新型卷弧刀翼探索研究  

Exploratory Research on the Innovative Blade Fin

作　　者：付梦思 陈浩[1] 王林林 李巍[1] 赵利军[1] Fu Meng-si;Chen Hao;Wang Lin-lin;Li Wei;Zhao Li-jun(Beijing Institute of Space Long March Vehicle,Beijing,100076)

机构地区：[1]北京航天长征飞行器研究所,北京100076

出　　处：《导弹与航天运载技术（中英文）》2023年第1期132-134,共3页Missiles and Space Vehicles

摘　　要：旨在解决强空间的约束下的尾翼增稳问题。结合马刀翼气动效率高和卷弧翼尺寸约束少的优点,创新性提出卷弧刀翼方案。通过结构设计,实现卷弧刀翼的折叠与展开锁定。采用CFD方法,计算了卷弧刀翼的气动特性,并将其与栅格翼结果进行了对比分析。结果表明,在一定马赫数范围内,卷弧刀翼增稳效果与栅格翼相当,阻力远小于栅格翼。卷弧刀翼作为一种新型增稳尾翼,具有工程可实现性,有望在尺寸约束和阻力约束都较强的环境下获得广泛应用。An innovative scheme which is called blade fin is proposed by combining the advantages of high aerodynamic efficiency of saber fin and less dimensional constraints of wrap-around fin to solve the stability augmentation problem in a finite space.The deployment and locking mechanism of the blade fin is realized in the structure design process.CFD method is used in the comparison of aerodynamic characteristics between blade fin and grid fin.The results show that the blade fin is equivalent to the grid fin in stability enhancement while it induces much less drag than the grid fin within a certain Mach number range.As an innovative type of stabilizing fin,the blade fin is feasible in engineering and can be widely used on the condition of strict constraints in both dimension and drag.

关 键 词：卷弧刀翼 栅格翼 机构设计 气动特性 

分 类 号：V525[航空宇航科学与技术—人机与环境工程]