Temperature Prediction of Rocket Control Cabin Based on Test Ballistic Data

FU Xiaowu; MAO Rui; DU Fenghuai

doi:10.15892/j.cnki.djzdxb.2025.01.010

Journal of Projectiles, Rockets, Missiles and Guidance >

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

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

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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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

Cite this article

FU Xiaowu , MAO Rui , DU Fenghuai . Temperature Prediction of Rocket Control Cabin Based on Test Ballistic Data[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2025 , 45(1) : 75 -79 . DOI: 10.15892/j.cnki.djzdxb.2025.01.010

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References

Publishing order | Descend order by publishing year | Descend order by cited within

[1]	王杰. 高超声速飞行器气动加热计算技术[D]. 南京: 南京航空航天大学, 2011. WANG J. Calculating method of aerodynamic heating for hypersonic aircrafts[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2011.

[2]	胡锐锋. 高速飞行气动环境、气动特性快速预测与应用[D]. 北京: 清华大学, 2012. HU R F. Aerodynamic environment and fast estimation methods for high speed flight with applications[D]. Beijing: Tsinghua University, 2012.

[3]	霍霖. 复杂外形高超声速飞行器气动热快速工程估算及热响应分析[D]. 长沙: 国防科学技术大学, 2012. HUO L. The rapid engineering aero-heating calculation and thermal respond for complex shaped hypersonic vehicles[D]. Changsha: National University of Defense Technology, 2012.

[4]	王俊. 高超声速飞行器气动热烧蚀预测与控制研究[D]. 广州: 华南理工大学, 2013. WANG J. Research on aerodynamic thermal ablation prediction and control for hypersonic vehicle[D]. Guangzhou: South China University of Technology, 2013.

[5]	张志豪, 孙得川. 飞行器气动加热烧蚀工程计算[J]. 兵工学报, 2015, 36(10):1949-1954. DOI ZHANG Z H, SUN D C. Calculation of aerodynamic heating and ablation of multi-layer thermal protection material[J]. Acta Armamentarii, 2015, 36(10):1949-1954.

[6]	孟竹喧, 胡凡, 彭科, 等. 高超声速助推滑翔飞行器气动热环境仿真分析[J]. 固体火箭技术, 2016, 39(2): 295-300. MENG Z X, HU F, PENG K, et al. Simulation and analysis of thermal environment calculation for hypersonic boost glide vehicle[J]. Journal of Solid Rocket Technology, 2016, 39 (2):295-300.

[7]	彭科. 飞行器气动力/热高精度快速计算方法及应用研究[D]. 长沙: 国防科学技术大学, 2016. PENG K. Accurate and rapid method of aircraft aero-force & aero-heating calculation and research on applications[D]. Changsha: National University of Defense Technology, 2016.

[8]	王晓婕. 飞行器沿弹道气动烧蚀过程数值模拟研究[D]. 大连: 大连理工大学, 2017. WANG X J. Research on numerical simulation of the process of airspace vehicles' ablation along the trajectory[D]. Dalian: Dalian University of Technology, 2017.

[9]	李佳伟, 王江峰, 程克明, 等. 高超声速全机外形气动加热与结构传热快速计算方法[J]. 空气动力学学报, 2019, 37(6):956-965. LI J W, WANG J F, CHENG K M, et al. Rapid method for calculating aero-heating coupled with structure heat transfer on hypersonic vehicles[J]. Acta Aerodynamica Sinica, 2019, 37(6):956-965.

[10]	洪元, 刘亮堂, 杨立明, 等. 气动加热环境下壁面热响应的快速分析方法[J]. 弹箭与制导学报, 2022, 42(1):82-85. DOI HONG Y, LIU L T, YANG L M, et al. A fast method to analyze thermal response of shell to aerodynamic heating[J]. Journal of Projectiles,Rockets,Missiles and Guidance, 2022, 42(1):82-85.

[11]	ZOBY E V, MOSS J N, SUTTON K. Approximate convective-heating equations for hypersonic flows[J]. Journal of Spacecraft and Rockets, 1981, 18(1):64-70.

[12]	CORDA S, ANDERSON J D. Viscous optimized hypersonic waveriders designed from axisymmetric flow fields:AIAA 88-0369[R]. AIAA 26th Aerospace Sciences Meeting. Reno:AIAA, 1988.

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