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弹箭与制导学报 >

2025 , Vol. 45 >Issue 3: 295 - 302

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.03.004

可见、红外图像感知、目标识别与制导技术

气动加热下蓝宝石窗口温度对红外成像的影响

  • 付小武 , 1, 2 ,
  • 史明东 3 ,
  • 毛瑞 1, 2
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  • 1 陆空基信息感知与控制全国重点实验室,陕西 西安 710065
  • 2 西安现代控制技术研究所,陕西 西安 710065
  • 3 西安导引科技有限责任公司,陕西 西安 710065

付小武(1987—),男,高级工程师,博士。E-mail:

收稿日期: 2025-02-27

  网络出版日期: 2025-07-09

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Effect of Sapphire Window Temperature on Infrared Imaging under Aerodynamic Heating

  • FU Xiaowu , 1, 2 ,
  • SHI Mingdong 3 ,
  • MAO Rui 1, 2
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  • 1 National Key Laboratory of Land and Air Based Information Perception and Control,Xi'an 710065,Shaanxi,China
  • 2 Xi'an Modern Control Technology Research Institute,Xi'an 710065,Shaanxi,China
  • 3 Xi'an Guidance Technology Co.,Ltd.,Xi'an 710065,Shaanxi,China

Received date: 2025-02-27

  Online published: 2025-07-09

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摘要

针对高速火箭弹末制导红外成像受气动加热影响的问题,通过数值模拟得到了蓝宝石红外窗口结构受气动加热引起的温度响应,在此基础上设计了风洞试验,研究了气动加热对红外导引头成像的影响。在数值模拟中,采用计算流体力学和工程算法相结合的方法得到红外头罩沿弹道的气动热,通过有限元方法得到头罩结构的温度响应。在风洞试验中,通过在头罩内表面布置测点,得到气动加热下头罩结构的温度响应,并测试了气动加热下红外导引头的成像效果。研究结果表明:在气动加热下,头罩内壁最高温度148 ℃远高于探测目标温度27 ℃,需根据蓝宝石窗口温度减少红外探测器的积分时间,并调整成像算法来进行图像纠正。

关键词： 气动热; 温度响应; 风洞试验; 红外成像

本文引用格式

付小武 , 史明东 , 毛瑞 . 气动加热下蓝宝石窗口温度对红外成像的影响[J]. 弹箭与制导学报, 2025 , 45(3) : 295 -302 . DOI: 10.15892/j.cnki.djzdxb.2025.03.004

Abstract

In view of the problem that the infrared imaging for terminal guidance of rockets is affected by aerodynamic heating, the temperature response of the sapphire infraredwindow structure caused by aerodynamic heating is obtained through numerical simulation. On this basis, a wind tunnel test is designed to study the effect of aerodynamic heating on the infrared imaging of the seeker. In the numerical simulation, the aerodynamic heating of the infrared dome along the ballistic trajectory is obtained by combining computational fluid dynamics and engineering algorithms, and the temperature response of the dome structure is obtained by the finite element method. In the wind tunnel test, measuring points are installed on the inner surface of the dome to obtain the temperature response of the dome structure under aerodynamic heating, and the imaging effect of the infrared seeker under aerodynamic heating is tested. The research results show that, under aerodynamic heating, the highestinner wall temperature of the dome is 148 ℃, which is much higher than the target temperature of 27 ℃. Based on the sapphire window temperature, it needs to reduce the integration time of the infrared detector and adjust imaging algorithmto perform image correction.

Key words： aerodynamic heating; temperature response; wind tunnel test; infrared imaging

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