Nonlinear aeroelastic analysis of a twin-tail boom UAV with rudder freeplay nonlinearities  

作　　者：Liuyue BAI Zhigang WU Chao YANG 

机构地区：[1]School of Aeronautic Science and Engineering,Beihang University,Beijing 10019l,China

出　　处：《Chinese Journal of Aeronautics》2024年第9期276-296,共21页中国航空学报（英文版）

摘　　要：The issue of nonlinear structural freeplays in aircraft has always been a significant con-cern.This study investigates the aeroelastic characteristics of a twin-tail boom Unmanned Aerial Vehicle(UAV)with simultaneous freeplay nonlinearity in its left and right rudders.A comprehen-sive Limit Cycle Oscillation(LCO)solution route is proposed for complex aircraft with multiple freeplays,which can consider both accuracy and effciency.For the first time,this study reveals the unique LCO characteristics exhibited by twin-tail boom UAVs with rudder freeplays and pro-vides simulations and explanations of interesting phenomena observed during actual flight.The governing equations are established using the free-interface component mode synthesis method,and the LCOs of the system are mainly solved through the improved time-domain numerical con-tinuation method and frequency-domain numerical continuation method.Furthermore,the study investigates the influence of the left and right rudder freeplay size ratio on the LCO characteristics.The results demonstrate that the twin-tail boom UAV exhibits two stable LCO types:close and dif-fering left and right rudder amplitudes.The proposed method successfully describes the complete LCO behaviors of the system.Overall,this study makes significant contributions to our understand-ing of the aeroelastic behavior of twin-tail boom UAVs with rudder freeplays.

关 键 词：Aeroelasticity Freeplay nonlinearity Limit cycle oscillation Numerical continuation Component mode synthesis 

分 类 号：V279[航空宇航科学与技术—飞行器设计] V211.47