小型巡飞弹舵翼折叠形式气动特性数值研究

Numerical Study on the Aerodynamic Characteristics of the Folded Rudder Wing of Small Patrol Missile

摘要

小型巡飞弹普遍采用弹翼/舵翼折叠设计,以方便贮存携带。以“X”型布局的小型巡飞弹为研究对象,选用面对称纵向折叠弹翼+纵向折叠舵翼、面对称纵向折叠弹翼+横向折叠舵翼两种方案的气动模型,通过数值模拟手段,对2种巡飞弹方案的主要气动特性进行了计算分析。通过风洞试验手段验证了数值模拟的可靠性,在飞行速度为30 m/s的相同工况下对两种方案展开了气动特性研究,分析对比了两种方案的升阻特性、斜吹力矩特性、稳定性、操纵性以及机动特性。结果表明:在相同的巡飞弹结构尺寸限制情况下,与横向折叠舵翼方案相比,纵向折叠舵翼方案在阻力特性、操纵性、机动性等方面都具有优势,两种方案的升力特性、相同质心条件下静稳定性一致,横向折叠舵翼方案还存在斜吹力矩较大的问题。在相同的结构尺寸限制下,“X”型面对称折叠翼巡飞弹的纵向折叠舵翼方案比横向折叠舵翼方案具有更好的气动特性表现。

Abstract

Small cruise missile generally features folding wing rudders to facilitate storage and transportation. A small cruise missile with an X-type configuration was selected as the research object, and two aerodynamic models were established: one featuring planar-symmetric longitudinally folding wings paired with longitudinally folding control surfaces, and the other with planar-symmetric longitudinally folding wings combined with transversely folding control surfaces. The main aerodynamic characteristics of the two schemes were calculated and analyzed by numerical simulation. After the reliability of the numerical simulation was verified through wind tunnel tests, aerodynamic characteristic investigations of the two schemes were conducted under the same operating condition (flight speed: 30 m/s). Comparative analyses were performed on the lift-drag characteristics, oblique blowing moment characteristics, stability, controllability, and maneuverability of the two configurations. The results indicate that under the same structural size constraints of the cruise missile, the scheme with longitudinally folding control surfaces exhibits advantages in drag performance, controllability, and maneuverability compared with the transversely folding control surface scheme. The two schemes demonstrate consistent lift characteristics and static stability with the same center of mass, while the transversely folding control surface scheme suffers from the issue of a significantly larger oblique blowing moment. Under the same structural size limitations, the X-type planar-symmetric folding-wing loitering missile equipped with longitudinally folding control surfaces achieves superior aerodynamic performance compared to the transversely folding control counterpart.

关键词

巡飞弹 / 折叠翼 / 气动特性 / 数值模拟

Key words

patrol missile / folding wing / aerodynamic characteristics / numerical simulation

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