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弹箭与制导学报 >

2023 , Vol. 43 >Issue 4: 68 - 73

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2023.04.010

攻角对整流罩温度场分布影响研究

  • 罗维 1 ,
  • 张雪峰 2 ,
  • 王秉政 3 ,
  • 刘星 1 ,
  • 朱天社 3
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  • 1 西安工业大学电子信息工程学院,陕西 西安 710021
  • 2 北京宇航系统工程研究所,北京 100076
  • 3 西北工业集团有限公司,陕西 西安 710043
刘星(1975—),男,研究员级高工,博士,研究方向:目标探测与识别。

罗维(1998—),女,硕士研究生,研究方向:整流罩温度场及红外制导。

收稿日期: 2022-12-02

  网络出版日期: 2025-02-07

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Study on the Influence of Angle of Attack on the Temperature Field Distribution of Fairing

  • LUO Wei 1 ,
  • ZHANG Xuefeng 2 ,
  • WANG Bingzheng 3 ,
  • LIU Xing 1 ,
  • ZHU Tianshe 3
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  • 1 School of Electronic Information Engineering, Xi'an Technology University, Xi'an 710021, Shaanxi, China
  • 2 Beijing Institute of Astronautical Systems Engineering, Beijing 100076,China
  • 3 Northwest Industrial Group Co., Ltd., Xi'an 710043, Shaanxi, China

Received date: 2022-12-02

  Online published: 2025-02-07

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摘要

针对整流罩温度场分布易受飞行攻角的影响问题,依据空气动力学理论建立整流罩的温度场模型,将数值计算的精确性与工程计算的高效性相结合,研究飞行器整流罩温度场分布情况,采用Fluent流体力学仿真软件,对基于蓝宝石(Al2O3)的整流罩在20 km高度、飞行速度5Ma、0°~15°不同攻角条件下的整流罩温度场分布进行仿真分析。结果表明: 在0°攻角下整流罩温度场相对于罩轴呈现轴对称分布,在15°攻角下整流罩的表面温度场呈现明显的不对称分布;小攻角飞行条件整流罩迎风、背风侧温度相差较小,15°大攻角飞行条件整流罩迎风面比背风面温度增加208.66 K。研究结果可为高超声速导弹整流罩热防护设计提供参考。

关键词： 整流罩; 攻角; 温度场; Fluent

本文引用格式

罗维 , 张雪峰 , 王秉政 , 刘星 , 朱天社 . 攻角对整流罩温度场分布影响研究[J]. 弹箭与制导学报, 2023 , 43(4) : 68 -73 . DOI: 10.15892/j.cnki.djzdxb.2023.04.010

Abstract

Aiming at the problem that the temperature field distribution of the fairing is easily affected by the flight angle of attack, the temperature field model of the fairing is established according to the aerodynamic theory, and the accuracy of the numerical calculation is combined with the efficiency of the engineering calculation to study the temperature field distribution of the aircraft fairing Fluent fluid mechanics simulation software is used to simulate and analyze the temperature field distribution of the fairing based on sapphire (Al2O3) at a height of 20 km, a flight speed of Mach 5, and different angles of attack from 0° to 15°. The results show that: at 0° angle of attack, the temperature field of the fairing presents an axisymmetric distribution relative to the axis of the fairing, and at 15° the surface temperature field of the fairing presents an obvious asymmetric distribution. The temperature difference on the leeward side is small, and the temperature on the windward side of the fairing is 208.66 K higher than that on the leeward side under the flight condition of a high angle of attack of 15°. Research results can provide reference for thermal protection design of hypersonic missile fairing.

Key words： fairing; angle of attack; temperature field; Fluent

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