摘要
针对相同空间约束条件下鸭式布局微小型制导弹药尾翼气动设计问题,提出了弹出式尾翼与折叠式尾翼两种解决方案,完成了两种方案气动外形的三维建模,利用计算流体力学方法计算得出0.4-0.8Ma之间的气动特性,分析比较两者的阻力特性和升力特性,得到了折叠式尾翼对微小型制导弹药的增升效果优于弹出式尾翼的结论。在微小型制导弹药的设计过程中,可利用折叠式尾翼设计方法有效的提高微小型制导弹药的可用过载。
Two aerodynamic design schemes for tail of canard-controlled miniature guided ammunition were presented in this paper,i. e.,pop-up tail and folded tails. The aerodynamic shape modeling for the two schemes was completed firstly. Then,the aerodynamic characteristics between 0. 4 Ma and 0. 8 Ma were calculated by the computational fluid dynamics method. Thus,the drag characteristics and lift characteristics of the two schemes were analyzed and compared. The calculation and analysis results show that the folded tail is better than pop-up tail in the same space constraints on increasing lift and improving available overload.
出处
《弹箭与制导学报》
CSCD
北大核心
2016年第1期135-139,共5页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
国家自然科学基金(61201417)
北京市科技新星计划(xxjh2015B041)
北京市教委青年拔尖人才培育计划(CIT&TCD201504055)资助
关键词
微小型制导弹药
弹出式尾翼
折叠式尾翼
气动特性
miniature guided ammunition
pop-up tail
folded tail
aerodynamic characteristics
