NONLINEAR MATHEMATICAL MODELING OF TRANSONIC FLUTTER BY NONLINEAR DYNAMICS APPROACH

采用非线性动力学方法对跨声速颤振进行非线性数学建模

• 批准号: 15560684
• 负责人: MATSUSHITA Hiroshi
• 金额: $ 1.92万
• 依托单位: UNIVERSITY OF FUKUI
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (C)
• 财政年份: 2003
• 资助国家: 日本
• 起止时间: 2003 至 2005
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-15560684/
• 关键词: INTERNATIONAL PERSONNEL EXCHANGE; DENMARK, HANGARY; AIRCRAFT; TRANSONIC FLUTTER; LIMIT CYCLE OSCILLATION; HOPF BIFURCATION

1. Flutter analysis based on Navier-Stokes code for a wing modelPreliminary analysis results conducted in 2001 has been reviewed and examined. The analytical results show that even though limit cycle oscillation (LCO) phenomena can be expressed specifying transonic flutter features, the results have some problems because an abrupt pressure change due to the enlarged part accommodating driving motors for control surfaces causes analytical difficulties. The follow-on analysis will be treated in the future program.2. Improvement of a nonlinear mathematical model for transonic flutter based on numerical analysisNonlinear terms are introduced in two modes making physical examination to nonlinear mathematical model derived in nonlinear dynamics approach. The bifurcation characteristics have been greatly improved accordingly to fit the wind tunnel test results. The results were presented at an international conference co-authored with a collaborative partner in Denmark (DTU). We discussed and … More confirmed the validity of mathematical modeling approach focusing the nonlinear relationship of generalized coordinates and the generalized aerodynamics.3. Refurbishing a wind tunnel test model and the results of transonic wind tunnel testsCracks at the part of the outer panel supporting a control surface and connecting ribs have been repaired. As the cooperation between the University of Fukui and the Japan Aerospace Exploration Agency, flutter experiment using a wing model at the agency's transonic wind tunnel has been carried out. In the tests bifurcation data have been obtained vibrating the wing model using its leading edge control surface as an exciter for the states with and without control. As a result, stability boundary and LCO have been successively confirmed in the test for controlled state. It is worldwide first time that LCO can happen at the dynamic pressure between the open loop and the closed loop flutter. Furthermore, for uncontrolled state at the subcritical dynamic pressure, a new phenomenon has been observed that the wing excited once staying in LCO then ceased flutter after removing the oscillation source. Less

1。基于在2001年进行的机翼模型初步分析结果的Navier-Stokes代码的扑打分析已进行了审查和检查。分析结果表明，即使极限循环振荡（LCO）现象可以表达为指定跨声音扑朔迷离特征，但结果存在一些问题，因为由于零件扩大而导致的驱动器驱动器会导致控制表面的突然变化，导致了分析困难。后续分析将在未来计划中进行处理2。基于数值分析术语的跨音量扑波的非线性数学模型的改进以两种模式引入，从而使在非线性动力学方法中得出的非线性数学模型进行了体格检查。分叉特征已得到相应的相应改进，以适应风洞测试结果。结果是在与丹麦（DTU）合作合作伙伴合着的国际会议上提出的。我们讨论并…更多地证实了数学建模方法的有效性，该方法集中了广义坐标和广义空气动力学的非线性关系3。翻新风洞测试模型以及支撑控制表面和连接肋骨的外面板部分的跨声音风隧道测试的结果已被修复。随着福岛大学与日本航空航天勘探局之间的合作，在该机构的跨性别风隧道上使用机翼模型的Flutter实验已经进行了。在测试中，分叉数据已经获得了翅膀模型的振动，它使用其前缘控制表面作为具有和没有控制的状态的激发仪。结果，在受控状态的测试中已成功确认了稳定性边界和LCO。在全球范围内，LCO首次可以在开环和闭环颤动之间的动态压力下发生。此外，对于在亚临界动态压力下的不受控制的状态，已经观察到一种新现象，即一旦停留在LCO中的机翼兴奋，然后在去除振荡源后停止了颤动。较少的

项目成果

LQG Flutter Control of Wind Tunnel Model Using Piezo-Ceramic Actuator

使用压电陶瓷执行器的风洞模型 LQG 颤振控制

• 发表时间: 2006
• 期刊: Proceedings of the 25th International Congress of the Aeronautical Sciences, Hamburg, Germany
• 作者: T.Kaneko;Y.Asano
• 通讯作者: Y.Asano

Experimental Confirmation of Limit Cycle Oscillation for Active Control of Transonic Flutter in Wind Tunnel

风洞跨音速颤振主动控制极限环振荡的实验验证

• 发表时间: 2006
• 期刊: Proceedings of the 25th International Congress of the Aeronautical Sciences, Hamburg, Germany
• 作者: H.Matsushita;J.Hatta;K.Saitoh
• 通讯作者: K.Saitoh

H.Matsushita, T.Miyata, M.Kawai, E.Mosekilde: "Nonlinear Mathematical Modeling of Aircraft Wing Flutter in Transonic Range"Proceedings of International Conference on Physics and Control 2003. 1-1. 195-199 (2003)

H.Matsushita、T.Miyata、M.Kawai、E.Mosekilde：“跨音速范围内飞机机翼颤振的非线性数学建模”2003 年国际物理与控制会议论文集。1-1。

Four-Mode Modeling of Nonlinear Characteristic of Transonic Flutter

跨音速颤振非线性特性的四模态建模

• 发表时间: 2004
• 期刊: KSASS-JSASS Joint Symposium on Aerospace Engineering. 42nd JSASS Aircraft Symposium 1
• 作者: J.Hatta;K.Imamura;H.Matsushita
• 通讯作者: H.Matsushita

Present Research Status at the System Control Group 1

系统控制组1的研究现状

• 发表时间: 2004
• 期刊: Proceedings of 4^<th> PKNU-UoF International Symposium on Advanced Mechanical Engineering 1
• 作者: H.Matsushita;M.Kawai
• 通讯作者: M.Kawai