Fluid-Structure Interaction Mechanism of Hypersonic Aircraft in Plasma Environment

doi:10.12382/bgxb.2022.0477

Abstract

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

CLC Number:

O362

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

Figures/Tables 11

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^-

Fig.1 Geometric dimensions of RAM C-Ⅱ

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

Fig.2 Structured meshing

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

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

Fig.5 Mises stress of aircraft under fluid structure coupling

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

Fig.7 Wall thermodynamic temperature at different velocities

Fig.8 Plasma distribution on boundary in Ma=22

Fig.9 Influence of plasma aerodynamic load

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