摘要
本文采用数值模拟方法研究亚音速和超音速条件下,反安定面展弦比对双鸭式布局导弹的近距耦合效应的影响。建立了数学模型,验证了数值方法,对展弦比为0.3、0.6和0.9的鸭式布局导弹进行了对比分析,重点研究了来流工况为Ma为0.5和2时,在不同攻角、不同展弦比下两鸭舵之间的涡系演变过程,并对舵面法向力和俯仰力矩进行了分析。结果表明:亚音速条件下,当展弦比为0.3时中大攻角以后近距耦合效应产生的增升效果明显,反安定面卷起的下洗涡与鸭舵涡卷绕融合后使之得到明显的增强,涡强度的增强延迟了鸭舵表面的流动分离,提高了失速后的法向力,并随着展弦比增加而提升效果减弱;当来流处于超音速时,随着展弦比的增加,鸭舵法向力先增大后减小,反安定面在展弦比为0.6左右时耦合效果较好;同时双鸭式布局反安定面在展弦比0.3~0.9范围内随着展弦比增加,提高操纵性效果越好。
In this paper,numerical simulation method was adopted to study the effect of aspect ration of anti-stabilizer on short-range coupling effect of dual canard missile under subsonic and supersonic conditions.The numerical models were established,and the reliability of the numerical method was verified.The evolution process of the vortex system between the two canards at different angles of attack and aspect ratios under the inflow conditions of Ma=0.5 and Ma=2 was studied.The normal force and pitching moment of the canard were analyzed.The results show that the near distance coupling effect is obvious when the aspect ratio is 0.3 under subsonic condition.The downwash vortex of anti stability surface is enhanced after merging with the whirlwind of canard.The enhancement of vortex strength delays the flow separation on the canard surface,improves the normal force after stall,and decreases with the increase of aspect ratio.When the inflow is in supersonic condition,the normal force of the canard increases first and then decreases with the increase of the aspect ratio,and the coupling effect of the anti stability surface is better when the aspect ratio is about 0.6.Meanwhile,with the increase of the aspect ratio of anti stability surface,the maneuverability effect of the dual canard missile is improved.
作者
吕代龙
陈少松
徐一航
邱佳伟
LV Dailong;CHEN Shaosong;XU Yihang;QIU Jiawei(School of Energy and Power engineering,Nanjing University of Science and Technology,Nanjing 290014,China)
出处
《弹道学报》
CSCD
北大核心
2022年第2期17-24,共8页
Journal of Ballistics
关键词
双鸭式布局
反安定面
近距耦合
展弦比
数值模拟
气动特性
double canard configuration
anti-stabilizer
close coupling
aspect ratio
numerical simulation
aerodynamic characteristics
