NONLINEAR MATHEMATICAL MODELING OF TRANSONIC FLUTTER BY NONLINEAR DYNAMICS APPROACH
| Project/Area Number |
15560684
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| Research Category |
Grant-in-Aid for Scientific Research (C)
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| Allocation Type | Single-year Grants |
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| Section | 一般 |
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| Research Field |
Aerospace engineering
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| Research Institution | UNIVERSITY OF FUKUI |
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Principal Investigator |
MATSUSHITA Hiroshi UNIVERSITY OF FUKUI, FACALTY OF ENGINEERING, PROFESSOR, 工学部, 教授 (90334804)
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| Co-Investigator(Kenkyū-buntansha) |
NAKAMICHI Jiro JAPAN AEROSPACE EXPLORATION AGENCY, AVIATION PROGRAM GROUP, TEAM LEADER, 航空プログラムグループ, チーム長 (30358684)
SAITOH Kenichi JAPAN AEROSPACE EXPLORATION AGENCY, INSTITUTE OF AEROSPACE TECHNOLOGY, RESEARCHER, 総合技術研究本部, 研究員 (70358688)
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| Project Period (FY) |
2003 – 2005
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| Project Status |
Completed (Fiscal Year 2005)
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| Budget Amount *help |
¥3,000,000 (Direct Cost: ¥3,000,000)
Fiscal Year 2005: ¥600,000 (Direct Cost: ¥600,000)
Fiscal Year 2004: ¥1,300,000 (Direct Cost: ¥1,300,000)
Fiscal Year 2003: ¥1,100,000 (Direct Cost: ¥1,100,000)
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| Keywords | INTERNATIONAL PERSONNEL EXCHANGE / DENMARK, HANGARY / AIRCRAFT / TRANSONIC FLUTTER / LIMIT CYCLE OSCILLATION / HOPF BIFURCATION |
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| Research Abstract |
1. Flutter analysis based on Navier-Stokes code for a wing model
Preliminary 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 analysis
Nonlinear 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 tests
Cracks 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
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Report
(4 results)
Research Products
(23 results)
