小型巡飞弹舵翼折叠形式气动特性数值研究OA

Small cruise missile generally features folding wing rudders to facilitate storage and transportation.A small cruise missile with an X-type configuration was selected as the research object,and two aerodynamic models were established:one featuring planar-symmetric longitudinally folding wings paired with longitudinally folding control surfaces,and the other with planar-symmetric longitudinally folding wings combined with transversely folding control surfaces.The main aerodynamic characteristics of the two schemes were calculated and analyzed by numerical simulation.After the reliability of the numerical simulation was verified through wind tunnel tests,aerodynamic characteristic investigations of the two schemes were conducted under the same operating condition(flight speed:30 m/s).Comparative analyses were performed on the lift-drag characteristics,oblique blowing moment characteristics,stability,controllability,and maneuverability of the two configurations.The results indicate that under the same structural size constraints of the cruise missile,the scheme with longitudinally folding control surfaces exhibits advantages in drag performance,controllability,and maneuverability compared with the transversely folding control surface scheme.The two schemes demonstrate consistent lift characteristics and static stability with the same center of mass,while the transversely folding control surface scheme suffers from the issue of a significantly larger oblique blowing moment.Under the same structural size limitations,the X-type planar-symmetric folding-wing loitering missile equipped with longitudinally folding control surfaces achieves superior aerodynamic performance compared to the transversely folding control surface counterpart.