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弹箭与制导学报 >

2025 , Vol. 45 >Issue 1: 75 - 79

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.01.010

基于试验弹道数据的火箭弹控制舱温度预测

  • 付小武 , 1, 2 ,
  • 毛瑞 1, 2 ,
  • 杜凤怀 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

付小武(1987—),男,高级工程师,博士。E-mail:

收稿日期: 2024-05-29

  网络出版日期: 2025-03-12

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Temperature Prediction of Rocket Control Cabin Based on Test Ballistic Data

  • FU Xiaowu , 1, 2 ,
  • MAO Rui 1, 2 ,
  • DU Fenghuai 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

Received date: 2024-05-29

  Online published: 2025-03-12

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摘要

通过气动热和结构热响应计算对火箭弹控制舱的温度进行了预测,并通过飞行试验进行了验证。首先,选取弹道特征点并进行转捩判断,通过计算流体力学和工程计算方法相结合得到火箭弹飞行的气动热环境;然后,基于有限差分方法,得到火箭弹控制舱处防热结构的温度响应;最后,将数值计算结果同飞行试验数据进行对比分析。结果表明,数值预测的火箭弹控制舱内壁最高温度比飞行试验值高5.6%,文中的数值预测方法可用于火箭弹的防热设计。

关键词： 弹道; 气动热; 温度响应; 飞行试验

本文引用格式

付小武 , 毛瑞 , 杜凤怀 . 基于试验弹道数据的火箭弹控制舱温度预测[J]. 弹箭与制导学报, 2025 , 45(1) : 75 -79 . DOI: 10.15892/j.cnki.djzdxb.2025.01.010

Abstract

The temperature of the rocket control cabin is predicted by aerodynamic heating and structural thermal response calculation, and verified by flight test. Firstly, the ballistic feature points are selected and transition is judged. The aerodynamic thermal environment of the rocket flight is obtained by the combination of computational fluid dynamics and engineering calculation methods. Then, based on the finite difference method, the temperature response of the heat protection structure at the rocket control cabin is obtained. Finally, the numerical calculation results are compared with the flight test data. The numerically predicted maximum temperature of the inner wall of the rocket control cabin is 5.6% higher than the flight test value, and the numerical prediction method in this paper can be used in the thermal protection design of the rocket.

Key words： ballistic trajectory; aerodynamic heating; temperature response; flight test

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