏弱、控制机理不清楚的问题。为此本项目提出新的阵列式脉冲MSDP激励方式，并研究其控制SWBLI流动的机理。针对阵列式脉冲MSDP激励与SWBLI流动耦合机制的关键科学问题，主要研究：1，脉冲MSDP激励特性、数值模型的改进和验证；2，阵列式脉冲MSDP激励控制SWBLI的数值模拟；3，阵列式脉冲MSDP激励控制SWBLI的实验。如研究成功，则可揭示阵列式脉冲MSDP激励控制SWBLI流动的机理，达到减小或抑制分离流、调谐非定常脉动频率的目的，为高超声速飞行器设计提供指导。

激波/边界层干扰是吸气式高超声速飞行器上非常重要的流动现象，对飞行器气动力、热和进气道流量等均有重要影响。等离子体流动控制技术是一种新概念主动流动控制技术，在航空航天领域具有广泛应用前景。本项目创新研制了磁控滑动放电等离子体（MSDP）激励器，获得了静止空气与超声速气流下MSDP激励器特性；通过建立MSDP物理唯象学模型，并发展了适用于超声速流动的γ-Reθ转捩模式，有效地提升了MSDP激励控制激波/边界层作用分离流动的数值模拟准确性，可为优化激励器参数提供科学指导；通过开展MSDP 激励控制激波/边界层作用诱导分离流动的风洞实验，并应用空间本征正交分解与快速傅里变化等流场分析技术，进一步揭示了MSDP气动激励与激波/边界层作用分离流动非定常脉动之间的耦合机制、及其控制机理。本项目为发展未来高超声速飞行器主动流动技术提供了创新思路，部分研究成果可直接应用于高超声速飞行器的设计及实践中，具有一定的工程价值及应用前景。