格尼襟翼对旋转导弹气动特性的影响  

Effect of Gurney flaps on aerodynamic characteristics of a spinning missile

作　　者：寇少博 冯立好[1] 李晓 杨欣 刘松彬 徐华松 KOU Shaobo;FENG Lihao;LI Xiao;YANG Xin;LIU Songbin;XU Huasong(Fluid Mechanics Key Laboratory of Education Ministry,Beihang University,Beijing 100191,China;Shanghai Institute of Mechanical and Electrical Engineering,Shanghai 201109,China)

机构地区：[1]北京航空航天大学流体力学研究所,北京100191 [2]上海机电工程研究所,上海201109

出　　处：《空气动力学学报》2023年第1期77-85,共9页Acta Aerodynamica Sinica

基　　金：上海航天科技创新基金。

摘　　要：旋转导弹多采用斜置尾翼产生滚转力矩,但存在转速稳定性差等问题,影响了命中精度。为改善旋转导弹气动特性,本文采用在导弹尾翼后缘放置格尼襟翼的方式代替传统斜置尾翼产生滚转力矩。通过数值模拟方法,研究了不同高度格尼襟翼对导弹气动特性的影响规律,并与斜置尾翼模型进行对比。结果表明:格尼襟翼能够产生保持导弹旋转的滚转力矩,且格尼襟翼高度增加,滚转力矩增大;相比斜置尾翼,格尼襟翼能够为导弹提供更大的滚转力矩,对导弹侧向力的影响相对更小。不同来流马赫数下格尼襟翼的操纵效率略有差异,亚声速来流时,格尼襟翼产生的滚转力矩随着导弹迎角增加而减小;超声速来流时,格尼襟翼产生的滚转力矩几乎不随迎角变化而改变,与亚声速来流相比,格尼襟翼的操纵效率降低。进一步通过分析流场揭示了格尼襟翼产生滚转力矩的流动机理:格尼襟翼使得导弹尾翼后缘附近产生非对称流动,以致各尾翼出现非对称的压力差,从而产生保持导弹旋转的滚转力矩。The spinning missiles usually adopt oblique tails to generate the rolling moment.However,such a configuration suffers from the problem of poor stability of rotating speed,which affects the hitting accuracy.To improve the aerodynamic performance of spinning missiles,the traditional oblique tails are substituted with Gurney flaps on the trailing edge of the tails to generate rolling moment in the present study.Effect of the Gurney flap height on the aerodynamic characteristics of the missile is studied by performing numerical simulations,and also compared with the oblique tail model.The results show that the Gurney flaps can generate the rolling moment for the missile,which increases with the Gurney flap height.Compared to the oblique tail model,the Gurney flaps can provide a larger rolling moment for the missile with a relatively small impact on side force.The maneuvering efficiency of the Gurney flaps is slightly different at different Mach numbers.The rolling moment decreases with the increase of the angle of attack in the subsonic regime,while it remains nearly unchanged with the angle of attack variation in the supersonic regime.Meanwhile,the maneuvering efficiency of the Gurney flaps is lower in the supersonic regime compared to that in the subsonic regime.It is found that,the Gurney flaps induce asymmetric flow near the trailing edge of the missile tail,resulting in the occurrence of asymmetric pressure difference among the tails,thus leading to the rolling moment generation.

关 键 词：旋转导弹 格尼襟翼 气动特性 滚转力矩 

分 类 号：TJ013[兵器科学与技术—兵器发射理论与技术]