Research on Aerodynamic Characteristics of Inlet Fairing Separation from a Hypersonic Missile

PANG Chuanbo; XIANG Yuwei; MA Xingpu; JIANG Shengju

doi:10.15892/j.cnki.djzdxb.2020.03.028

Journal of Projectiles, Rockets, Missiles and Guidance >

2020 , Vol. 40 >Issue 3: 123 - 128

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2020.03.028

Research on Aerodynamic Characteristics of Inlet Fairing Separation from a Hypersonic Missile

PANG Chuanbo ,
XIANG Yuwei ,
MA Xingpu ,
JIANG Shengju

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Xi’an Modern Control Technology Research Institute, Xi’an 710065, China

Received date: 2019-05-14

Online published: 2025-02-12

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Abstract

Unsteady CFD method based on dynamic chimera grid combined with CFE has been used to simulate fairing separation from a hypersonic missile, the security and interference characteristic of the process was analyzed and discussed. The result shows when the fairing stays a larger pitch angle, it is more secure and takes less time during the process, but the interference is stronger and lasts longer. The attitude angle of the fairing can be effective adjusted by designing its mass distribution and release angle rationally.

Key words： multi-body interference; separation; inlet fairing; unsteady

Cite this article

PANG Chuanbo , XIANG Yuwei , MA Xingpu , JIANG Shengju . Research on Aerodynamic Characteristics of Inlet Fairing Separation from a Hypersonic Missile[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2020 , 40(3) : 123 -128 . DOI: 10.15892/j.cnki.djzdxb.2020.03.028

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