高超声速飞行器流热固耦合实时仿真技术

doi:10.16182/j.issn1004731x.joss.21-FZ0838

系统仿真学报 ›› 2021, Vol. 33 ›› Issue (12): 2820-2827.doi: 10.16182/j.issn1004731x.joss.21-FZ0838

高超声速飞行器流热固耦合实时仿真技术

刘云钦¹, 李妮¹, 赵路明¹, 白金鹏², 李婷珽², 王晨光²

1.北京航空航天大学,自动化科学与电气工程学院,北京 100191;
2.空战系统技术航空科技重点实验室,辽宁沈阳 110035

收稿日期:2021-06-08 修回日期:2021-08-18 出版日期:2021-12-18 发布日期:2022-01-13
作者简介:刘云钦(1999-),男,硕士生,研究方向为系统建模与仿真。E-mail：2581219875@qq.com
基金资助:
国家自然科学基金(61773032)

Real-time Simulation Technology of Fluid-thermo-solid Coupling of Hypersonic Vehicle

Liu Yunqin¹, Li Ni¹, Zhao Luming¹, Bai Jinpeng², Li Tingjun², Wang Chenguang²

1. School of Automation Science and Electrical Engineering, Beihang University, Beijing 100191, China;
2. Key Laboratory of Aviation Science and Technology of Air Combat System Technology, Shenyang 110035, China

Received:2021-06-08 Revised:2021-08-18 Online:2021-12-18 Published:2022-01-13

摘要/Abstract

摘要： 高超声速飞行器建模中流热固物理场耦合特性求解是不可回避的难点,流热固耦合实时仿真尤其具有挑战。针对流热固耦合实时仿真中求解精度和求解效率相互矛盾的问题,建立了一种基于计算流体力学/计算结构力学的流热固耦合特性求解方法,实现了流体、温度、结构形变场耦合的高精度求解。根据多工况离线解集建模方法,通过积累大量离线解作为在线计算的有效支撑,平衡了求解精度和求解效率的矛盾。进行了虚拟试飞试验,分析了流热固耦合效应对飞行器攻角和净推力的影响,并与NASA实验数据进行对比,验证了模型的正确性。

关键词: 高超声速飞行器, 流热固物理场耦合, 实时仿真, 多工况离线解集, 虚拟试飞

Abstract: The solution of the coupling characteristics of fluid-thermo-solid physics in the modeling of hypersonic vehicle is an unavoidable difficulty, and the real-time simulation of fluid-thermo-solid coupling is particularly challenging. Aiming at the conflicting problem of solution accuracy and solution efficiency in fluid-thermo-solid coupling real-time simulation, a CFD (Computational Fluid Dynamics)/ CSD (Computational Structural Dynamics)-based fluid-thermo-solid coupling characteristic solution method is established, which realizes the high-precision solution of the fluid, temperature, and structural deformation field coupling. According to the multi-condition offline solution set modeling method, by accumulating a large number of offline solutions as effective support for online calculation, the contradiction between solution accuracy and solution efficiency is balanced. A virtual flight test is carried out to analyze the influence of the coupling effect on the angle of attack and net thrust of the aircraft, and compared with NASA experimental data to verify the correctness of the model.

Key words: hypersonic vehicle, fluid-thermo-solid physics coupling, real-time simulation, multi-condition offline solution set, virtual test flight

中图分类号:

TP391.9

刘云钦, 李妮, 赵路明, 白金鹏, 李婷珽, 王晨光. 高超声速飞行器流热固耦合实时仿真技术[J]. 系统仿真学报, 2021, 33(12): 2820-2827.

Liu Yunqin, Li Ni, Zhao Luming, Bai Jinpeng, Li Tingjun, Wang Chenguang. Real-time Simulation Technology of Fluid-thermo-solid Coupling of Hypersonic Vehicle[J]. Journal of System Simulation, 2021, 33(12): 2820-2827.

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高超声速飞行器流热固耦合实时仿真技术

Real-time Simulation Technology of Fluid-thermo-solid Coupling of Hypersonic Vehicle

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