New Estimation Method for Flutter or Divergence Boundary from Random Responses at Subcritical Speeds

Material type: 文書・図像類

Author: 松崎, 雄嗣ほか

Publisher: 航空宇宙技術研究所

Publication date: 1981-04

Material Format: Digital

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Note (General)：: 従来の様に減衰率と振動数の測定や推定をすることなく,サブクリティカルな領域での気流の乱れによって励振された応答からフラッタ限界値,あるいはダイバージェンス限界値を推定する新しい方法を提案する.離散化した応答は,自己回帰移動平均過程で表わせると仮定し,自己回帰および移動平均過程の次数と係数は赤池の推定...

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Material Type: 文書・図像類
Title: New Estimation Method for Flutter or Divergence Boundary from Random Responses at Subcritical Speeds
Author/Editor: 松崎, 雄嗣
安藤, 泰勝
MATSUZAKI, Yuji
ANDO, Yasukatsu
Author Heading: 松崎, 雄嗣
安藤, 泰勝
MATSUZAKI, Yuji
ANDO, Yasukatsu
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1981-04
Publication Date (W3CDTF): 1981-04
Periodical title: Technical Report of National Aerospace Laboratory TR-667T
No. or year of volume/issue: 667T
Volume: 667T
Pages: 14-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: eng
Target Audience: 一般
Note (General): 従来の様に減衰率と振動数の測定や推定をすることなく,サブクリティカルな領域での気流の乱れによって励振された応答からフラッタ限界値,あるいはダイバージェンス限界値を推定する新しい方法を提案する.離散化した応答は,自己回帰移動平均過程で表わせると仮定し,自己回帰および移動平均過程の次数と係数は赤池の推定法を用いて決定する.限界値の推定は自己回帰係数で表示されるJuryの安定行列式を用いて行う.本手法を,当所の遷音速フラッタ試験設備を用いて行った片持翼の試験結果に適用し,限界値より十分低い動圧のデータから精度良くフラッタ限界値の推定が出来ることを明らかにした.
The present paper describes a new technique for estimating the flutter or divergence boundary from responses due to turbulence at subcritical speeds. The boundary can be predicted without estimating or measuring the dampings and frequencies of the aeroelastic modes. The sampled time response is modeled by the mixed autoregressive moving average process. The orders and coefficients of both autoregressive and moving average parts of the process are determined with the aid of Akaike's estimation procedure. The stability boundary is estimated by using Jury's stability determinants which are expressed in terms of the autoregressive coefficients alone. The modal frequencies and damping are also evaluated from the coefficients. The technique proposed has been applied with success to signals from a cantilever wing model tested in a low supersonic flow. Comparison between the actual and estimated flutter boundaries shows that an accurate estimation can be made from data obtained in a narrow range of the dynamic pressure which is sufficiently below the boundary.
資料番号: NALTR0667000
レポート番号: NAL TR-667T
Access Restrictions: 限定公開
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ