摘要
为保证管式发射折叠固定翼飞机出筒过程的可靠飞行,采用数值仿真方法分析研究了飞机在弹机分离阶段的气动特性。研究了飞机在不同机翼折叠角和出筒速度下的升力、阻力、压心位置和出筒速度动态变化对飞机气动特性的影响。结果表明:飞机在出筒过程前半段迎风面积少导致飞机升力小,应尽量缩短机翼展开时间。出筒过程中,飞机升阻比在飞机出筒前半段随着机翼折叠角的增大而增加,在后半段飞机升阻比逐渐趋于8。本文所研究串列式折叠固定翼飞机在出筒过程压心位置变化较小,压心位置最大波动量不超过5.62%。
In order to ensure the reliable flight of a gun-launched folding fixed-wing aircraft during the exit process,this paper studies the aerodynamic performance of the aircraft during the separation phase of the missile through numerical simulation.Firstly,the lift,drag and pressure center position of the aircraft under different wing folding angles and exit velocities are studied.Secondly,the influence of the dynamic change of the exit velocity on the aircraft aerodynamic characteristics are studied.The results show that the small windward area in the first half of the aircraft exit process leads to the small lift of the aircraft,and the wing deployment time should be minimized.In the process of exit,the aircraft lift-drag ratio increases with the increase of the wing folding angle in the first half of the aircraft exit,and the aircraft lift-drag ratio gradually tends to be 8 in the second half.In this paper,the pressure center position of the tandem folding fixed-wing aircraft has a small change during the exit process,and the maximum fluctuation of the pressure center position is less than 5.62%。
作者
杨海涛
习敏
廖贵超
胡建文
帅超
YANG Haitao;XI Min;LIAO Guichao;HU Jianwen;SHUAI Chao(No.710 Research and Development Institute,China State Shipbuilding Corporation Limited,Yichang 443000,China)
出处
《兵器装备工程学报》
CAS
CSCD
北大核心
2023年第S01期74-78,共5页
Journal of Ordnance Equipment Engineering
关键词
管式发射巡飞弹
折叠翼
气动特性
数值仿真
gun-launched loitering munitions
folding wings
aerodynamic performance
numerical simulation
