气动力/热与结构多场耦合试验模型方案初步设计

doi:10.7527/S1000-6893.2017.221165

固体力学与飞行器总体设计

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气动力/热与结构多场耦合试验模型方案初步设计

刘磊¹, 代光月¹, 曾磊¹, 王振锋², 桂业伟¹

1. 中国空气动力研究与发展中心空气动力学国家重点实验室, 绵阳 621000;
2. 中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室, 绵阳 621000

收稿日期:2017-02-06 修回日期:2017-04-26 出版日期:2017-11-15 发布日期:2017-04-26
通讯作者: 曾磊 E-mail:zenglei0ok@126.com
基金资助:
国家自然科学基金（11472295）

Preliminary test model design of fluid-thermal-structural interaction problems

LIU Lei¹, DAI Guangyue¹, ZENG Lei¹, WANG Zhenfeng², GUI Yewei¹

1. State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China;
2. Science and Technology on Scramjet Laboratory, Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2017-02-06 Revised:2017-04-26 Online:2017-11-15 Published:2017-04-26
Supported by:
National Natural Science Foundation of China (11472295)

摘要/Abstract

摘要：

以多渠道、多机制交叉耦合为热防护结构特点的新一代高超声速飞行器必须采用气动力/热与结构多场耦合计算方法进行研究。目前，国外已建立较完善的耦合分析系统并用于飞行器研制，国内的中国空气动力研究与发展中心（CARDC）也已自主研发了热环境/热响应耦合计算平台（FL-CAPTER）。为验证多场耦合计算平台所用方法的有效性和计算结果的准确性，设计并开展气动力/热与结构耦合的地面试验具有十分重要的意义。本文结合气动力/热与结构多场耦合试验设计需求，以现有材料和设备能力为依托，开展了试验风洞选取、模型尺寸估算、模型材料选择、模型气动设计与模型结构设计工作。初步研究表明，模型支撑结构附近迎风面局部高温热膨胀将有利于模型前体结构产生可观的整体变形量。本文以此设计了带压缩拐角的二级压缩面结构模型，通过短时间不锈钢模型验证试验和计算对比分析初步验证了模型设计的可行性，并以此为基础预测了高温合金模型的试验结果。为下一步开展高温合金长时间风洞试验奠定了技术基础。

关键词: 多场耦合, 试验模型, 设计, 气动热, 热响应, 热变形

Abstract:

The thermal protection system, which relates to the safety of hypersonic vehicle, is one of the key techniques for the design and manufacture of hypersonic vehicles. The new thermal protection mode based on multi-channel coupling is becoming the main thermal protection mode for new generation hypersonic vehicles. The computation strategy and method for fluid-thermal-structural coupling problem must be considered under this new mode. At present, a mature coupling analysis system has been established and been used in aircraft development abord. In China, the in-house Coupled Analysis Platform for Thermal Environment and structure Response (FL-CAPTER) platform has also been independently developed by China Aerodynamic Research and Development Center (CARDC). In order to verify the effectiveness of the multi-field coupling calculation method, designing a wind tunnel test has very important significance. In this paper, according to coupling test requirements, wind tunnel selection, model size estimation, model material selection, model aerodynamic design and model structure design are carried out based on existing materials and equipment capacities. The preliminary study shows that the local high temperature near the model support structure will be beneficial to produce a considerable deformation in front of the model. On this basis, the exploratory design of the test model is carried out, and the short time wind tunnel test of the stainless steel model is completed. The test model is calculated using the in-house FL-CAPTER platform. The results show that the test model is feasible. This work establishes the foundation for improving the high-temperature alloy test model design.

Key words: multi-field coupling, test model, design, aeroheating, thermal response, thermal deformation

中图分类号:

V211.3

刘磊, 代光月, 曾磊, 王振锋, 桂业伟. 气动力/热与结构多场耦合试验模型方案初步设计[J]. 航空学报, 2017, 38(11): 221165-221165.

LIU Lei, DAI Guangyue, ZENG Lei, WANG Zhenfeng, GUI Yewei. Preliminary test model design of fluid-thermal-structural interaction problems[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(11): 221165-221165.

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

气动力/热与结构多场耦合试验模型方案初步设计

Preliminary test model design of fluid-thermal-structural interaction problems

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