等离子体环境下高超声速飞行器的流-固耦合机制

doi:10.12382/bgxb.2022.0477

摘要/Abstract

摘要：

高超声速飞行器在高温空气中穿行时处于等离子体环境中,相较于热完全气体有较大不同。考虑等离子体真实气体效应才能更好地计算飞行器与周围流体的流体与固体(简称流固)耦合作用。基于等离子体化学非平衡流体动力学方程组,结合流固耦合方程建立流固耦合模型。以RAM-C飞行器为算例计算并验证该模型,分析飞行器的流固耦合作用机制。计算结果表明:等离子体相较于热完全气体,气动压力增大,气动黏性力增大,最大气动黏性力位置发生迁移;等离子体气动荷载的作用位置利于钝体承受,最大流固耦合应力相较于热完全气体更小;高速飞行器前端主要承受原子气体的流固耦合作用,电子和离子对飞行器的流固耦合作用十分微小,在中部及后部分子气体对飞行器的作用更加明显。

关键词: 高超声速飞行器, 流固耦合, 等离子体, 热化学非平衡, 真实气体

Abstract:

Hypersonic vehicles are in a plasma environment when passing through high-temperature air, different from thermal perfect gas conditions. Accounting for the real gas effect of plasma is crucial for accurately calculate the fluid structure interaction between aircraft and surrounding fluid. In this paper, based on the plasma chemical non-equilibrium hydrodynamic equations, combined with the fluid solid coupling equations, a fluid solid coupling model is established. Taking the RAM-C aircraft as an example, the model is calculated and verified, and the fluid structure interaction mechanism of the aircraft is discussed. The results show that the aerodynamic pressure and aerodynamic viscosity of plasma increase, and the position of the maximum aerodynamic viscosity shifts compared with that of thermal perfect gas. The position of plasma aerodynamic load is favorable for the bluff body to bear, and the maximum fluid solid coupling stress is less than that of thermal perfect gas. The front end of high-speed aircraft mainly bears the fluid solid coupling of atomic gas, while the fluid solid coupling of electrons and ions on the aircraft is very low. The effect of molecular gas on the aircraft is more obvious in the middle and rear parts.

Key words: hypersonic vehicle, fluid structure coupling, plasma, thermochemical nonequilibrium, real gas

中图分类号:

O362

王琛, 田振国, 沈振兴. 等离子体环境下高超声速飞行器的流-固耦合机制[J]. 兵工学报, 2023, 44(10): 3038-3046.

WANG Chen, TIAN Zhenguo, SHEN Zhenxing. Fluid-Structure Interaction Mechanism of Hypersonic Aircraft in Plasma Environment[J]. Acta Armamentarii, 2023, 44(10): 3038-3046.

图/表 11

表1 化学反应式

Table 1 Chemical reaction

化学反应式	第三碰撞体M_i
O₂+M₁ $\rightleftarrows$ 2O+M₁	O,N,O₂,N₂,NO
N₂+M₂ $\rightleftarrows$ 2N+M₂	O,O₂,N₂,NO
N₂+N $\rightleftarrows$ 2N+N
NO+M₃ $\rightleftarrows$ N+O+M₃	O,N,O₂,N₂,NO
NO+O $\rightleftarrows$ O₂+N
N₂+O $\rightleftarrows$ NO+N
N+O $\rightleftarrows$ NO⁺+e^-

表1 化学反应式

Table 1 Chemical reaction

化学反应式	第三碰撞体M_i
O₂+M₁ $\rightleftarrows$ 2O+M₁	O,N,O₂,N₂,NO
N₂+M₂ $\rightleftarrows$ 2N+M₂	O,O₂,N₂,NO
N₂+N $\rightleftarrows$ 2N+N
NO+M₃ $\rightleftarrows$ N+O+M₃	O,N,O₂,N₂,NO
NO+O $\rightleftarrows$ O₂+N
N₂+O $\rightleftarrows$ NO+N
N+O $\rightleftarrows$ NO⁺+e^-

图1 RAM C-Ⅱ的几何尺寸

Fig.1 Geometric dimensions of RAM C-Ⅱ

表2 算例检验

Table 2 Example test

网格划分方法	温度/ 10⁴K	电子数密度/ 10²⁰m^-3	应力/ (10⁴N·m^-2)
文献[4]	1.515	1.150
40×(50+4)网格	1.58	4.09	3.43
50×(60+6)网格	1.57	4.12	3.42
60×(70+8)网格	1.57	4.10	3.42

图2 结构化网格划分

Fig.2 Structured meshing

图3 等离子体与热完全气体的气动力对比

Fig.3 Comparison of aerodynamic forces between plasma and thermal perfect gas

图4 等离子体和热完全气体的冲击与摩擦对比

Fig.4 Shock and friction comparison for plasma and thermal perfect gas

图5 流固耦合作用下飞行器的Mises应力

Fig.5 Mises stress of aircraft under fluid structure coupling

图6 不同速度下等离子体组分壁面分布

Fig.6 Distribution of plasma components on the wall at different velocities

图7 不同速度下的壁面热力学温度

Fig.7 Wall thermodynamic temperature at different velocities

图8 Ma=22等离子体壁面分布

Fig.8 Plasma distribution on boundary in Ma=22

图9 等离子体气动荷载影响

Fig.9 Influence of plasma aerodynamic load

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