巡飞弹柔性弹翼气动特性研究  

Research on Aerodynamic Performance of Inflatable Wing for Loitering Munitions

作　　者：王昊宇[1] 王华[1] Wang Haoyu Wang Hua(School of Astronautics, Beihang University, Beijing 100191, China)

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《战术导弹技术》2017年第3期41-46,共6页Tactical Missile Technology

基　　金：航空创新基金(CASC0105)

摘　　要：为了分析柔性弹翼的气动特性,采用气动仿真软件分析了不同弹翼翼型的升阻比特性,获得了弹翼表面鼓包和弯曲变形对巡飞弹飞行气动特性的影响规律,采用模型飞行技术对柔性弹翼进行了试飞测试验证,结果表明柔性弹翼表面鼓包使得其阻力系数约增加5%,一定的挠度使得其升力系数相比于无弯曲变形时大幅提高。通过创新性地给弹翼增加光滑蒙皮进行整形,有助于负载能力和飞行质量的提升。In order to analysis the aerodynamic characteristics of inflatable wing,the aerodynamic simulations are used to analysis lift-to-drag ratio for vary airfoils,the influences that wing bulge surface and deflection on aerodynamic characteristics are obtained. At the same time,the flight experiments for inflatable wing were carried out. The results show that the drag coefficient of inflatable wing bulge was increased by 5%,certain deflection made the lift improve greatly without bending deformation. A innovative method is that smooth skin was added to wing,which benefits the raise of load capacity and quality of flight.

关 键 词：巡飞弹 充气弹翼 鼓包 挠度 飞行试验 

分 类 号：TJ013.2[兵器科学与技术—兵器发射理论与技术]