以大展弦比轴对称气动布局为研究对象，通过数学仿真计算和风洞试验得到大展弦比轴对称气动布局的升阻力特性和弹翼受力情况。考虑到弹翼在气动载荷作用下会产生上翻现象，分析了弹翼上翻5°和10°时对全弹升阻力的影响。针对大展弦比气动布局采用折叠式弹翼组件的特点，分析了弹翼展开机构不同步对全弹气动特性的影响。结果表明，弹翼上翻对升力影响较大，对阻力影响可以忽略；弹翼展开不同步对全弹气动特性影响较小。根据小型无人机载弹作战任务，提出了大展弦比轴对称气动布局在无人机弹药上使用的建议。%In order to study the high-aspect-ratio axial-symmetrical aerodynamic configuration of small am-munition,the lift-drag characteristics of the aerodynamic configuration and the force on elastic wing were obtained by mathematical simulation and wind tunnel test. Taking into account the effect of the elastic wing on the aerodynamic load, the effects of the wing turning over 5° and 10° on the whole spring resistance were analyzed. Aiming at the characteristics of the folding wing assembly,the impact of the de-ployable mechanism on the aerodynamic characteristics of the projectile was analyzed. The results show that the effect of the wing turning over on the lift force is great, and the effect on drag force can be neglected. The non synchronization of missile wing has little influence on the aerodynamic characteristics of the whole missile. Based on the operational mission of the small unmanned aerial vehicle,the use of the high-aspect-ratio axial-symmetrical aerodynamic configuration on the UAV ammunition was proposed.
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