大后掠机翼外侧翼下导弹气动特性分析

位于大后掠翼战斗机机翼下的导弹,在飞行中受到的气动载荷,会对结构疲劳特性产生显著影响。为了研究导弹的气动载荷,建立了某型战斗机挂载导弹的气动仿真模型,设计了 3种导弹构型,分别为带前后弹翼导弹、只带后弹翼的导弹与只有弹体不带弹翼的导弹。对飞机翼下挂载 3种不同构型的导弹进行了气动特性的数值模拟与分析,并对比了导弹的气动载荷分布规律。计算结果表明:位于大后掠机翼下方的导弹,由于机翼下方的洗流作用,会受到较大的气动载荷,导弹的气动载荷以侧力和滚转及偏转力矩为主要分量；滚转力矩的方向会导致导弹与发射装置连接处靠近飞机对称面一侧受力较大,容易降低疲劳寿命；导弹的气动载荷主要由后弹翼产生,可在设计弹翼时适当减小后弹翼的面积,从而降低战斗机后掠翼洗流对翼下挂载导弹气动特性的影响。

Analysisofa Aerodynamic Characteristicsof Missiles Under the Outer WingofLarge Swept Wings

Theaerodynamicloadonmissilesmountedunderlargesweptwingscanhaveasignificantimpactonstructural fatiguecharacteristics.To studytheaerodynamicload onmissiles,anaerodynamicmodelof afightermountedmissileis established.Threemissileconfigurationsaredesigned,namely, missileswithfrontandrearwings,missileswithonlyrear wings, and missiles with only body but no wings. Numerical simulation and analysis of aerodynamic characteristics are conductedonthreedifferentconfigurationsofmissilesmountedunderthewingoftheaircraft,andthedistributionofaero-dynamicloadsonthemissilesarecompared.Theresultsindicatethatthemissilemountedunderthewingwillbesubject-edtosignificantaerodynamicloadsdue tothewashingeffect.Theaerodynamicload onthemissileismainlycomposed oflateralforce,rollingandyaw moment.Thedirectionofrolling momentwillcauseagreaterforce ontheside nearthe plane of symmetry at the connection between the missile and the launch device, which will reduce the fatigue life.The aerodynamicload onthemissileismainlygeneratedbythe rearwing.The areaofthe rearwingcanbeappropriately re-ducedtoreducetheinfluenceofthewashflowofthefighter''ssweptwing ontheaerodynamiccharacteristicsofthemis-silemountedunderthewingwhendesigningthewing.