CAJ | 학술논문

对采用复合材料玻璃纤维、碳纤维加工的静气动弹性模型进行了高速风洞试验研究，测试了模型的柔度矩阵、气动力、表面压力、弯／扭应变信号及弯／扭变形，为静气动弹性模型刚度试验、弯／扭应变信号测量、模型变形视频测量（VMD）及风洞总压控制等静气动弹性风洞试验能力的提高积累了经验，为飞行器静气动弹性研究提供了良好的试验平台。研究表明：静气动弹性模型较刚性模型升力线斜率及襟副翼效率下降、气动焦点前移；静气动弹性模型与刚性模型表面压力差异明显；在小迎角范围内，静气动弹性机翼模型弯／扭应变信号随迎角增加基本呈线性变化；在正迎角时，大展弦比后掠机翼静气动弹性模型的剖面扭转变形使有效迎角减小，剖面越靠近翼尖弯／扭变形越大。
대채용복합재료파리섬유、탄섬유가공적정기동탄성모형진행료고속풍동시험연구，측시료모형적유도구진、기동력、표면압력、만／뉴응변신호급만／뉴변형，위정기동탄성모형강도시험、만／뉴응변신호측량、모형변형시빈측량（VMD）급풍동총압공제등정기동탄성풍동시험능력적제고적루료경험，위비행기정기동탄성연구제공료량호적시험평태。연구표명：정기동탄성모형교강성모형승력선사솔급금부익효솔하강、기동초점전이；정기동탄성모형여강성모형표면압력차이명현；재소영각범위내，정기동탄성궤익모형만／뉴응변신호수영각증가기본정선성변화；재정영각시，대전현비후략궤익정기동탄성모형적부면뉴전변형사유효영각감소，부면월고근익첨만／뉴변형월대。
Experimental investigation on static aeroelastic was carried out in high speed wind tunnel using glass fiber models and carbon fiber models respectively.Flexibility matrix,aerody-namic force,pressure,bending/torsion strain signals and bending/torsional deformations of models are measured.Experience is accumulated for developing high speed wind tunnel static aeroelastic experimental techniques such as stiffness test,bending/torsion strain signals gauging, videogrammetric model deformation and wind tunnel total pressure control.The investigation shows:comparing with rigid model,lift curve slope and aileron/flap efficiency of static aeroelas-tic model decrease,aerodynamic center of static aerodynamic model shifts forward,pressure dis-tributions of static aeroelastic model change significantly;static aeroelastic wing model bending/torsion strain signals,which can be used to analyze aerodynamic loads,are nearly linear variation with attack angle at small attack angles,for lift coefficient and pitching moment coefficient of static aeroelastic wing model change linearly with attack angle at small attack angles;at the posi-tive attack angle,effective angle of attack decreases due to torsional deformation for high-aspect-ratio backward-swept wing static aeroelastic model,wing section bending/torsional deformations gradually increase as wing section position varies from wing-inboard to wing-tip.