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兵工学报 ›› 2021, Vol. 42 ›› Issue (12): 2575-2585.doi: 10.3969/j.issn.1000-1093.2021.12.005

• 论文 • 上一篇    下一篇

旋转稳定弹扰流片气动外形多目标优化设计

钱龙1, 常思江1, 倪旖2   

  1. (1.南京理工大学 能源与动力工程学院, 江苏 南京 210094; 2.上海机电工程研究所, 上海 201109)
  • 发布日期:2022-01-15
  • 通讯作者: 常思江(1983—),男,副研究员,博士 E-mail:ballistics@126.com
  • 作者简介:钱龙(1995—),男,硕士研究生。E-mail: qianlong@njust.edu.cn
  • 基金资助:
    瞬态冲击技术重点实验室基金项目(6142606183107)

Multi-objective Optimization of Aerodynamic Shape of Microspoiler for Spin-stabilized Projectile

QIAN Long1, CHANG Sijiang1, NI Yi2   

  1. (1.School of Energy and Power Engineering,Nanjing University of Science and Technology,Nanjing 210094,Jiangsu,China;2.Shanghai Institute of Mechanical and Electrical Engineering,Shanghai 201109,China)
  • Published:2022-01-15

摘要: 为提升旋转稳定弹的射击精度,将微型扰流片应用于旋转稳定弹,可以为弹丸提供侧向升力、改变弹体姿态,继而达到改变飞行轨迹的目的。通过数值模拟方法计算扰流片轴向力系数、法向力系数和静力矩系数,分析扰流片气动系数随外形参数和马赫数的变化规律,以及外形参数和马赫数对平衡攻角的影响;以扰流片主要外形参数为设计变量,以弹道修正量和终点存速为目标,考虑攻角、修正能力、扰流片尺寸等约束,建立多目标优化设计模型,并采用遗传算法获得全局最优解。结果表明:采用扰流片对弹丸进行姿态调整、弹道修正的方法可行有效;在亚跨声速段扰流片外形参数存在升阻比最优解,在超声速下升阻比随马赫数增加呈下降趋势。

关键词: 旋转稳定弹, 扰流片, 气动特性, 多目标优化

Abstract: In order to improve the shooting accuracy of a spin-stabilized projectile,a microspoiler is used for the spin-stabilized projectile to provide lateral lift for the projectile,thus changing the projectile body attitude and achieving the purpose of changing the flight trajectory. Through the numerical simulation method,the axial force coefficient,normal force coefficient and static moment coefficient of microspoiler are calculated,the change of the aerodynamic coefficient of microspoiler with the shape parameters and Mach number is analyzed,and the influences of shape parameters and Mach number on the equilibrium angle of attack are analyzed. A multi-objective optimization design model is established. In the proposed model, the main shape parameters of microspoiler are used as design variables,the trajectory correction and the terminal remaining speed are taken as the optimiztion targets,and the angle of attack,correction ability,spoiler size and other constraints are considered. The genetic algorithm is used to obtain global optimal solution. The results show that the method of using the microspoiler to adjust the projectile's attitude and trajectory is feasible and effective;there is an optimal solution for the lift-to-drag ratio in the shape parameters of microspoiler in the sub-transonic range,and the lift-to-drag ratio decreases with the increase in Mach number at supersonic speed.

Key words: spin-stabilizedprojectile, microspoiler, aerodynamiccharacteristics, multi-objectiveoptimization

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