Consideration for Flutter Prediction Parameters
The flutter boundary is conventionally estimated through the evaluation of the damping of critical mode. In addition to the difficulty of accurate measurement, however, the damping often changes abruptly toward zero near the critical flow speed. For two-mode systems authors have introduced the flutter margin for discrete-time systems (FMDS) in the previous paper and overcame the defect of the conventional method which uses damping as a measure of stability. In this paper new flutter prediction parameters applicable to three-mode systems are proposed. These parameters are constructed based on Jurys stability parameters for discrete-time systems. Numerical studies using a two-dimensional wing model shows that the new parameters decreases almost linearly in the whole subcritical range as the dynamic pressure increases, and the change of model configuration does not give a serious impact to the favorable property of the parameters. The parameters proposed are shown to satisfy important requirements for the accurate and reliable prediction of flutter boundary, and are superior to damping or Jurys stability parameter available presently.
aeroelasticity flutter prediction flight testing system identification autoregressive moving average model Jurys stability test
Tbrii Hiroshi
Department of Business Management, Meijo University, Nagoya 468-8502, Japan
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
917-920
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）