无伞末敏弹气动特性风洞实验研究

为实现末敏弹的无伞稳态扫描运动,设计了一种短圆柱轴向非对称尾翼子弹气动外形。设计了模型和实验装置,进行了大迎角低速风洞实验。获得了模型在有/无减旋翼、固定和自由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。实验结果表明:设计的尾翼能够为模型提供较大的阻力,旋转时模型的阻力系数有所减小;在有减旋翼的情况下,模型能够保持较低的稳定转速;模型的静稳定性较差;模型旋转时稳定性有较大的改善。需要进一步改进尾翼,提高静稳定性,为扫描角的稳定提供保证。实验结果可为无伞末敏弹的设计和改进提供参考。

Wind Tunnel Experimental Investigation on Aerodynamic Characteristics of Non-Parachute Terminal Sensitive Ammunition

A kind of projectile's aerodynamic configuration with short cylinder and axial asymmetric tail wings was designed. High angle of attack low speed wind tunnel experiment was carried out based on self-designed specimen model and experimental equipment. Aerodynamic force of model with or without rotating damping wing was obtained under being fixed or free rotating conditions. The rotate speed of model affected by aerodynamic force was also measured. Results show that the designed tail wings can provide large drag force for model, while the drag coefficient of model becomes smaller during rotating. The model with rotating damping wing can keep low stable spin rate. Model has bad static stability, but the stability is improved greatly when it is rotating. In order to improve the static stability of model and to guarantee the stability of the scanning angle, the tail wing shape needs to be optimized. Above mentioned investigation may provide reference for non-parachute TSA design and improvement.