CAJ | 학술논문

大柔性太阳能无人机在气动载荷的作用下产生较大的弹性变形，基于刚性或线弹性假设的结构模型已然不能满足这类飞机配平与飞行载荷分析的精度要求。基于 co?rotational（CR）理论建立了大柔性飞机结构模型，并耦合片条气动力模型，提出了一种可以考虑几何非线性效应的大柔性飞机非线性配平及飞行载荷分析的方法。以类“太阳神”布局太阳能无人机为例，采用该方法对其不同有效载荷下的纵向配平及飞行载荷特性进行了较为深入的研究。研究结果表明：有效载荷较大时，采用线弹性假设的结构模型解得的配平误差可达50％以上，对翼尖位移的预测误差可达25％以上；该方法能够较合理地预测大柔性无人机的配平及飞行载荷特性，满足大柔性太阳能无人机结构设计对飞行载荷分析的工程精度要求。
대유성태양능무인궤재기동재하적작용하산생교대적탄성변형，기우강성혹선탄성가설적결구모형이연불능만족저류비궤배평여비행재하분석적정도요구。기우 co?rotational（CR）이론건립료대유성비궤결구모형，병우합편조기동력모형，제출료일충가이고필궤하비선성효응적대유성비궤비선성배평급비행재하분석적방법。이류“태양신”포국태양능무인궤위례，채용해방법대기불동유효재하하적종향배평급비행재하특성진행료교위심입적연구。연구결과표명：유효재하교대시，채용선탄성가설적결구모형해득적배평오차가체50％이상，대익첨위이적예측오차가체25％이상；해방법능구교합리지예측대유성무인궤적배평급비행재하특성，만족대유성태양능무인궤결구설계대비행재하분석적공정정도요구。
A very flexible solar powered UAV under aerodynamic load undergoes large deformation; thus it is im?possible to obtain its precise nonlinear trimming and flight load characteristics with the structural models that have rigid or linear assumptions. Therefore, combining the co?rotational theory with the aerodynamic strip theory, we de?velop an analysis algorithm which can deal with the geometrically nonlinear trimming and flight load characteristics of the very flexible solar?powered UAV. Taking a UAV with the layout similar to Helios for example, we explore the nonlinear trimming and flight load characteristics of the UAV under different payloads. The exploration results, given in Fig.5 through 12, and their analysis show preliminarily that: when applying the linear structural model to a large payload region, the trimming error of the UAV reaches 50% and the forecast error of its wingtip displacement reaches 25%. Our analysis algorithm can forecast the reasonable results on the very flexible solar?powered UAV and satisfy the precision requirements for the very flexible solar?powered UAV design in engineering.