S-S双翼末敏弹气动外形优化设计

Optimum Design on Aerodynamic Shape of the S-S Style Non-parachute Terminal Sensitive Projectile

为获得S-S型双翼末敏弹最佳尾翼气动外形,基于计算流体力学和正交试验方法,以S-S型末敏弹模型的气动参数为源数据,对尾翼弯折面积和弯折角两因素组合进行优化设计,得到了此类型末敏弹尾翼参数对气动特性影响的主次关系,并提出了满足最大阻力系数和最大极阻尼力矩系数的末敏弹尾翼结构。结果表明:优化所得气动结构比优化前模型阻力系数提高7.11%,极阻尼力矩系数提高15.77%。高塔自由飞行试验结果显示:优化所得气动外形末敏弹落速为30.0 m/s,转速为11.5 r/s,下落过程中落速和转速及扫描角保持稳定,满足稳态扫描的要求。

To seek the best aerodynamic shape of S-S style wings terminal sensitive projectile （TSP） , based on computational fluid dynamics and orthogonal test, the wing bent area and bent angle are opti- mized with source aerodynamic parameters of the S-S style TSP aerodynamic model. Then the primary and secondary relations of wing parameters which affect the aerodynamic characteristics are obtained, and one aerodynamic shape, which has the largest drag coefficient and polar torque coefficient, is determined. The results show that, compared with the initial model, the drag coefficient increases by 7.11% and the torque coefficient increases by 15.77%. The tower free flight tests showed that the falling speed and rota- tion speed of the optimized TSP structure are 30.0 m/s and 11.5 r/s, respectively. The falling speed, ro- tation speed and scanning angle of TSP stayed steady during its falling which means that the optimized aerodynamic shape can lead to steady scanning motion.