不同尾翼灵巧子弹气动特性实验研究

Experimental investigation on aerodynamic characteristics of smart submunitions with different tail fins

从无伞灵巧子弹稳态扫描的必要条件出发,设计了轴向折叠和径向折叠两种尾翼类型的子弹气动外形。设计了模型和实验装置,进行了小迎角低速风洞实验。获得了模型在固定和旋转条件下的气动力数据,测量了模型在气动力作用下的转速,对模型的稳定性进行了分析。实验结果表明:模型采用轴向折叠尾翼,能够设计足够有效的迎风面积和增阻效果良好的翼面形状,维持较为稳定的转速,具有良好的旋转稳定性;采用径向折叠尾翼的模型,增阻效果不明显,稳定旋转能力较差。实验结果为无伞灵巧子弹的设计提供了重要参考。

Based on the requirements of steady scanning of non-parachute smart submunitions,two kinds of aerodynamic configurations are designed,including lengthways-folded and radial-folded tail fins.Experimental models and equipments are designed and low speed wind tunnel experiment at small angles of attack is made.The aerodynamic force data of models both fixed and rotating are obtained and the rotate speed is measured.The stability of the models is analyzed.The experimental results indicated that the model with lengthways-folded tail fins have enough effective frontal area and wing shape of bigger resistance.The lengthways-folded tail fins can also keep steady rotating speed and make the model spin steadily.The model with radial-folded tail fins has bad capability of resistance and poor behave of steady rotating.The investigation gives important references to designs of non-parachute smart submunitions.