摘要
飞行器跨声速工况下颤振边界快速下降，是结构设计和强度校核重点关注的状态之一，目前工程中采用基于偶极子格网法的线性分析手段无法准确预测跨声速颤振边界，风洞试验仍然是研究飞行器跨声速颤振特性的重要手段。以两套颤振试验标准模型为研究对象，在FL-3风洞中开展了风洞跨声速试验研究，采用PEAK-HOLD亚临界响应分析方法预测了模型的跨声速颤振边界，并利用ZAERO和CFD/CSD耦合两种数值计算方法预测了试验模型的颤振边界。结果表明：PEAK-HOLD亚临界响应分析方法预测颤振边界具有较好的趋势性，颤振边界合理可靠；ZAERO线性方法对跨声速颤振边界的预测精度较低，而基于CFD/CSD耦合的非线性方法得到的跨声速颤振边界与试验吻合较好，相互验证了风洞试验和数值计算的可靠性。
Abstract
Aircraft’s flutter boundary fast dropping under transonic working condition is one of important states for structure design and strength checking. At present, the transonic flutter boundary can’t be correctly predicted using the linear analysis technique based on the di-pole grid method. Wind tunnel test is still an important means to study aircraft’s transonic flutter characteristics. Here, two sets of flutter test standard models were taken as the study objects to conduct wind tunnel transonic tests in the FL-3 wind tunnel. The PEAK-HOLD subcritical response analysis method was used to predict models’ transonic flutter boundary. Furthermore, the ZAERO numerical computation method and the CFD/CSD coupled one were used to predict models’ flutter boundary, respectively. The results showed that the flutter boundary predicted with the PEAK-HOLD method has a better tendency and it is reasonable and reliable; the prediction accuracy of the transonic flutter boundary using the ZAERO linear method is lower, but the transonic flutter boundary predicted using the CFD/CSD coupled nonlinear method agrees better with that using wind tunnel tests to verify the reliability of wind tunnel tests and numerical computation.
关键词
跨声速颤振 /
颤振标模 /
亚临界响应 /
风洞试验 /
数值计算
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Key words
transonic flutter /
test model /
subcritical response /
wind tunnel test /
numerical calculation
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侯良学1,2，张戈12，刘南1,2，王冬1,2，钱卫3，杨希明1,2.
基于风洞试验模型的跨声速颤振研究[J]. 振动与冲击, 2019, 38(13): 236-241
HOU Liangxue12， ZHANG Ge12， LIU Nan12，WANG Dong12，QIAN Wei3，YANG Ximing12.
Transonic flutter based on wind tunnel test model[J]. Journal of Vibration and Shock, 2019, 38(13): 236-241
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脚注
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