类X-43A飞行器高超声速分离仿真

doi:10.7527/S1000-6893.2021.25171

Abstract

Abstract: Stage separation process widely exists in the military and aerospace applications of hypersonic aerocraft. To further understand the aerodynamic interference and parameter effects in the process, an aerocraft similar to X-43A is chosen as the research object, and the simulation method of mesh deformation/local grid reconstruction adopted. The typical flow field structure, particularly the interstage interference between the aerocraft and the assistor, during the separation process is analysed. Additionally, the influences of the initial angle of attack and ejection force on the axial and normal relative distance, aerodynamic force and the angle of attack during the separation process are emphatically discussed. The results show that the interstage separation process is disturbed by the vortex and shock waves. The angle of attack has a large effect on the relative distance between the aerocraft and the assistor, and a small or negative angle of attack is more helpful for the safe separation. The ejection force has a significant influence on the axial relative distance, and a larger ejection force enables faster separation of the aerocraft from the interstage interference zone to reach a safe separation distance.

Key words: aerocraft similar to X-43A, hypersonic separation, mesh deformation, local grid reconstruction, aerodynamic interference

CLC Number:

V421

ZHAO Fei, LIU Liling, SHI Yong, ZUO Guang, WAN Qian, ZHANG Yujia. Hypersonic separation simulation of aerocraft similar to X-43A[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(5): 125171-125171.

References

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Hypersonic separation simulation of aerocraft similar to X-43A

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