Predicting wing-pylon-nacelle configuration flutter characteristics using adaptive continuation method  

作　　者：Qijing Yu M.Damodaran B.C.Khoo 

机构地区：[1]Department of Mechanical Engineering,The Open University of China,Beijing 100039,China [2]Engineering Research Center of Integration and Application of Digital Learning Technology,Ministry of Education,Beijing 100039,China [3]Temasek Laboratories,National University of Singapore,Singapore 117411,Singapore [4]Department of Mechanical Engineering,National University of Singapore,Singapore 117575,Singapore

出　　处：《Advances in Aerodynamics》2023年第1期428-451,共24页空气动力学进展（英文）

基　　金：the Innovation Fund of the Engineering Research Center of Integration and Application of Digital Learning Technology,Ministry of Education(1221043);the Youth Research Project-The Open University of China(Q21A0009);the Adult continuing education research program-China Adult Education Association(2021-326Y).

摘　　要：In this study,the aeroelastic response of a wing-pylon-nacelle system in subsonic and low supersonic flow regimes is analyzed using the continuation method in conjunction with an adaptive step size control algorithm.Idealizing the pylon and nacelle as a point mass,the computed effects of a standard structural analysis of the wing together with the pylon and nacelle are compared with those of a clean wing to build a reduced-order model for analysis.The aerodynamic forces relating to different reduced frequencies are assessed using the Doublet Lattice Method(DLM)in the subsonic flow regime and supersonic lifting surface theory relying on the unsteady linearized small-disturbance potential flow model in the low supersonic flow regime.The Rational Function Approximation(RFA)method is then utilized for the state-space formulation of the system equations,appended with the continuation method for flutter prediction.Thereafter,the linearized aeroelastic equations are resolved using the continuation method with adaptive step size,the results of which are matched with those obtained from the traditional p-k method to emphasize that the continuation method exhibits a distinct advantage in achieving better accuracy in estimating the flutter speed and identifying the“mode switching”phenomenon.

关 键 词：Aeroelasticity Continuation method with adaptive step-size FLUTTER 

分 类 号：V21[航空宇航科学与技术—航空宇航推进理论与工程]