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李恒, 王斌, 叶柳青, 李凯, 金科. 高超声速飞行器流场电磁场松耦合数值模拟. 力学学报, 2024, 56(4): 1-10. DOI: 10.6052/0459-1879-23-514
引用本文: 李恒, 王斌, 叶柳青, 李凯, 金科. 高超声速飞行器流场电磁场松耦合数值模拟. 力学学报, 2024, 56(4): 1-10. DOI: 10.6052/0459-1879-23-514
Li Heng, Wang Bin, Ye Liuqing, Li Kai, Jin Ke. A loose coupling numerical simulation method between flow field and electromagnetic field of hypersonic vehicle. Chinese Journal of Theoretical and Applied Mechanics, 2024, 56(4): 1-10. DOI: 10.6052/0459-1879-23-514
Citation: Li Heng, Wang Bin, Ye Liuqing, Li Kai, Jin Ke. A loose coupling numerical simulation method between flow field and electromagnetic field of hypersonic vehicle. Chinese Journal of Theoretical and Applied Mechanics, 2024, 56(4): 1-10. DOI: 10.6052/0459-1879-23-514

高超声速飞行器流场电磁场松耦合数值模拟

A LOOSE COUPLING NUMERICAL SIMULATION METHOD BETWEEN FLOW FIELD AND ELECTROMAGNETIC FIELD OF HYPERSONIC VEHICLE

  • 摘要: 在高超声速再入式飞行器通信黑障问题众多解决方案中, 电磁调控方法是最具可行性的方法之一. 一个细致可靠的电磁调控方案不仅需要准确考虑外加电磁场对导电流体作用, 还需要考虑因流体高速运动产生的感生电磁场对导电流体的作用. 对于高超声速飞行器典型飞行状态, 全磁流体力学方法因数值刚性问题很难直接用于流场和电磁场耦合模拟, 而低磁雷诺数近似方法无法考虑感生磁场对导电流体作用. 针对磁流体力学两种经典方法应用于高超声速飞行器电磁调控方案设计时存在的困难和不足, 文章在数值求解流动控制方程N-S方程和电磁控制方程双曲Maxwell方程的基础上, 将两者结合起来松耦合迭代求解, 建立适用于高超声速飞行器流场和电磁耦合的数值模拟方法. 通过磁流体激波反射和二维超声速磁流体喷管两个典型算例, 对文章的数值方法进行验证. 基于数值方法对外加偶极子磁场作用下某高超声速飞行器典型飞行状态下流场电磁耦合问题进行了研究, 数值模拟结果表明, 磁雷诺数为0.7557时, 不考虑感生磁场对流体运动影响时激波脱体距离相对于考虑感生磁场作用时大11.11%, 此误差已不容忽视, 对于该飞行状态, 应完整考虑流场和磁场相互作用而不是仅考虑外加磁场对流场运动影响.

     

    Abstract: Among the many solutions to the communication blackout problem of hypersonic re-entry vehicles, the electromagnetic control method is one of the most feasible methods. A precise electromagnetic control scheme not only needs to accurately consider the effect of the applied electromagnetic field on the conductive fluid, but also needs to consider the effect of the induced electromagnetic field caused by the high-speed motion of the fluid on the conductive fluid. For the typical flight state of a hypersonic vehicle, the full MHD method is difficult to be directly used in the simulation of the coupling between flow field and electromagnetic field due to the problem of numerical rigidity, and the low magnetic Reynolds number approximation method cannot consider the effect of the induced magnetic field on the conductive fluid. Aiming at the difficulties and deficiencies in the application of the two classic methods of MHD to the design of electromagnetic control methods for hypersonic vehicles, this paper numerically solves the flow governing equation NS equation and the electromagnetic governing equation hyperbolic Maxwell equation, and combines them together by a loosely coupled iterative solution, and finally, a numerical simulation method suitable for coupling between flow field and electromagnetic field of hypersonic vehicle is established. The numerical method is verified by two test cases, and that is MHD shock reflection and two-dimensional supersonic MHD nozzle. Based on the numerical method in this paper, the coupling problem between flow field and electromagnetic field in a typical flight state of a hypersonic vehicle under the action of an applied dipole magnetic field is studied. The numerical simulation results show that, at the state of the magnetic Reynolds number 0.7557, when the effect of induced magnetic field on the fluid is ignored, the shock stand-off distance is 11.11% larger than that when the induced magnetic field is considered. The error cannot be ignored. For the flight state, the interaction between the flow field and the magnetic field should be fully considered instead of only considering the influence of the applied magnetic field on the flow field motion.

     

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