CAJ | 학술논문

由于间隙的存在，随着速度的增加操纵面会发生非线性气动弹性响应，即操纵面发生极限环振动，其振动频率比飞机结构疲劳载荷谱的频率高，因此操纵面在每次飞行中只需经历1～2 s 的极限环振动，其在整个飞机服役期内累加得到的总循环数将达到10万次的量级，可见操纵面极限环振动引起的结构疲劳损伤不容忽视，所以需要建立起操纵面气动弹性数据（飞行速度和间隙）与结构疲劳损伤的对应关系。针对此问题，将非线性气动弹性分析方法和结构疲劳预测技术结合，发展一套分析流程用来讨论操纵面极限环振动与周边结构疲劳的关系，为设定操纵面间隙值提供参考。为了对此分析流程进行说明，对具有操纵面的复杂机翼进行了非线性气动弹性分析获得其偏转角响应，并将其转化为作用在作动器两头耳片上的疲劳载荷谱，通过疲劳分析获得周边结构疲劳特性与操纵面非线性气动弹性响应的关系。
유우간극적존재，수착속도적증가조종면회발생비선성기동탄성향응，즉조종면발생겁한배진동，기진동빈솔비비궤결구피로재하보적빈솔고，인차조종면재매차비행중지수경력1～2 s 적겁한배진동，기재정개비궤복역기내루가득도적총순배수장체도10만차적량급，가견조종면겁한배진동인기적결구피로손상불용홀시，소이수요건립기조종면기동탄성수거（비행속도화간극）여결구피로손상적대응관계。침대차문제，장비선성기동탄성분석방법화결구피로예측기술결합，발전일투분석류정용래토론조종면겁한배진동여주변결구피로적관계，위설정조종면간극치제공삼고。위료대차분석류정진행설명，대구유조종면적복잡궤익진행료비선성기동탄성분석획득기편전각향응，병장기전화위작용재작동기량두이편상적피로재하보，통과피로분석획득주변결구피로특성여조종면비선성기동탄성향응적관계。
Due to free play,aeroelastic response of a control surface is nonlinear,limited cycle vibration (LCO) occurs on the control surface.Frequencies of LCO are higher than those of fatigue load spectrum of a plane structure,the total vibration cycle number of the control surface with in a plane's lifetime will be more than one hundred thousand times, and the fatigue damage of the control surface induced by LCO has to be taken into account.Thus the relationship between the aeroelastic data of the control surface (free play and velocity)and structural fatigue damage should be established. Here,based on the nonlinear aeroelastic analysis and the structural fatigue analysis,an analysis procedure was developed to study the relationship between LCO of the control surface and structural fatigue damage,and this analysis procedure could guide the setting of free play.In order to illustrate this method,the rotational angle responses of a control surface were obtained with the nonlinear aeroelastic analysis.Based on these responses,the fatigue load spectrum was gained. Finally,the structural fatigue analysis was performed to obtain the relationship between the fatigue damage features of the periphery structures and the nonlinear aeroelastic response of a control surface.