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 Navier-Stokes 代码的机翼模型颤振分析 对 2001 年进行的初步分析结果进行了回顾和检验。分析结果表明，尽管可以通过指定跨音速颤振特征来表达极限循环振荡 (LCO) 现象，但结果仍然存在偏差。一些问题是由于控制面驱动电机部分增大导致压力突变造成分析困难，后续分析将在以后的程序中进行处理。 2．基于数值分析的跨音速颤振非线性数学模型在两种模态中引入了非线性项，对非线性动力学方法导出的非线性数学模型进行了物理检验，大大改善了分叉特性，以适应风洞试验结果。与丹麦合作伙伴（DTU）共同举办的一次国际会议，我们讨论并证实了关注广义坐标非线性关系和广义空气动力学的数学建模方法的有效性。3。隧道试验模型和跨音速风洞试验结果 支撑控制面和连接肋的外板部分的裂纹已得到修复。福井大学与日本宇宙航空研究开发机构合作，使用机翼模型进行了颤振实验。在该机构的跨音速风洞测试中，使用其前缘控制面作为有控制和无控制状态的激励器，获得了振动机翼模型的分叉数据。 LCO在受控状态下的试验中得到了成功证实，这是全球首次在开环和闭环动压之间发生LCO，而且对于亚临界动压下的非受控状态，出现了一种新现象。据观察，机翼一旦停留在 LCO 处就会兴奋，然后在去除振荡源后停止颤动。

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

Subcritical Hopf Bifurcation of Transonic Flutter in Open and Closed Loop System

开环和闭环系统中跨音速颤振的亚临界Hopf分岔

• 发表时间: 2005
• 期刊: Proceedings of the International Conference on Computational and Experimental Engineering and Sciences, Keynote Lecture, Chennai, India
• 作者: H.Matsushita;K.Saitoh
• 通讯作者: K.Saitoh